Tandem rotary detonation combustor system

Abstract

A combustor system is provided that includes rotating detonation combustors (RDCs) arranged in series. In some embodiments, a combustor system includes a volume that receives a core oxidant-fuel mixture. The combustor system includes a first RDC having a first detonation chamber. The first detonation chamber receives a first pilot oxidant-fuel mixture and is defined by a first channel formed in the peripheral wall. The combustor system also includes at least one additional RDC having a second detonation chamber. A second detonation chamber receives a second pilot oxidant-fuel mixture and is defined by a second channel formed in the peripheral wall. The first pilot oxidant-fuel mixture reacts in the first detonation chamber and the second pilot oxidant-fuel mixture reacts in the second detonation chamber to generate a rotating detonation combustion wave directed by the first channel and the second channel to support the reaction consuming the core oxidant-fuel mixture.

Description

[0001] Government interests

[0002] This invention was made with U.S. Government support under Department of Defense Award FA8650-19-D-2507. The Government has certain rights in this invention. Technical Field

[0003] These teachings relate generally to combustors, and more particularly, to rotating detonation combustors. Background Art

[0004] The typical gas turbine engine is based on the Brayton cycle, in which air is compressed adiabatically, heat is added at a constant pressure, the resulting hot gases are expanded in a turbine, and the heat is rejected at a constant pressure. Energy above that required to drive the compression system can then be used for propulsion or other work. Such gas turbine engines typically rely on deflagration combustion to burn the fuel / air mixture and produce combustion gas products that travel within the combustion chamber at a relatively slow rate and constant pressure. Improvements in engine efficiency are sought by modifying the engine architecture so that combustion occurs in the form of detonation. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] Various needs are at least partially met by providing a tandem rotating detonation combustor (RDC) system as described in the following detailed description, particularly when studied in conjunction with the accompanying drawings. A full and enabling disclosure of aspects of the present specification, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, wherein:

[0006] Figure 1A A schematic perspective view of a first embodiment including a burner system having a series RDC;

[0007] Figure 1B Including the intercept along line 1B Figure 1A A schematic cross-sectional view of a burner system;

[0008] Figure 2 A schematic cross-sectional side view of a second embodiment including a burner system having a series RDC;

[0009] Figure 3 A schematic cross-sectional side view of a third embodiment including a burner system having a series RDC;

[0010] Figure 4 A schematic cross-sectional side view of a fourth embodiment including a burner system having a series RDC;

[0011] Figure 5 A schematic cross-sectional side view of a fifth embodiment including a burner system having a series RDC;

[0012] Figure 6 A schematic cross-sectional side view of a sixth embodiment including a burner system having a series RDC;

[0013] Figure 7 A schematic cross-sectional side view of a seventh embodiment including a burner system having a series RDC;

[0014] Figure 8 A schematic cross-sectional side view of an eighth embodiment including a burner system having a series RDC;

[0015] Fig. 9 A schematic cross-sectional side view of a ninth embodiment including a burner system having a series RDC;

[0016] Fig.10 A schematic cross-sectional side view of a tenth embodiment including a burner system having a series RDC;

[0017] Fig.11 A schematic cross-sectional side view of an eleventh embodiment including a burner system having a series RDC;

[0018] Fig.12 A schematic cross-sectional side view of a twelfth embodiment including a burner system having a series RDC;

[0019] Fig.13 A schematic cross-sectional side view of a thirteenth embodiment including a burner system having a series RDC;

[0020] Fig.14 A schematic cross-sectional side view of a fourteenth embodiment including a burner system having a series RDC;

[0021] Fig.15 A schematic cross-sectional side view of a fifteenth embodiment including a burner system having a series RDC;

[0022] Fig.16 A schematic cross-sectional side view of a sixteenth embodiment including a burner system having a series RDC;

[0023] Fig.17 A schematic cross-sectional side view of a seventeenth embodiment including a burner system having a series RDC;

[0024] Fig.18 A schematic cross-sectional side view of an eighteenth embodiment including a burner system having a series RDC;

[0025] Fig.19 A schematic cross-sectional side view of a nineteenth embodiment including a burner system having a series RDC;

[0026] Fig. 20 A schematic cross-sectional side view of a twentieth embodiment including a burner system having a series RDC;

[0027] Fig.21 A schematic diagram of a gas turbine engine having a tandem RDC including various embodiments according to these teachings;

[0028] Fig. 22 including schematic diagrams of ramjets / scramjets with tandem RDCs according to various embodiments of these teachings;

[0029] Fig.23 including schematic diagrams of ramjets / scramjets with tandem RDCs according to various embodiments of these teachings;

[0030] Fig.24 A schematic diagram of a rocket engine having a tandem RDC including various embodiments according to these teachings; and

[0031] Fig.25 A flow chart of a method of supporting a combustion reaction using at least two RDCs arranged in series is included.

[0032] The elements in the drawings are shown for simplicity and clarity and are not necessarily drawn to scale. For example, the size and / or relative positioning of some elements in the drawings may be exaggerated relative to other elements to help improve the understanding of the various embodiments of the present teachings. In addition, common but well-understood elements that are useful or necessary in commercially feasible embodiments are generally not depicted to facilitate less obstructed viewing of these different embodiments of the present teachings. Certain actions and / or steps may be described or depicted in a specific order of occurrence, but those skilled in the art will understand that such specificity regarding order is not actually required. DETAILED DESCRIPTION

[0033] Compared with the constant pressure combustion process, the detonation-based pressure gain combustion process has the potential to provide a combustion system with higher fuel efficiency and even reduced weight, size, or both. Rotating detonation combustion is a detonation-based pressure gain combustion process. Detonation can be initiated in a detonation chamber by igniting a mixture of fuel and oxidant. The detonation products expand out of the chamber and are pushed out by the incoming fuel and oxidant. Rotating detonation combustion may include one or more detonation waves traveling around the detonation chamber azimuth. However, the performance of rotating detonation combustion may depend on the percentage of heat release occurring in the detonation mode. In general, a rotating detonation combustor (RDC) system combines at least two RDCs arranged in series to increase, maximize, optimize, etc. The heat release occurring in the detonation mode. Compared with conventional detonation-based burners, detonation burners can result in shorter burners. The pressure gain of the detonation burner can also improve the overall cycle efficiency. Compared with the detonation mode, the performance of the RDC is proportional to the amount of heat released by the detonation mode. Combining at least two RDCs in series as described herein may maximize or otherwise increase heat release in the detonation mode to achieve improved performance by increasing the maximum pressure and temperature in the cycle and thereby enhancing available useful work or thrust.

[0034] In combination with RDCs in series, including RDCs of different sizes (e.g., having different diameters, volumes, etc.) can also increase the operating range and scalability of the combustor. For example, by using smaller RDCs, smaller amounts of oxidizer and fuel can be consumed. In addition, by using fewer RDCs simultaneously (e.g., producing a smaller amount of thrust), a smaller amount of oxidizer and fuel can be consumed. In contrast, by using more RDCs simultaneously, a larger amount of oxidizer and fuel can be consumed. In addition, by using larger RDCs (e.g., producing a larger amount of thrust), a larger amount of oxidizer and fuel can be consumed. Therefore, compared to a single RDC, including at least two RDCs in series can achieve more precise control by fine-tuning thrust and outlet temperature. In addition, including RDCs of different diameters in series can produce different operating frequencies, and the different operating frequencies can have a beneficial interaction with engine noise or possible mechanical wear of downstream machinery.

[0035] Additionally, conventional detonation combustors may face challenges in maintaining combustion efficiency throughout a cycle or mission. Certain applications may require diffusion of the heat released by the detonation combustion reaction. Multiple RDCs in a series arrangement that can be operated individually or together can address these challenges to increase the operability and flexibility of the RDC.

[0036] The series RDC described herein can be incorporated into a gas turbine engine. A gas turbine engine generally includes a core engine system and an exhaust system. The core engine system includes an engine turbomachinery, and the exhaust system includes an outlet nozzle that generates thrust. In some high-performance gas turbine engines, the exhaust system may incorporate an enhancer, also known as an afterburner. The enhancer is generally located at the end of the engine turbomachinery, in a duct upstream of the outlet nozzle. In operation, the enhancer can provide additional heat to the exhaust oxidant flow leaving the core engine system to increase engine thrust. Incorporating an enhancer into a gas turbine engine may add additional axial length and volume, particularly to the exhaust system of the gas turbine engine. The increase in axial length and volume also increases the weight of the gas turbine engine, which further leads to an increase in fuel consumption. By incorporating a series RDC into an enhancer, increased heat release can be achieved, and thus thrust can be increased without increasing or reducing the length or volume of the exhaust system.

[0037] The tandem RDCs described herein may also be incorporated into a ramjet, scramjet, or rocket engine to provide additional heat to the exhaust oxidizer flow and enhance thrust.

[0038] Unless otherwise specified herein, the terms and expressions used herein have the ordinary technical meanings given to the terms and expressions by those skilled in the art in the above technical field. Unless otherwise specifically indicated, the word "or" used herein should be interpreted as having a disjunctive structure, not a conjunction structure. Unless otherwise specified herein, the terms "connect", "fix", "attach to", etc. refer to both direct connection, fixation or attachment, and indirect connection, fixation or attachment through one or more intermediate components or features.

[0039] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0040] As used herein throughout the specification and claims, approximating language is applied to modify any quantitative representation that can be permissibly varied without resulting in a change in the basic function to which it is related. Thus, values ​​modified by terms such as "about," "approximately," and "substantially" are not limited to the precise values ​​specified. In at least some cases, approximate language may correspond to the precision of an instrument used to measure a value, or the precision of a method or machine used to construct or manufacture a component and / or system. For example, approximate language may refer to within a 10% margin.

[0041] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0042] Referring now to the drawings, and in particular to FIGS. 1-11 , various embodiments of a burner system including a plurality of RDCs in series are shown. In the embodiments of FIGS. 1-11 , the RDC includes an outer channel having a pilot oxidant fuel supply coupled thereto, the pilot oxidant fuel supply acting as a pilot to induce a rotating detonation reaction in the burner system. The outer channel is formed in a first wall of the burner system, so that a rotating detonation wave induced in the outer channel can travel radially inward toward a core of the burner system. In this manner, the rotating detonation reaction induced by the outer pilot can support a combustion reaction occurring within the core.

[0043] Go to Figure 1A and Figure 1B , a first embodiment of a burner system 100 including a plurality of RDCs arranged in series is shown. The burner system 100 includes a series of RDCs having a centerless configuration and the same or similar cross-sectional areas. The burner system 100 includes a first wall 104 separated from a second wall 105 by a space 107. The first wall 104 defines a core 102. The first wall 104 is an inner wall of the burner system 100. The second wall 105 is an outer wall and may extend around the periphery of the burner system 100.

[0044] The first wall 104 defines the core 102. The core 102 receives the core oxidant fuel mixture 201. The core 102 includes a first detonation chamber 120, a second detonation chamber 124, and a third detonation chamber 130 arranged in series. The core 102 is an open space and has no center body. For reference, the centerline X extends axially through the core 102. The burner system 100 includes a first portion 103A and a second portion 103B. The first portion 103A is disposed upstream of the second portion 103B. The first portion 103A of the burner system 100 receives reactants for reactions occurring therein. The reactants may be used for combustion reactions, detonation reactions, or combinations thereof occurring within the burner system 100. The reactants may include a core oxidant-fuel mixture and / or one or more pilot oxidant-fuel mixtures. The oxidant may include any gas, liquid, or solid oxidant or a combination thereof. The fuel may include any gas, liquid, or solid fuel. For fluids, the fuel injection scheme may be different. The second portion 103B of the burner system 100 releases the reaction products. The reaction products may include combustion products, detonation products, or a combination thereof.

[0045] Although the burner system 100 is depicted as being cylindrical and the second wall 105 is straight, the burner systems described herein need not be cylindrical. For example, depending on the structure or engine in which the burner system 100 is implemented, the second wall 105 can have any suitable shape or configuration. It should be understood that the burner systems described herein can take any suitable shape as dictated by the application.

[0046] like Figure 1A As shown, the burner system 100 includes a first RDC 106, a second RDC 108, and a third RDC 110. Specifically, the first RDC 106, the second RDC 108, and the third RDC 110 are arranged in series. Although the burner system 100 is shown as including three RDCs, it is contemplated that any number of series RDCs can be incorporated into the burner system described herein. In some aspects, the burner system includes at least two RDCs arranged in series.

[0047] Go to Figure 1B , the first wall 104 of the burner system 100 includes a first outer channel 112, a second outer channel 126, and a third outer channel 132. The first outer channel 112 of the first wall 104 is coupled to a first pilot oxidant-fuel supply 123 through a first pilot fuel supply system 122. The first pilot oxidant-fuel supply 123 can be coupled to the first outer channel 112 in any suitable manner (e.g., through one or more openings in the first wall 104). The second outer channel 126 of the first wall 104 is coupled to a second pilot oxidant-fuel supply 129 through a second pilot fuel supply system 128. The second pilot oxidant-fuel supply 129 can be coupled to the second outer channel 126 in any suitable manner (e.g., through one or more openings defined in the first wall 104). The third outer channel 132 in the first wall 104 is coupled to a third pilot oxidant-fuel supply 135 through a third pilot fuel supply system 134. The third pilot oxidant-fuel supply 135 may be coupled to the third outer channel 132 in any suitable manner, such as, for example, through one or more openings in the first wall 104 .

[0048] In some approaches, the first pilot oxidant-fuel supply 123 , the second pilot oxidant-fuel supply 129 , and the third pilot oxidant-fuel supply 135 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 107 .

[0049] The first RDC 106 of the burner system 100 includes a first detonation chamber 120, a first outer channel 112, and a first pilot fuel supply system 122. The first outer channel 112 and the first pilot fuel supply system 122 act as a pilot for the first RDC 106. The first RDC 106 has a first cross-sectional area A1. The first detonation chamber 120 is at least partially defined by the first outer channel 112. The first outer channel 112 extends circumferentially around the centerline X of the burner system 100. The shape of the first detonation chamber 120 is generally cylindrical, however, in some methods, the first detonation chamber 120 can take other non-circular shapes (e.g., non-circular cross-sectional areas from an end view), such as rectangular or elliptical shapes. Because the core 102 does not have a center body, the first detonation chamber 120 is open and the shape is not annular. The size of the outer diameter of the first RDC 106 can vary based on the application. In some applications, such as missile, aircraft, power generation, and engine applications, the outer diameter of the first RDC 106 may be between about 3 inches and about 36 inches.

[0050] A first outer channel 112 is formed in the first wall 104. The first outer channel 112 is a stabilizing structure that can help stabilize or otherwise direct the rotating detonation wave generated in the first RDC 106. The first outer channel 112 is defined by a rearward-facing step 114 and a forward-facing step 116, which are recessed relative to adjacent portions of the first wall 104 and joined together by a recessed surface 118. The recessed surface 118 is, for example, recessed relative to adjacent portions of the first wall 104. The rearward-facing step 114 faces opposite to the flow direction in the core 102 (e.g., the flow through the core 102 will flow over the rearward-facing step 114). In contrast, the forward-facing step 116 faces the flow direction (e.g., the flow through the core 102 will impact the forward-facing step 116). One or more of the rearward-facing step 114 and the forward-facing step 116 may be inclined or disposed at an angle relative to the radial direction. For example, one or both of the rearward-facing step 114 and the forward-facing step 116 may not be perpendicular to the first wall 104, but may be tilted relative to the first wall 104. Inclining one or more of the rearward-facing step 114 and the forward-facing step 116 may help focus the energy from the rotating detonation wave radially through the first detonation chamber 120 and anchor the rotating detonation wave circumferentially to limit axial travel. It is also contemplated that one or more of the rearward-facing step 114 and the forward-facing step 116 may be curved or rounded. The first outer channel 112 may also lack the rearward-facing step 114 or the forward-facing step 116. In addition, the length of the first outer channel 112 (e.g., the length of the first outer channel 112 obtained from the rearward-facing step 114 to the forward-facing step 116) may vary depending on the application.

[0051] The first pilot fuel supply system 122. The first pilot fuel supply system 122 is configured to supply liquid, gaseous or solid fuel to the first outer channel 112. In this way, the first pilot fuel supply system 122 supplies the first pilot oxidant-fuel mixture to the first outer channel 112. Exemplary fuels include, but are not limited to, Jet-A fuel, methane, ethylene or H2 to the first RDC 106. The first pilot fuel supply system 122 delivers fuel or a pilot fuel-oxidant mixture to the first outer channel 112. The first pilot fuel supply system 122 may include any suitable fuel injection scheme, such as a nozzle, an impact double nozzle, a three-nozzle or a four-nozzle, a co-swirl injector, a reverse swirl injector or the like. The first pilot fuel supply system 122 may introduce oxidant together with the fuel, or it may bias more oxidant toward the centerline X of the first detonation chamber 120 to increase the oxidant availability of the subsequent RDC. In one non-limiting example, the first pilot fuel supply system 122 includes one or more vanes extending into the first outer channel 112. The vanes may include slots or other openings such that fuel is injected into the vanes and from the vanes through the slots or openings and into the first outer channel 112. In yet another example, the first pilot fuel supply system 122 includes one or more orifices through which fuel is injected from a fuel supply into the first outer channel 112. The first RDC 106 may also include an igniter ( Figure 1B 110). The igniter may be disposed, for example, in the first outer channel 112 and configured to ignite the oxidant-fuel mixture. Any suitable igniter may be used, such as a spark, a kernel, a pulse detonation wave, a plasma field, etc.

[0052] The second RDC 108 includes a second detonation chamber 124, a second outer channel 126, and a second pilot fuel supply system 128. The second RDC 108 has a second cross-sectional area A2. The second detonation chamber 124 is at least partially defined by the second outer channel 126. The second RDC 108 also includes a second pilot fuel supply system 128. The second detonation chamber 124, the second outer channel 126, and the second pilot fuel supply system 128 are formed similarly to the first detonation chamber 120, the first outer channel 112, and the first pilot fuel supply system 122, respectively.

[0053] The third RDC 110 includes a third detonation chamber 130, a third outer channel 132, and a third pilot fuel supply system 134. The third RDC 110 has a third cross-sectional area A3. The third detonation chamber 130 is at least partially defined by the third outer channel 132. The third RDC 110 also includes a third pilot fuel supply system 134. The third detonation chamber 130, the third outer channel 132, and the third pilot fuel supply system 134 are formed similarly to the first detonation chamber 120, the first outer channel 112, and the first pilot fuel supply system 122.

[0054] In the non-limiting example shown, the cross-sectional areas of the first RDC 106, the second RDC 108, and the third RDC 110 are approximately the same and do not vary from the first portion 103A of the burner system 100 to the second portion 103B of the burner system 100. That is, the first cross-sectional area A1, the second cross-sectional area A2, and the third cross-sectional area A3 are the same or approximately the same.

[0055] In operation, a rotating detonation reaction is initiated in one or more of the first RDC 106, the second RDC 108, and the third RDC 110. In the first RDC, the first pilot fuel supply system 122 supplies a pilot fuel or a pilot fuel-oxidant mixture to the first outer channel 112. The pilot fuel-oxidant mixture reacts in the first detonation chamber 120 of the first RDC 106. An igniter (not shown) ignites the pilot fuel-oxidant mixture in the first outer channel 112 to initiate a rotating detonation reaction. The rotating detonation reaction generates a rotating detonation wave. The first outer channel 112 can anchor the rotating detonation wave so that the wave propagates circumferentially around the first detonation chamber 120. In addition, the first outer channel 112 can help guide or direct the rotating detonation wave to the center line X of the volume so that the reaction can consume the core oxidant-fuel mixture (i.e., core flow) present at or near the center line X of the core 102. The rotating detonation wave may include a combustion front (i.e., a chemical reaction that occurs when the fuel-oxidant mixture burns) and a shock wave. The detonation reaction produces a combustion front coupled to the shock wave, and the combustion reaction includes a combustion front. Similar reactions occur in sequence in one or more of the second RDC 108 and the third RDC 110. The second RDC 108 burns the core flow in one or more of the combustion reaction and the detonation reaction, which consumes the remaining unburned fuel and oxygen leaving the first RDC 106. Similarly, the third RDC 110 burns the core flow in one or more of the combustion reaction and the detonation reaction, which consumes the unburned fuel and oxygen leaving the second RDC 108. The series RDC in the burner system 100 can promote a more efficient and compact combustion reaction. The compact nature of the combustion reaction limits the reaction to a smaller volume, thereby allowing the size of the burner system 100 to be reduced. Including the second RDC 108 and the third RDC 110 in series with the first RDC 106 can provide operational flexibility for the burner system 100. For example, any combination of the first RDC 106, the second RDC 108, and the third RDC 110 may be used in operation.

[0056] Go to Figure 2 , a second embodiment of a burner system 200 including a tandem RDC is shown. The burner system 200 includes a tandem RDC having approximately the same cross-sectional area and annular configuration due to the inclusion of a center body 240. Elements of the second embodiment similar to elements of the first embodiment have been given similar reference numbers in the 200 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as the first RDC 206 in the second embodiment.

[0057] The drawings of the various embodiments described herein include schematic depictions of combustor systems and various components thereof.Thus, the various components, such as the center body, may be formed in any suitable aerodynamic shape.

[0058] The burner system 200 includes a first wall 204 separated from a second wall 205 by a space 207. The first wall 204 defines a core 202 that receives a core oxidant fuel mixture 201. The core 202 includes a first detonation chamber 220, a second detonation chamber 224, and a third detonation chamber 230 arranged in series. The first wall 204 is an inner wall of the burner system 200. The second wall 205 is an outer wall and may extend around the periphery of the burner system 200.

[0059] The first wall 204 of the burner system 200 includes a first outer channel 212, a second outer channel 226, and a third outer channel 232. The first outer channel 212 of the first wall 204 is coupled to a first pilot oxidant-fuel supply 223 through a first pilot fuel supply system 222. The first pilot oxidant-fuel supply 223 can be coupled to the first outer channel 212 in any suitable manner (e.g., through one or more openings in the first wall 204). The second outer channel 226 of the first wall 204 is coupled to a second pilot oxidant-fuel supply 229 through a second pilot fuel supply system 228. The second pilot oxidant-fuel supply 229 can be coupled to the second outer channel 226 in any suitable manner (e.g., through one or more openings defined in the first wall 204). The third outer channel 232 in the first wall 204 is coupled to a third pilot oxidant-fuel supply 235 through a third pilot fuel supply system 234. The third pilot oxidant-fuel supply 235 may be coupled to the third outer channel 232 in any suitable manner (eg, through one or more openings in the first wall 204 ).

[0060] In some approaches, the first pilot oxidant-fuel supply 223 , the second pilot oxidant-fuel supply 229 , and the third pilot oxidant-fuel supply 235 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 207 .

[0061] The first RDC 206 includes a first detonation chamber 220, a first outer channel 212, and a first pilot fuel supply system 222. The first RDC 206 has a first cross-sectional area A1. The first detonation chamber 220 is at least partially surrounded by the first outer channel 212. The first pilot fuel supply system 222 delivers a first pilot oxidant-fuel supply 223 to the first outer channel 212.

[0062] The second RDC 208 includes a second detonation chamber 224, a second outer channel 226, and a second pilot fuel supply system 228. The second RDC 208 has a second cross-sectional area A2. The second detonation chamber 224 is at least partially surrounded by the second outer channel 226. The second pilot fuel supply system 228 delivers a second pilot oxidant-fuel supply 229 to the second outer channel 226.

[0063] The third RDC 210 includes a third detonation chamber 230, a third outer channel 232, and a third pilot fuel supply system 234. The third RDC 210 has a third cross-sectional area A3. The third detonation chamber 230 is at least partially surrounded by the third outer channel 232. The third pilot fuel supply system 234 delivers a third pilot oxidant-fuel supply 235 to the third outer channel 232.

[0064] The cross-sectional areas of the first RDC 206 , the second RDC 208 , and the third RDC 210 are approximately the same and thus do not vary from an upstream portion to a downstream portion of the combustor system 200 .

[0065] The combustor system 200 is similar to the combustor system 100 in most respects, except that the core 202 of the combustor system 200 includes a center body 240. Thus, the first detonation chamber 220, the second detonation chamber 224, and the third detonation chamber 230 are annular. An annular RDC is also known as a full-flow RDC, and is generally designed so that the tangential rotating detonation wave occupies the entire height and width of the annulus. Depending on the application (e.g., in applications where it is desired to maximize or otherwise increase thrust generation), an annular RDC can potentially result in improved performance.

[0066] Figure 3 A third embodiment of a burner system 300 including a series RDC is shown. The burner system 300 includes a plurality of RDCs arranged in series. The series RDCs in the burner system 300 have an increased cross-sectional area. Elements of the third embodiment similar to elements in the first embodiment have been given similar reference numbers in the 300 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as the first RDC 306 in the third embodiment.

[0067] The burner system 300 includes a first wall 304 separated from a second wall 305 by a space 307. The first wall 304 defines a core 302 that receives a core oxidant fuel mixture 301. The core 302 includes a first detonation chamber 320, a second detonation chamber 324, and a third detonation chamber 330 arranged in series. The first wall 304 is an inner wall of the burner system 300. The second wall 305 is an outer wall and may extend around the periphery of the burner system 300.

[0068] The first wall 304 of the burner system 300 includes a first outer channel 312, a second outer channel 326, and a third outer channel 332. The first outer channel 312 of the first wall 304 is coupled to a first pilot oxidant-fuel supply 323 through a first pilot fuel supply system 322. The first pilot oxidant-fuel supply 323 can be coupled to the first outer channel 312 in any suitable manner (e.g., through one or more openings in the first wall 304). The second outer channel 326 of the first wall 304 is coupled to a second pilot oxidant-fuel supply 329 through a second pilot fuel supply system 328. The second pilot oxidant-fuel supply 329 can be coupled to the second outer channel 326 in any suitable manner (e.g., through one or more openings defined in the first wall 304). The third outer channel 332 in the first wall 304 is coupled to a third pilot oxidant-fuel supply 335 through a third pilot fuel supply system 334. The third pilot oxidant-fuel supply 335 may be coupled to the third outer channel 332 in any suitable manner (eg, through one or more openings in the first wall 304 ).

[0069] In some approaches, the first pilot oxidant-fuel supply 323 , the second pilot oxidant-fuel supply 329 , and the third pilot oxidant-fuel supply 335 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 307 .

[0070] The burner system 300 has a centerbody-less design, and therefore, the core 302 is open and generally unobstructed from the centerline X of the core 302 to the first wall 304. The burner system 300 includes a first RDC 306, a second RDC 308, and a third RDC 310 arranged in series.

[0071] The first RDC 306 includes a first detonation chamber 320, a first outer channel 312, and a first pilot fuel supply system 322. The first RDC 306 has a first cross-sectional area A1. The first detonation chamber 320 is at least partially surrounded by the first outer channel 312. The first pilot fuel supply system 322 delivers a first pilot oxidant-fuel supply 323 to the first outer channel 312.

[0072] The second RDC 308 includes a second detonation chamber 324, a second outer channel 326, and a second pilot fuel supply system 328. The second RDC 308 has a second cross-sectional area A2. The second detonation chamber 324 is at least partially surrounded by the second outer channel 326. The second pilot fuel supply system 328 delivers a second pilot oxidant-fuel supply 329 to the second outer channel 326.

[0073] The third RDC 310 includes a third detonation chamber 330, a third outer channel 332, and a third pilot fuel supply system 334. The third RDC 310 has a third cross-sectional area A3. The third detonation chamber 330 is at least partially surrounded by the third outer channel 332. The third pilot fuel supply system 334 delivers a third pilot oxidant-fuel supply 335 to the third outer channel 332.

[0074] The burner system 300 is similar to the burner system 100 in most respects, except that the cross-sectional areas of the first RDC 306, the second RDC 308, and the third RDC 310 increase in size from an upstream portion of the burner system 300 to a downstream portion of the burner system 300. Thus, the second cross-sectional area A2 is greater than the first cross-sectional area A1, and the third cross-sectional area A3 is greater than the second cross-sectional area A2 (e.g., A1<A2<A3).

[0075] Figure 4 A fourth embodiment of a burner system 400 having a tandem RDC is shown. The burner system 400 includes a tandem RDC having an increased cross-sectional area with a center body 440. Elements of the fourth embodiment that are similar to elements in the first embodiment have been given similar reference numbers in the 400 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 406 in the fourth embodiment.

[0076] The burner system 400 includes a first wall 404 separated from a second wall 405 by a space 407. The first wall 404 defines a core 402 that receives a core oxidant fuel mixture 401. The core 402 includes a first detonation chamber 420, a second detonation chamber 424, and a third detonation chamber 430 arranged in series. The first wall 404 is an inner wall of the burner system 400. The second wall 405 is an outer wall and may extend around the periphery of the burner system 400.

[0077] The first wall 404 of the burner system 400 includes a first outer channel 412, a second outer channel 426, and a third outer channel 432. The first outer channel 412 of the first wall 404 is coupled to a first pilot oxidant-fuel supply 423 through a first pilot fuel supply system 422. The first pilot oxidant-fuel supply 423 can be coupled to the first outer channel 412 in any suitable manner (e.g., through one or more openings in the first wall 404). The second outer channel 426 of the first wall 404 is coupled to a second pilot oxidant-fuel supply 429 through a second pilot fuel supply system 428. The second pilot oxidant-fuel supply 429 can be coupled to the second outer channel 426 in any suitable manner (e.g., through one or more openings defined in the first wall 404). The third outer channel 432 in the first wall 404 is coupled to a third pilot oxidant-fuel supply 435 through a third pilot fuel supply system 434. The third pilot oxidant-fuel supply 435 may be coupled to the third outer channel 432 in any suitable manner (eg, through one or more openings in the first wall 404 ).

[0078] In some approaches, the first pilot oxidant-fuel supply 423 , the second pilot oxidant-fuel supply 429 , and the third pilot oxidant-fuel supply 435 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 407 .

[0079] The core 402 of the burner system 400 includes a center body 440. The center body 440 extends axially through the core 402 along a center line X. The core 402 is bounded by a first wall 404. The burner system 400 includes a first RDC 406, a second RDC 408, and a third RDC 410.

[0080] The first RDC 406 includes a first detonation chamber 420, a first outer channel 412, and a first pilot fuel supply system 422. The first detonation chamber 420 is at least partially surrounded by the first outer channel 412. The first pilot fuel supply system 422 delivers a first pilot oxidant-fuel supply 423 to the first outer channel 412.

[0081] The second RDC 408 includes a second detonation chamber 424, a second outer channel 426, and a second pilot fuel supply system 428. The second RDC 408 has a second cross-sectional area A2. The second detonation chamber 424 is at least partially surrounded by the second outer channel 426. The second pilot fuel supply system 428 delivers a second pilot oxidant-fuel supply 429 to the second outer channel 426.

[0082] The third RDC 410 includes a third detonation chamber 430, a third outer channel 432, and a third pilot fuel supply system 434. The third RDC 410 has a third cross-sectional area A3. The third detonation chamber 430 is at least partially surrounded by the third outer channel 432. The third pilot fuel supply system 434 delivers a third pilot oxidant-fuel supply 435 to the third outer channel 432.

[0083] The burner system 400 is similar to the burner system 100 in most respects, except that the size of the cross-sectional area of ​​the first RDC 406, the second RDC 408, and the third RDC 410 increases from the upstream portion of the burner system 400 to the downstream portion of the burner system 400. Therefore, the second cross-sectional area A2 is greater than the first cross-sectional area A1, and the third cross-sectional area A3 is greater than the second cross-sectional area A2 (e.g., A1<A2<A3). In addition, because the core 402 includes a center body 440, the first detonation chamber 420, the second detonation chamber 424, and the third detonation chamber 430 are annular in shape, rather than open cylinders in a center body-less configuration.

[0084] Figure 5 A fifth embodiment of a burner system 500 including a tandem RDC is shown. The burner system 500 includes a tandem RDC having a center body 540. The tandem RDCs in the burner system 500 have a combination of full flow, pilot flow, and center body-less configurations. Elements of the fifth embodiment that are similar to elements in the first embodiment have been given similar reference numbers in the 500 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as the first RDC 506 in the fifth embodiment.

[0085] The burner system 500 includes a first wall 504 separated from a second wall 505 by a space 507. The first wall 504 defines a core 502 that receives a core oxidant fuel mixture 501. The core 502 includes a first detonation chamber 520, a second detonation chamber 524, and a third detonation chamber 530 arranged in series. The first wall 504 is an inner wall of the burner system 500. The second wall 505 is an outer wall and may extend around the periphery of the burner system 500.

[0086] The first wall 504 of the burner system 500 includes a first outer channel 512, a second outer channel 526, and a third outer channel 532. The first outer channel 512 of the first wall 504 is coupled to a first pilot oxidant-fuel supply 523 through a first pilot fuel supply system 522. The first pilot oxidant-fuel supply 523 can be coupled to the first outer channel 512 in any suitable manner (e.g., through one or more openings in the first wall 504). The second outer channel 526 of the first wall 504 is coupled to a second pilot oxidant-fuel supply 529 through a second pilot fuel supply system 528. The second pilot oxidant-fuel supply 529 can be coupled to the second outer channel 526 in any suitable manner (e.g., through one or more openings defined in the first wall 504). The third outer channel 532 in the first wall 504 is coupled to a third pilot oxidant-fuel supply 535 through a third pilot fuel supply system 534. The third pilot oxidant-fuel supply 535 may be coupled to the third outer channel 532 in any suitable manner (eg, through one or more openings in the first wall 504 ).

[0087] In some approaches, the first pilot oxidant-fuel supply 523 , the second pilot oxidant-fuel supply 529 , and the third pilot oxidant-fuel supply 535 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 507 .

[0088] The combustor system 500 also includes a first RDC 506 , a second RDC 508 , and a third RDC 510 .

[0089] The first RDC 506 includes a first detonation chamber 520, a first outer channel 512, and a first pilot fuel supply system 522. The first detonation chamber 520 is at least partially surrounded by the first outer channel 512. The first pilot fuel supply system 522 delivers a first pilot oxidant-fuel supply 523 to the first outer channel 512.

[0090] The second RDC 508 includes a second detonation chamber 524, a second outer channel 526, and a second pilot fuel supply system 528. The second detonation chamber 524 is at least partially surrounded by the second outer channel 526. The second pilot fuel supply system 528 delivers a second pilot oxidant-fuel supply 529 to the second outer channel 526.

[0091] The third RDC 510 includes a third detonation chamber 530, a third outer channel 532, and a third pilot fuel supply system 534. The third detonation chamber 530 is at least partially surrounded by the third outer channel 532. The third pilot fuel supply system 534 delivers a third pilot oxidant-fuel supply 535 to the third outer channel 532.

[0092] The burner system 500 is similar to the burner system 100 in most respects, except that the core 502 of the burner system 500 includes a center body 540. The center body 540 has a first portion 541A and a second portion 541B. The first portion 541A is upstream of the second portion 541B. The first portion 541A of the center body 540 is disposed in the first RDC 506 and has a constant or approximately constant cross-sectional size. The second portion 541B of the center body 540 is disposed in the second RDC 508 downstream of the first RDC 506. The second portion 541B of the center body 540 has a tapered shape that decreases from the upstream end to the downstream end of the second portion 541B. The second portion 541B of the center body 540 terminates upstream of the third RDC 510.

[0093] Because the center body 540 extends through the first RDC 506 and the second RDC 508, the first detonation chamber 520 and the second detonation chamber 524 are annular. Due to the reduction in the cross-sectional size of the second portion 541B of the center body 540, the annular cross-sectional area of ​​the second detonation chamber 524 increases from upstream to downstream. In addition, because the center body 540 terminates upstream of the third RDC 510, the third detonation chamber 530 is center body-free, that is, it is uninterrupted from the centerline X of the core 502 to the first wall 504. So constructed, the burner system 500 includes a combination of a full-flow RDC (e.g., the first RDC 506), a pilot-flow RDC (e.g., the second RDC 508), and a center body-free RDC (e.g., the third RDC 510). In a full-flow RDC, the detonation wave is designed to occupy the entire height and width of the ring. In a pilot flow RDC, the detonation wave does not occupy one or more of the height and width of the ring and stabilizes the core flame in a detonation or deflagration mode within the ring. In a centerbody-less RDC, there is no centerbody, and therefore, the detonation is designed to extend through the core of the detonation chamber and reach the centerline X to consume the core oxidant-fuel mixture that may be present in the core of the detonation chamber. The detonation wave in the centerbody-less RDC burns the injected core fuel in a detonation mode or a deflagration mode or a combination thereof.

[0094] In some embodiments, the center body 540 can be translatable and can move through at least a portion of the core 502. For example, the center body 540 can be mechanically or fluidically translated in one or more of an upstream direction and a downstream direction along the centerline X. In this manner, the combustor system 500 can have a variable geometry. Translation of the center body 540 can change which of the first RDC 506, the second RDC 508, and the third RDC 510 is full flow, pilot flow, or center body-less.

[0095] Figure 6A sixth embodiment of a burner system 600 including a tandem RDC is shown. At least a portion of the burner system 600 includes a center body 640. The cross-sectional dimensions of at least a portion of the center body 640 decrease from upstream to downstream. The burner system 600 includes a combination of expansion tandem RDCs having a combination of full flow, pilot flow, and center body-less configurations. Elements of the sixth embodiment similar to those of the fifth embodiment have been given similar reference numbers in the 600 series, and only general differences will be discussed. For example, the first RDC 506 described in the fifth embodiment is numbered as first RDC 606 in the sixth embodiment.

[0096] The burner system 600 includes a first wall 604 separated from a second wall 605 by a space 607. The first wall 604 defines a core 602 that receives a core oxidant fuel mixture 601. The core 602 includes a first detonation chamber 620, a second detonation chamber 624, and a third detonation chamber 630 arranged in series. The first wall 604 is an inner wall of the burner system 600. The second wall 605 is an outer wall and can extend around the periphery of the burner system 600.

[0097] The first wall 604 of the burner system 600 includes a first outer channel 612, a second outer channel 626, and a third outer channel 632. The first outer channel 612 of the first wall 604 is coupled to a first pilot oxidant-fuel supply 623 through a first pilot fuel supply system 622. The first pilot oxidant-fuel supply 623 can be coupled to the first outer channel 612 in any suitable manner (e.g., through one or more openings in the first wall 604). The second outer channel 626 of the first wall 604 is coupled to a second pilot oxidant-fuel supply 629 through a second pilot fuel supply system 628. The second pilot oxidant-fuel supply 629 can be coupled to the second outer channel 626 in any suitable manner (e.g., through one or more openings defined in the first wall 604). The third outer channel 632 in the first wall 604 is coupled to a third pilot oxidant-fuel supply 635 through a third pilot fuel supply system 634. The third pilot oxidant-fuel supply 635 may be coupled to the third outer channel 632 in any suitable manner (eg, through one or more openings in the first wall 604 ).

[0098] In some approaches, the first pilot oxidant-fuel supply 623 , the second pilot oxidant-fuel supply 629 , and the third pilot oxidant-fuel supply 635 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 607 .

[0099] The combustor system 600 also includes a first RDC 606 , a second RDC 608 , and a third RDC 610 within the core 602 .

[0100] The first RDC 606 includes a first detonation chamber 620, a first outer channel 612, and a first pilot fuel supply system 622. The first RDC 606 has a first cross-sectional area A1. The first detonation chamber 620 is at least partially surrounded by the first outer channel 612. The first pilot fuel supply system 622 delivers a first pilot oxidant-fuel supply 623 to the first outer channel 612.

[0101] The second RDC 608 includes a second detonation chamber 624, a second outer channel 626, and a second pilot fuel supply system 628. The second RDC 608 has a second cross-sectional area A2. The second detonation chamber 624 is at least partially surrounded by the second outer channel 626. The second pilot fuel supply system 628 delivers a second pilot oxidant-fuel supply 629 to the second outer channel 626.

[0102] The third RDC 610 includes a third detonation chamber 630, a third outer channel 632, and a third pilot fuel supply system 634. The third RDC 610 has a third cross-sectional area A3. The third detonation chamber 630 is at least partially surrounded by the third outer channel 632. The third pilot fuel supply system 634 delivers a third pilot oxidant-fuel supply 635 to the third outer channel 632.

[0103] The burner system 600 includes a center body 640. The center body 640 has a first portion 641A and a second portion 641B. The first portion 641A is upstream of the second portion 641B. The first portion 641A of the center body 640 is disposed in the first RDC 606 and has a constant or approximately constant diameter (and cross-sectional area). The second portion 641B of the center body 640 is disposed in the second RDC 608 downstream of the first RDC 606. The second portion 641B of the center body 640 has a tapered shape that decreases from the upstream end to the downstream end of the second portion 641B. The second portion 641B of the center body 640 terminates upstream of the third RDC 610.

[0104] The burner system 600 is similar in most respects to the burner system 500, except that the core 602 of the burner system 600 is expanding. That is, the core 602 of the burner system 600 increases from the upstream end to the downstream end of the burner system. Thus, the first cross-sectional area A1 of the first RDC 606 is less than the second cross-sectional area A2 of the second RDC 608, and similarly, the second cross-sectional area A2 of the second RDC 608 is less than the third cross-sectional area A3 of the third RDC 610 (e.g., A1<A2<A3).

[0105] In some embodiments, the center body 640 can be translatable and can move through at least a portion of the core 602. For example, the center body 640 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0106] Figure 7 A seventh embodiment of a burner system 700 including a tandem RDC is shown. At least a portion of the burner system 700 includes a center body 740. The cross-sectional dimensions of at least a portion of the center body 740 increase from upstream to downstream. The burner system 700 includes a tandem RDC having a combination of no center body, pilot flow, and full flow configurations. Elements of the seventh embodiment similar to those in the first embodiment have been given similar reference numbers in the 700 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as the first RDC 706 in the seventh embodiment.

[0107] The burner system 700 includes a first wall 704 separated from a second wall 705 by a space 707. The first wall 704 defines a core 702 that receives a core oxidant fuel mixture 701. The core 702 includes a first detonation chamber 720, a second detonation chamber 724, and a third detonation chamber 730 arranged in series. The first wall 704 is an inner wall of the burner system 700. The second wall 705 is an outer wall and can extend around the periphery of the burner system 700.

[0108] The first wall 704 of the burner system 700 includes a first outer channel 712, a second outer channel 726, and a third outer channel 732. The first outer channel 712 of the first wall 704 is coupled to a first pilot oxidant-fuel supply 723 through a first pilot fuel supply system 722. The first pilot oxidant-fuel supply 723 can be coupled to the first outer channel 712 in any suitable manner (e.g., through one or more openings in the first wall 704). The second outer channel 726 of the first wall 704 is coupled to a second pilot oxidant-fuel supply 729 through a second pilot fuel supply system 728. The second pilot oxidant-fuel supply 729 can be coupled to the second outer channel 726 in any suitable manner (e.g., through one or more openings defined in the first wall 704). The third outer channel 732 in the first wall 704 is coupled to a third pilot oxidant-fuel supply 735 through a third pilot fuel supply system 734. The third pilot oxidant-fuel supply 735 may be coupled to the third outer channel 732 in any suitable manner (eg, via one or more openings in the first wall 704 ).

[0109] In some approaches, the first pilot oxidant-fuel supply 723 , the second pilot oxidant-fuel supply 729 , and the third pilot oxidant-fuel supply 735 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 707 .

[0110] The combustor system 700 also includes a first RDC 706 , a second RDC 708 , and a third RDC 710 within the core 702 .

[0111] The first RDC 706 includes a first detonation chamber 720, a first outer channel 712, and a first pilot fuel supply system 722. The first detonation chamber 720 is at least partially surrounded by the first outer channel 712. The first pilot fuel supply system 722 delivers a first pilot oxidant-fuel supply 723 to the first outer channel 712.

[0112] The second RDC 708 includes a second detonation chamber 724, a second outer channel 726, and a second pilot fuel supply system 728. The second detonation chamber 724 is at least partially surrounded by the second outer channel 726. The second pilot fuel supply system 728 delivers a second pilot oxidant-fuel supply 729 to the second outer channel 726.

[0113] The third RDC 710 includes a third detonation chamber 730, a third outer channel 732, and a third pilot fuel supply system 734. The third detonation chamber 730 is at least partially surrounded by the third outer channel 732. The third pilot fuel supply system 734 delivers a third pilot oxidant-fuel supply 735 to the third outer channel 732.

[0114] The burner system 700 is similar in most respects to the burner system 100, except that the core 702 of the burner system 700 includes a center body 740. The center body 740 is generally conical and has a tapered shape that increases from an upstream end of the center body 740 to a downstream end of the center body 740. The center body 740 is disposed downstream of the first RDC 706 and extends through the second RDC 708 and the third RDC 710.

[0115] Because the center body 740 extends through the second RDC 708 and the third RDC 710, the second detonation chamber 724 and the third detonation chamber 730 are annular. Due to the increasing conical shape of the center body 540, the annular cross-sectional area of ​​the second detonation chamber 724 and the third detonation chamber 730 decreases from upstream to downstream. In addition, because the center body 740 starts downstream of the first RDC 706, the first detonation chamber 720 is center body-free, that is, it is uninterrupted from the centerline X of the core 702 to the first wall 704. So configured, the combustor system 500 includes a combination of a center body-free RDC (e.g., the first RDC 706), a pilot flow RDC (e.g., the second RDC 708), and a full flow RDC (e.g., the third RDC 710).

[0116] In some embodiments, the center body 740 can be translatable and can move through at least a portion of the core 702. For example, the center body 740 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0117] Figure 8 The eighth embodiment of a burner system 800 including a series RDC. At least a portion of the burner system 800 includes a center body 840. The cross-sectional size of at least a portion of the center body 840 increases from upstream to downstream. The burner system 800 includes an expansion series RDC having a combination of no center body, pilot flow and full flow configurations. Elements of the eighth embodiment similar to those in the seventh embodiment have been given similar reference numbers in the 800 series, and only general differences will be discussed. For example, the first RDC 706 described in the seventh embodiment is numbered as the first RDC 806 in the eighth embodiment.

[0118] The burner system 800 includes a first wall 804 separated from a second wall 805 by a space 807. The first wall 804 defines a core 802 that receives a core oxidant fuel mixture 801. The core 802 includes a first detonation chamber 820, a second detonation chamber 824, and a third detonation chamber 830 arranged in series. The first wall 804 is an inner wall of the burner system 800. The second wall 805 is an outer wall and can extend around the periphery of the burner system 800.

[0119] The first wall 804 of the burner system 800 includes a first outer channel 812, a second outer channel 826, and a third outer channel 832. The first outer channel 812 of the first wall 804 is coupled to a first pilot oxidant-fuel supply 823 through a first pilot fuel supply system 822. The first pilot oxidant-fuel supply 823 can be coupled to the first outer channel 812 in any suitable manner (e.g., through one or more openings in the first wall 804). The second outer channel 826 of the first wall 804 is coupled to a second pilot oxidant-fuel supply 829 through a second pilot fuel supply system 828. The second pilot oxidant-fuel supply 829 can be coupled to the second outer channel 826 in any suitable manner (e.g., through one or more openings defined in the first wall 804). The third outer channel 832 in the first wall 804 is coupled to a third pilot oxidant-fuel supply 835 through a third pilot fuel supply system 734. The third pilot oxidant-fuel supply 835 may be coupled to the third outer channel 832 in any suitable manner (eg, via one or more openings in the first wall 804 ).

[0120] In some approaches, the first pilot oxidant-fuel supply 823 , the second pilot oxidant-fuel supply 829 , and the third pilot oxidant-fuel supply 835 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 807 .

[0121] The combustor system 800 also includes a first RDC 806 , a second RDC 808 , and a third RDC 810 within the core 802 .

[0122] The first RDC 806 includes a first detonation chamber 820, a first outer channel 812, and a first pilot fuel supply system 822. The first RDC 806 has a first cross-sectional area A1. The first detonation chamber 820 is at least partially surrounded by the first outer channel 812. The first pilot fuel supply system 822 delivers a first pilot oxidant-fuel supply 823 to the first outer channel 812. The second RDC 808 has a second cross-sectional area A2.

[0123] The second RDC 808 includes a second detonation chamber 824, a second outer channel 826, and a second pilot fuel supply system 828. The second detonation chamber 824 is at least partially surrounded by the second outer channel 826. The second pilot fuel supply system 828 delivers a second pilot oxidant-fuel supply 829 to the second outer channel 826. The third RDC 810 has a third cross-sectional area A3.

[0124] The third RDC 810 includes a third detonation chamber 830, a third outer channel 832, and a third pilot fuel supply system 834. The third detonation chamber 830 is at least partially surrounded by the third outer channel 832. The third pilot fuel supply system 834 delivers a third pilot oxidant-fuel supply 835 to the third outer channel 832.

[0125] The burner system 800 is similar in most respects to the burner system 700, except that the core 802 of the burner system 800 is expanding. That is, the core 802 of the burner system 800 increases from the upstream end to the downstream end of the burner system. Thus, the first cross-sectional area A1 of the first RDC 806 is less than the second cross-sectional area A2 of the second RDC 808, and similarly, the second cross-sectional area A2 of the second RDC 808 is less than the third cross-sectional area A3 of the third RDC 810 (e.g., A1<A2<A3).

[0126] In some embodiments, the center body 840 can be translatable and can move through at least a portion of the core 802. For example, the center body 840 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0127] Fig. 9 A ninth embodiment of a burner system 900 including a tandem RDC is shown. In particular, the burner system 900 includes an expanded centerbody-less tandem RDC. Elements of the ninth embodiment similar to elements in the first embodiment have been given similar reference numbers in the 900 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 906 in the ninth embodiment.

[0128] The burner system 900 includes a first wall 904 separated from a second wall 905 by a space 907. The first wall 904 defines a core 902 that receives a core oxidant fuel mixture 901. The core 902 includes a first detonation chamber 920, a second detonation chamber 924, a third detonation chamber 930, and a fourth detonation chamber 948 arranged in series. The first wall 904 is an inner wall of the burner system 900. The second wall 905 is an outer wall and can extend around the periphery of the burner system 900.

[0129] The first wall 904 of the burner system 900 includes a first outer channel 912, a second outer channel 926, a third outer channel 932, and a fourth outer channel 950. The first outer channel 912 of the first wall 904 is coupled to a first pilot oxidant-fuel supply 923 through a first pilot fuel supply system 922. The first pilot oxidant-fuel supply 923 can be coupled to the first outer channel 912 in any suitable manner (e.g., through one or more openings in the first wall 904). The second outer channel 926 of the first wall 904 is coupled to a second pilot oxidant-fuel supply 929 through a second pilot fuel supply system 928. The second pilot oxidant-fuel supply 929 can be coupled to the second outer channel 926 in any suitable manner (e.g., through one or more openings defined in the first wall 904). The third outer channel 932 in the first wall 904 is coupled to a third pilot oxidant-fuel supply 935 through a third pilot fuel supply system 934. The third pilot oxidant-fuel supply 935 may be coupled to the third outer channel 932 in any suitable manner, such as through one or more openings in the first wall 904. The fourth outer channel 950 in the first wall 904 is coupled to the fourth pilot oxidant-fuel supply 953 through a fourth pilot fuel supply system 952. The fourth pilot oxidant-fuel supply 953 may be coupled to the fourth outer channel 950 in any suitable manner, such as through one or more openings in the first wall 904.

[0130] In some methods, the first pilot oxidant-fuel supply 923, the second pilot oxidant-fuel supply 929, the third pilot oxidant-fuel supply 935, and the fourth pilot oxidant-fuel supply 953 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 907.

[0131] One difference between the first and ninth embodiments is that the burner system 900 has a first wall 904 that is stepped and defines a detonation chamber that increases in size from an upstream portion of the burner system 900 to a downstream portion of the burner system 900. Another difference is the shape of the first outer channel 912, the second outer channel 926, the third outer channel 932, and the fourth outer channel 950. The stepped arrangement of the first wall 904 forms a channel that lacks a forward-facing step and instead includes only a rearward-facing step 914 and a recessed portion 918. Although removing the forward-facing step may potentially reduce the effectiveness of the detonation wave penetrating toward the center, in some applications this may be a preferred approach.

[0132] The burner system 900 includes a first RDC 906, a second RDC 908, a third RDC 910, and a fourth RDC 946. The burner system 900 has a core 902 defined by a first wall 904. The core 902 has no center body. The first wall 904 is stepped to define a plurality of stabilizing structures therein (e.g., a first outer channel 912, a second outer channel 926, a third outer channel 932, and a fourth outer channel 950).

[0133] The first RDC 906 includes a first detonation chamber 920, a first outer channel 912, and a first pilot fuel supply system 922. The first RDC 906 has a first cross-sectional area A1. The first detonation chamber 920 is defined by the first outer channel 912. The first outer channel 912 includes a rearward step 914 and a recessed portion 918. The recessed portion 918 is recessed relative to an adjacent portion of the first wall 904. The first pilot fuel supply system 922 is coupled to the first outer channel 912 to deliver a first pilot oxidant-fuel supply 923 to one or more of the first outer channel 912 and the first detonation chamber 920.

[0134] The second RDC 908 includes a second detonation chamber 924, a second outer channel 926, and a second pilot fuel supply system 928. The second RDC 908 has a second cross-sectional area A2. The second detonation chamber 924, the second outer channel 926, and the second pilot fuel supply system 928 are similar to the first detonation chamber 920, the first outer channel 912, and the first pilot fuel supply system 922, respectively.

[0135] The third RDC 910 includes a third detonation chamber 930, a third outer channel 932, and a third pilot fuel supply system 934. The third RDC 910 has a third cross-sectional area A3. The third detonation chamber 930, the third outer channel 932, and the third pilot fuel supply system 934 are similar to the first detonation chamber 920, the first outer channel 912, and the first pilot fuel supply system 922, respectively.

[0136] The fourth RDC 946 includes a fourth detonation chamber 948, a fourth outer channel 950, and a fourth pilot fuel supply system 952. The fourth RDC 946 has a fourth cross-sectional area A4. The fourth RDC 946 includes a fourth detonation chamber 948, a fourth outer channel 950, and a fourth pilot fuel supply system 952 that are similar to the first detonation chamber 920, the first outer channel 912, and the first pilot fuel supply system 922, respectively.

[0137] In the burner system 900, the cross-sectional area of the series of RDCs increases from the upstream end to the downstream end of the burner system 900 (e.g., A1 < A2 < A3 < A4). That is, the first cross-sectional area A1 of the first RDC 906 is less than the second cross-sectional area A2 of the second RDC 908, the second cross-sectional area A2 of the second RDC 908 is less than the third cross-sectional area A3 of the third RDC 910, and the third cross-sectional area A3 of the third RDC 910 is less than the fourth cross-sectional area A4 of the fourth RDC 946.

[0138] Fig.10 A tenth embodiment of a burner system 1000 including a series of RDCs is shown. In particular, the burner system 1000 includes an expanding series of RDCs having a central body 1040. The cross-sectional dimensions of at least a portion of the central body 1040 increase from upstream to downstream. Elements of the tenth embodiment that are similar to elements in the ninth embodiment have been given similar reference numerals in the 1000 series and only the general differences will be discussed. For example, the first RDC 906 described in the ninth embodiment is numbered the first RDC 1006 in the tenth embodiment. One difference between the ninth and tenth embodiments is that the burner system 1000 in the tenth embodiment has a central body 1040.

[0139] The burner system 1000 includes a first wall 1004 spaced from a second wall 1005 by a space 1007. The first wall 1004 defines a core 1002 that receives a core oxidizer fuel mixture 1001. The core 1002 includes a first detonation chamber 1020, a second detonation chamber 1024, a third detonation chamber 1030, and a fourth detonation chamber 1048 arranged in series. The first wall 1004 is the inner wall of the burner system 1000. The second wall 1005 is the outer wall and may extend around the periphery of the burner system 1000.

[0140] The first wall 1004 of the burner system 1000 includes a first outer channel 1012, a second outer channel 1026, a third outer channel 1032, and a fourth outer channel 1050. The first outer channel 1012 of the first wall 1004 is coupled to a first pilot oxidant-fuel supply 1023 through a first pilot fuel supply system 1022. The first pilot oxidant-fuel supply 1023 can be coupled to the first outer channel 1012 in any suitable manner (e.g., through one or more openings in the first wall 1004). The second outer channel 1026 of the first wall 1004 is coupled to a second pilot oxidant-fuel supply 1029 through a second pilot fuel supply system 1028. The second pilot oxidant-fuel supply 1029 can be coupled to the second outer channel 1026 in any suitable manner (e.g., through one or more openings defined in the first wall 1004). A third outer channel 1032 in the first wall 1004 is coupled to a third pilot oxidant-fuel supply 1035 through a third pilot fuel supply system 1034. The third pilot oxidant-fuel supply 1035 can be coupled to the third outer channel 1032 in any suitable manner, such as through one or more openings in the first wall 1004. A fourth outer channel 1050 in the first wall 1004 is coupled to a fourth pilot oxidant-fuel supply 1053 through a fourth pilot fuel supply system 1052. The fourth pilot oxidant-fuel supply 1053 can be coupled to the fourth outer channel 1050 in any suitable manner, such as through one or more openings in the first wall 1004.

[0141] In some methods, the first pilot oxidant-fuel supply 1023, the second pilot oxidant-fuel supply 1029, the third pilot oxidant-fuel supply 1035, and the fourth pilot oxidant-fuel supply 1053 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1007.

[0142] The combustor system 1000 includes a first RDC 1006 , a second RDC 1008 , a third RDC 1010 , and a fourth RDC 1046 in the core 1002 .

[0143] The first RDC 1006 includes a first detonation chamber 1020, a first outer channel 1012, and a first pilot fuel supply system 1022. The first detonation chamber 1020 is at least partially surrounded by the first outer channel 1012. The first pilot fuel supply system 1022 delivers a first pilot oxidant-fuel supply 1023 to the first outer channel 1012.

[0144] The second RDC 1008 includes a second detonation chamber 1024, a second outer channel 1026, and a second pilot fuel supply system 1028. The second detonation chamber 1124 is at least partially surrounded by the second outer channel 1026. The second pilot fuel supply system 1028 delivers a second pilot oxidant-fuel supply 1029 to the second outer channel 1026.

[0145] The third RDC 1010 includes a third detonation chamber 1030, a third outer channel 1032, and a third pilot fuel supply system 1034. The third detonation chamber 1130 is at least partially surrounded by the third outer channel 1032. The third pilot fuel supply system 1034 delivers a third pilot oxidant-fuel supply 1035 to the third outer channel 1032.

[0146] The fourth RDC 1046 includes a fourth detonation chamber 1048, a fourth outer channel 1050, and a fourth pilot fuel supply system 1052. The fourth detonation chamber 1048 is at least partially surrounded by the fourth outer channel 1050. The fourth pilot fuel supply system 1052 delivers a fourth pilot oxidant-fuel supply 1053 to the fourth outer channel 1050.

[0147] The center body 1040 of the burner system 1000 extends axially through the core 1002 from the upstream portion to the downstream portion of the burner system 1000. The center body 1040 has a first portion 1041A and a second portion 1041B. The first portion 1041A is upstream of the second portion 1041B. The first portion 1041A has a constant or approximately constant cross-sectional area CB1, and therefore, the shape of the first portion 1041A is generally cylindrical ( Fig.10 The second portion 1041B of the center body 1040 has an increased cross-sectional area CB2, and the second portion 1041B is generally conical ( Fig.10 1041B has a tapered shape that increases from the upstream portion of the burner system 1000 to the downstream portion of the burner system 1000. Due to the presence of the center body 1040, the first detonation chamber 1020, the second detonation chamber 1024, and the third detonation chamber 1030 are annular. In addition, the tapered shape of the center body 1040 causes the first detonation chamber 1020, the second detonation chamber 1024, the third detonation chamber 1030, and the fourth detonation chamber 1048 to be approximately the same size (e.g., having approximately the same cross-sectional area, the same volume, etc.).

[0148] In some embodiments, the center body 1040 can be translatable and can move through at least a portion of the core 1002. For example, the center body 1040 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0149] Fig.11 An eleventh embodiment of a burner system 1100 including a tandem RDC is shown. The burner system 1100 includes an expanded tandem RDC having a combination of centerbody-less, pilot flow, and full flow RDCs. Elements of the eleventh embodiment similar to elements in the ninth embodiment have been given similar reference numbers in the 1100 series, and only general differences will be discussed. For example, the first RDC 906 described in the ninth embodiment is numbered as the first RDC 1106 in the eleventh embodiment. One difference between the ninth and eleventh embodiments is that the burner system 1100 has a centerbody 1140 disposed in a portion of the burner system 1100.

[0150] The burner system 1100 includes a first wall 1104 separated from a second wall 1105 by a space 1107. The first wall 1104 defines a core 1102 that receives a core oxidant-fuel mixture 1101. The core 1102 includes a first detonation chamber 1120, a second detonation chamber 1124, a third detonation chamber 1130, and a fourth detonation chamber 1148 arranged in series. The first wall 1104 is an inner wall of the burner system 1100. The second wall 1105 is an outer wall and can extend around the periphery of the burner system 1100.

[0151] The first wall 1104 of the burner system 1100 includes a first outer channel 1112, a second outer channel 1126, a third outer channel 1132, and a fourth outer channel 1150. The first outer channel 1112 of the first wall 1104 is coupled to a first pilot oxidant-fuel supply 1123 through a first pilot fuel supply system 1122. The first pilot oxidant-fuel supply 1123 can be coupled to the first outer channel 1112 in any suitable manner (e.g., through one or more openings in the first wall 1104). The second outer channel 1126 of the first wall 1104 is coupled to a second pilot oxidant-fuel supply 1129 through a second pilot fuel supply system 1128. The second pilot oxidant-fuel supply 1129 can be coupled to the second outer channel 1126 in any suitable manner (e.g., through one or more openings defined in the first wall 1104). A third outer channel 1132 in the first wall 1104 is coupled to a third pilot oxidant-fuel supply 1135 via a third pilot fuel supply system 1134. The third pilot oxidant-fuel supply 1135 can be coupled to the third outer channel 1132 in any suitable manner, such as through one or more openings in the first wall 1104. A fourth outer channel 1150 in the first wall 1104 is coupled to a fourth pilot oxidant-fuel supply 1153 via a fourth pilot fuel supply system 1152. The fourth pilot oxidant-fuel supply 1153 can be coupled to the fourth outer channel 1150 in any suitable manner, such as through one or more openings in the first wall 1104.

[0152] In some methods, the first pilot oxidant-fuel supply 1123, the second pilot oxidant-fuel supply 1129, the third pilot oxidant-fuel supply 1135, and the fourth pilot oxidant-fuel supply 1153 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1107.

[0153] The burner system 1100 includes a first RDC 1106 , a second RDC 1108 , a third RDC 1110 , and a fourth RDC 1146 .

[0154] The first RDC 1106 includes a first detonation chamber 1120, a first outer channel 1112, and a first pilot fuel supply system 1122. The first detonation chamber 1120 is at least partially surrounded by the first outer channel 1112. The first pilot fuel supply system 1122 delivers a first pilot oxidant-fuel supply 1123 to the first outer channel 1112.

[0155] The second RDC 1108 includes a second detonation chamber 1124, a second outer channel 1126, and a second pilot fuel supply system 1128. The second detonation chamber 1124 is at least partially surrounded by the second outer channel 1126. The second pilot fuel supply system 1128 delivers a second pilot oxidant-fuel supply 1129 to the second outer channel 1126.

[0156] The third RDC 1110 includes a third detonation chamber 1130, a third outer channel 1132, and a third pilot fuel supply system 1134. The third detonation chamber 1130 is at least partially surrounded by the third outer channel 1132. The third pilot fuel supply system 1134 delivers a third pilot oxidant-fuel supply 1135 to the third outer channel 1132.

[0157] The fourth RDC 1146 includes a fourth detonation chamber 1148, a fourth outer channel 1150, and a fourth pilot fuel supply system 1152. The fourth detonation chamber 1148 is at least partially surrounded by the fourth outer channel 1150. The fourth pilot fuel supply system 1152 delivers a fourth pilot oxidant-fuel supply 1153 to the fourth outer channel 1150.

[0158] The center body 1140 of the combustor system 1100 extends axially through the core 1102, extending from an upstream portion to a downstream portion of the combustor system 1100. The center body 1140 begins after the first RDC 1106 and extends through the second RDC 1108, the third RDC 1110, and the fourth RDC 1146. Due to the positioning of the center body 1140, the first detonation chamber 1120 of the first RDC 1106 is cylindrical and generally unobstructed. In contrast, the second detonation chamber 1124 of the second RDC 1108, the third detonation chamber 1130 of the third RDC 1110, and the fourth detonation chamber 1148 of the fourth RDC 1146 are annular in shape.

[0159] The center body 1140 has a tapered shape with a size increasing from the upstream portion to the downstream portion of the center body 1140. The center body 1140 is generally conical ( Fig.11 11). The center body 1140 has a cross-sectional area CB1 that increases from an upstream portion to a downstream portion of the combustor system 1100.

[0160] In some embodiments, the center body 1140 can be translatable and can move through at least a portion of the core 1102. For example, the center body 1140 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0161] Now go to Figure 12-14 , various burner systems including multiple RDCs connected in series are shown. Figure 12-14 In an embodiment of the invention, the RDC includes an inner channel of an inner pilot for initiating a rotating detonation reaction and an inner pilot oxidant-fuel supply. The inner channel is formed in the center body of the combustor system, so that the rotating detonation wave initiated in the inner channel can travel radially outward. In this way, the rotating detonation reaction initiated in the inner channel can support the combustion reaction in the ring surrounding the center body of the system.

[0162] Fig.12 A twelfth embodiment of a burner system 1200 including a tandem RDC is shown. The burner system 1200 includes a tandem RDC having the same or similar cross-sectional area and having a center body injection of a pilot fuel. Elements of the twelfth embodiment similar to elements in the first embodiment have been given similar reference numbers in the 1200 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 1206 in the twelfth embodiment. The burner system 1200 is similar to the burner system 100, except that the burner system 1200 lacks a second wall and includes a center body 1240. The pilot fuel is injected into the RDC via the center body 1240, rather than along the first wall 1204. In addition, the tandem RDC in the burner system 1200 includes an inner channel formed in an outer surface 1244 of the center body 1240, rather than an outer channel formed in the first wall 1204.

[0163] A first wall 1204 of the burner system 1200 defines a core 1202. The first wall 1204 may extend around the periphery of the burner system 1200. The first wall 1204 defines the core 1202 that receives the core oxidant fuel mixture 1201. The core 1202 includes a first detonation chamber 1220, a second detonation chamber 1224, and a third detonation chamber 1230 arranged in series. A center body 1240 is disposed in the core 1202, extending axially along a centerline X. The center body 1240 is at least partially defined by an outer surface 1244. The outer surface 1244 is spaced apart from the first wall 1204. A cavity 1242 or opening extends through the center body 1240.

[0164] The exterior surface 1244 of the center body 1240 includes a first inner channel 1212, a second inner channel 1226, and a third inner channel 1232. The first inner channel 1212 of the center body 1240 is coupled to a first pilot oxidant-fuel supply 1223 through a first pilot fuel supply system 1222. The first pilot oxidant-fuel supply 1223 may be coupled to the first inner channel 1212 in any suitable manner (e.g., through one or more openings in the exterior surface 1244 of the center body 1240). The second inner channel 1226 of the center body 1240 is coupled to a second pilot oxidant-fuel supply 1229 through a second pilot fuel supply system 1228. The second pilot oxidant-fuel supply 1229 may be coupled to the second inner channel 1226 in any suitable manner (e.g., through one or more openings defined in the exterior surface 1244 of the center body 1240). The third inner channel 1232 in the center body 1240 is coupled to a third pilot oxidant-fuel supply 1235 through a third pilot fuel supply system 1234. The third pilot oxidant-fuel supply 1235 may be coupled to the third inner channel 1232 in any suitable manner, such as, for example, through one or more openings in an outer surface 1244 of the center body 1240.

[0165] In some approaches, the first pilot oxidant-fuel supply 1223, the second pilot oxidant-fuel supply 1229, and the third pilot oxidant-fuel supply 1235 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1207. For example, a pilot fuel or a pilot fuel-oxidant mixture can be injected into the cavity 1242 of the center body 1240 to provide the pilot fuel for the RDC.

[0166] The burner system 1200 also includes a first RDC 1206 , a second RDC 1208 , and a third RDC 1210 arranged in series.

[0167] The first RDC 1206 includes a first detonation chamber 1220, a first inner channel 1212, and a first pilot fuel supply system 1222. The first RDC 1206 has a first cross-sectional area A1. Due to the presence of the center body 1240, the shape of the first detonation chamber 1220 is generally annular. The outer surface 1244 of the center body 1240 forms the inner wall of the first detonation chamber 1220, and the first wall 1204 forms the outer wall of the first detonation chamber 1220. The first detonation chamber 1220 is at least partially defined by the first inner channel 1212 formed in the outer surface 1244 of the center body 1240. Similar to the first outer channel 112, the first inner channel 1212 includes a rearward step 1214 and a forward step 1216, which are recessed in the outer surface 1244 of the center body 1240 and joined together by a recessed surface 1218. The recessed surface 1218 is, for example, recessed relative to adjacent portions of the exterior surface 1244. A first pilot fuel supply system 1222 is coupled to the first inner channel 1212. The first pilot fuel supply system 1222 receives a first pilot oxidant-fuel supply 1223 from the cavity 1242 of the center body 1240 and delivers the first pilot oxidant-fuel supply 1223 to the first inner channel 1212 to support one or more reactions occurring therein.

[0168] The second RDC 1208 includes a second detonation chamber 1224, a second inner channel 1226, and a second pilot fuel supply system 1228. The second RDC 1208 has a second cross-sectional area A2. The second detonation chamber 1224 is similar to the first detonation chamber 1220. The second inner channel 1226 and the second pilot fuel supply system 1228 are similar to the first inner channel 1212 and the first pilot fuel supply system 1222, respectively.

[0169] The third RDC 1210 includes a third detonation chamber 1230, a third inner channel 1232, and a third pilot fuel supply system 1234. The third RDC 1210 has a third cross-sectional area A3. The third detonation chamber 1230 is similar to the first detonation chamber 1220. The third inner channel 1232 and the third pilot fuel supply system 1234 are similar to the first inner channel 1212 and the first pilot fuel supply system 1222, respectively.

[0170] The cross-sectional areas of the first RDC 1206, the second RDC 1208, and the third RDC 1210 are approximately the same and generally do not vary from an upstream portion of the burner system 1200 to a downstream portion of the burner system 1200. That is, the first cross-sectional area A1, the second cross-sectional area A2, and the third cross-sectional area A3 are the same or approximately the same.

[0171] In operation, a rotating detonation reaction is initiated in one or more of the first RDC 1206, the second RDC 1208, and the third RDC 1210. The first inner channel 1212 and the first pilot fuel supply system 1222 are used as internal pilots for the rotating detonation reaction and the combustion reaction occurring in the first detonation chamber 1220. In the first RDC, the first pilot fuel supply system 1222 supplies the first inner channel 1212 with a pilot fuel or a pilot fuel-oxidant mixture. The first pilot fuel supply system 1222 receives the pilot fuel or the pilot fuel-oxidant mixture from the cavity 1242 of the center body 1240. An igniter (not shown) ignites the pilot fuel-oxidant mixture in the first inner channel 1212 to initiate a rotating detonation reaction. The rotating detonation reaction generates a rotating detonation wave. The first inner channel 1212 can anchor the rotating detonation wave so that the wave propagates circumferentially around the center body 1240 in the first detonation chamber 1220. Additionally, the first inner channel 1212 can help direct the rotating detonation wave axially through the first detonation chamber 1220 away from the center body 1240 so that the reaction can consume the core oxidant-fuel mixture present in the core of the first detonation chamber 1220 and adjacent to the first wall 1204. Similar reactions occur in one or more of the second RDC 1208 and the third RDC 1210.

[0172] Fig.13 A thirteenth embodiment of a burner system 1300 including a plurality of series RDCs is shown. The burner system 1300 includes a series RDC with an increased cross-sectional area and a center body injection of a pilot flow. Elements of the thirteenth embodiment similar to those in the twelfth embodiment have been given similar reference numbers in the 1300 series, and only general differences will be discussed. For example, the first RDC 1206 described in the twelfth embodiment is numbered as the first RDC 1306 in the thirteenth embodiment. The burner system 1300 is similar to the burner system 1200, except that the burner system 1300 has a center body 1340. The center body 1340 has a first cross-sectional area CB1 that is greater than a second cross-sectional area CB2. The cross-sectional area CB1 is the cross-sectional area of ​​the upstream portion of the burner system 1300, while the cross-sectional area CB2 is the cross-sectional area of ​​the downstream portion of the burner system 1300. The cross-sectional area of ​​the center body 1340 need not decrease linearly. A cavity 1342 or opening extends through the center body 1340.

[0173] The burner system 1300 is defined by a first wall 1304 surrounding a core 1302. The core 1302 receives a core oxidant fuel mixture 1301. The core 1302 includes a first detonation chamber 1320, a second detonation chamber 1324, and a third detonation chamber 1330 arranged in series. A center body 1340 has an outer surface 1344. The center body 1340 is disposed in the core 1302.

[0174] The exterior surface 1344 of the center body 1340 includes a first inner channel 1312, a second inner channel 1326, and a third inner channel 1332. The first inner channel 1312 of the center body 1340 is coupled to a first pilot oxidant-fuel supply 1323 through a first pilot fuel supply system 1322. The first pilot oxidant-fuel supply 1323 may be coupled to the first inner channel 1312 in any suitable manner (e.g., through one or more openings in the exterior surface 1344 of the center body 1340). The second inner channel 1326 of the center body 1340 is coupled to a second pilot oxidant-fuel supply 1329 through a second pilot fuel supply system 1328. The second pilot oxidant-fuel supply 1329 may be coupled to the second inner channel 1326 in any suitable manner (e.g., through one or more openings defined in the exterior surface 1344 of the center body 1340). The third inner channel 1332 in the center body 1340 is coupled to a third pilot oxidant-fuel supply 1335 through a third pilot fuel supply system 1334. The third pilot oxidant-fuel supply 1335 may be coupled to the third inner channel 1332 in any suitable manner, such as, for example, through one or more openings in an outer surface 1344 of the center body 1340.

[0175] In some approaches, the first pilot oxidant-fuel supply 1323, the second pilot oxidant-fuel supply 1329, and the third pilot oxidant-fuel supply 1335 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 1307. For example, a pilot fuel or a pilot fuel-oxidant mixture may be injected into the cavity 1342 of the center body 1340 to provide the pilot fuel for the RDC.

[0176] The combustor system 1300 includes a first RDC 1306 , a second RDC 1308 , and a third RDC 1310 arranged in series in the core 1302 .

[0177] The first RDC 1306 includes a first detonation chamber 1320, a first inner channel 1312, and a first pilot fuel supply system 1322. The first RDC 1306 has a first cross-sectional area A1. The interior of the first detonation chamber 1320 is at least partially defined by the first inner channel 1312, and the exterior is defined by the first wall 1304. The first pilot fuel supply system 1322 delivers a first pilot oxidant-fuel supply 1323 to the first inner channel 1312.

[0178] The second RDC 1308 includes a second detonation chamber 1324, a second inner channel 1326, and a second pilot fuel supply system 1328. The second detonation chamber 1324 has a second cross-sectional area A2. The inner portion of the second detonation chamber 1324 is at least partially defined by the second inner channel 1326, and the outer portion is defined by the first wall 1304. The second pilot fuel supply system 1328 delivers a second pilot oxidant-fuel supply 1329 to the second inner channel 1326.

[0179] The third RDC 1310 includes a third detonation chamber 1330, a third inner channel 1332, and a third pilot fuel supply system 1334. The third detonation chamber 1330 has a third cross-sectional area A3. The inner portion of the third detonation chamber 1330 is at least partially defined by the third inner channel 1332, and the outer portion is defined by the first wall 1304. The third pilot fuel supply system 1334 delivers a third pilot oxidant-fuel supply 1335 to the third inner channel 1332.

[0180] In the combustor system 1300, the volume of the detonation chamber of the series RDC increases from upstream to downstream due to the decrease in the cross-sectional area of ​​the center body 1340. The first cross-sectional area A1 of the first detonation chamber 1320 is smaller than the second cross-sectional area A2 of the second detonation chamber 1324, and similarly, the second cross-sectional area A2 of the second detonation chamber 1324 is smaller than the third cross-sectional area A3 of the third detonation chamber 1330 (e.g., A1<A2<A3). Therefore, the volume of the first detonation chamber 1320 is smaller than that of the second detonation chamber 1324. Similarly, the volume of the second detonation chamber 1324 is smaller than that of the third detonation chamber 1330.

[0181] Fig.14 A fourteenth embodiment of a burner system 1400 including a tandem RDC is shown. The burner system 1400 includes a contracting tandem RDC with a center body injection of pilot fuel. Elements of the fourteenth embodiment similar to those in the first embodiment have been given similar reference numbers in the 1400 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 1406 in the fourteenth embodiment. The burner system 1400 is similar to the burner system 100, except that the burner system 1400 includes a center body 1440, and the pilot fuel is injected into the RDC via the center body 1440. A cavity 1442 or opening extends through the center body 1440. In addition, the tandem RDC in the burner system 1400 includes an inner channel formed in an outer surface 1444 of the center body 1440, rather than an outer channel formed in the first wall 1404. In addition, the first wall 1404 defining the core 1402 of the burner system 1400 has an inclined or tapered portion, resulting in a contracted size of the RDC.

[0182] The burner system 1400 is defined by a first wall 1404 surrounding a core 1402. At least a portion of the first wall 1404 has a tapered thickness that decreases from upstream to downstream. The core 1402 receives a core oxidant fuel mixture 1401. The core 1402 includes a first detonation chamber 1420, a second detonation chamber 1424, and a third detonation chamber 1430 arranged in series. The center body 1440 has an outer surface 1444.

[0183] A center body 1440 is disposed within the core 1402. The center body 1440 has an exterior surface 1444.

[0184] The exterior surface 1444 of the center body 1440 includes a first inner channel 1412, a second inner channel 1426, and a third inner channel 1432. The first inner channel 1412 of the center body 1440 is coupled to a first pilot oxidant-fuel supply 1423 through a first pilot fuel supply system 1422. The first pilot oxidant-fuel supply 1423 may be coupled to the first inner channel 1412 in any suitable manner (e.g., through one or more openings in the exterior surface 1444 of the center body 1440). The second inner channel 1426 of the center body 1440 is coupled to a second pilot oxidant-fuel supply 1429 through a second pilot fuel supply system 1428. The second pilot oxidant-fuel supply 1429 may be coupled to the second inner channel 1426 in any suitable manner (e.g., through one or more openings defined in the exterior surface 1444 of the center body 1440). The third inner channel 1432 in the center body 1440 is coupled to a third pilot oxidant-fuel supply 1435 through a third pilot fuel supply system 1434. The third pilot oxidant-fuel supply 1435 may be coupled to the third inner channel 1432 in any suitable manner, such as, for example, through one or more openings in an outer surface 1444 of the center body 1440.

[0185] In some approaches, the first pilot oxidant-fuel supply 1423, the second pilot oxidant-fuel supply 1429, and the third pilot oxidant-fuel supply 1435 may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the space 1407. For example, a pilot fuel or a pilot fuel-oxidant mixture may be injected into the cavity 1442 of the center body 1440 to provide the pilot fuel for the RDC.

[0186] The burner system 1400 includes a first RDC 1406 , a second RDC 1408 , and a third RDC 1410 arranged in series.

[0187] A center body 1440 of the burner system 1400 extends through the core 1402 of the burner system 1400. The center body 1440 extends through the first RDC 1406 and the second RDC 1408. The burner system 1400. The center body 1440 is stepped in such a manner that a stabilizing structure (e.g., the first inner channel 1412 and the second inner channel 1426) is defined therein. The stepped arrangement of the center body 1440 forms the first inner channel 1412 and the second inner channel 1426 that lack a forward facing step and instead include only a rearward facing step and a recessed portion.

[0188] The first RDC 1406 includes a first detonation chamber 1420, a first inner channel 1412, and a first pilot fuel supply system 1422. The first RDC 1406 has a first cross-sectional area A1. The first detonation chamber 1420 is partially defined by the first inner channel 1412 and the first wall 1404. Because the center body 1440 extends through the first RDC 1406, the first detonation chamber 1420 is annular. The first inner channel 1412 includes a rearward step 1414 and a recessed portion 1418. The recessed portion 1418 is recessed relative to an adjacent portion of the center body 1440. The first pilot fuel supply system 1422 is connected to the first inner channel 1412. The first pilot fuel supply system 1422 delivers a first pilot oxidant-fuel supply 1423 to one or more of the first inner channel 1412 and the first detonation chamber 1420. The first pilot fuel supply system is supplied by the center body 1440.

[0189] The second RDC 1408 includes a second detonation chamber 1424, a second inner channel 1426, and a second pilot fuel supply system 1428. The second RDC 1408 has a second cross-sectional area A2. The second detonation chamber 1424, the second inner channel 1426, and the second pilot fuel supply system 1428 are similar to the first detonation chamber 1420, the first inner channel 1412, and the first pilot fuel supply system 1422, respectively.

[0190] The third RDC 1410 includes a third detonation chamber 1430, a third inner channel 1432, and a third pilot fuel supply system 1434. The third RDC 1410 has a third cross-sectional area A3. Because the center body 1440 terminates upstream of the third RDC 1410, the third detonation chamber 1430 is center body-less, and there is no obstruction from the center line X of the core 1402 to the first wall 1404. The third pilot fuel supply system 1434 delivers pilot fuel along the center line X at the core of the third detonation chamber 1430.

[0191] Due to the reduced tapered shape of the first wall 1404 , the third cross-sectional area A3 of the third RDC 1410 is smaller than the second cross-sectional area A2 of the second RDC 1408 , and similarly, the second cross-sectional area A2 of the second RDC 1408 is smaller than the first cross-sectional area A1 of the first RDC 1406 (eg, A3 < A2 < A1 ).

[0192] In some embodiments, the center body 1440 can be translatable and can move through at least a portion of the core 1402. For example, the center body 1440 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0193] Now go to Figure 15-20 , various burner systems including multiple RDCs arranged in series are shown. Figure 15-20 In an embodiment of the present invention, the RDC includes an inner channel coupled to an inner pilot oxidant-fuel supply and an outer channel coupled to an outer pilot oxidant-fuel supply. Rotating detonation reactions may be initiated in the inner channel and the outer channel.

[0194] Fig.15A fifteenth embodiment of a burner system 1500 including a tandem RDC is shown. The burner system 1500 includes an expansion-contraction tandem RDC having an inner pilot and an outer pilot. Elements of the fifteenth embodiment similar to those in the first embodiment have been given similar reference numbers in the 1500 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 1506 in the fifteenth embodiment. One difference between the first and fifteenth embodiments is that the burner system 1500 has a first wall 1504 that is stepped and defines a detonation chamber that increases in size from an upstream portion of the burner system 1500 to a downstream portion of the burner system 1500. A further difference is that the burner system 1500 includes a center body 1540, and the pilot fuel is injected into the RDC via the center body 1540. Furthermore, in addition to the outer channels formed in the first wall 1504 of the burner system 1500, the tandem RDC in the burner system 1500 also includes inner channels formed in the outer surface 1544 of the center body 1540. Another difference is the shape of the channels. The stepped arrangement of the first wall 1504 forms the first outer channel 1512B, the second outer channel 1526B, and the third outer channel 1532B that lack the forward facing step and include only the rearward facing step and the recessed portion. Similarly, the stepped arrangement of the center body 1540 forms the inner channels 1512A, 1526A that include only the rearward facing step and the recessed portion. Although the removal of the rearward facing step may potentially reduce the effectiveness of the detonation wave penetrating toward the center, in certain applications, this may be the preferred approach, for example, in applications where the detonation wave may travel upstream.

[0195] The burner system 1500 includes a first wall 1504 separated from a second wall 1505 by a space 1507. The first wall 1504 defines a core 1502. The core 1502 receives a core oxidant fuel mixture 1501. The core 1502 includes a first detonation chamber 1520, a second detonation chamber 1524, and a third detonation chamber 1530 arranged in series. The first wall 1504 is an inner wall of the burner system 1500. The second wall 1505 is an outer wall and can extend around the periphery of the burner system 1500.

[0196] The first wall 1504 of the burner system 1500 includes a first outer channel 1512B, a second outer channel 1526B, and a third outer channel 1532B. The first outer channel 1512B of the first wall 1504 is coupled to a first outer pilot oxidant-fuel supply 1523B through a first outer pilot fuel supply system 1522B. The first outer pilot oxidant-fuel supply 1523B can be coupled to the first outer channel 1512B in any suitable manner (e.g., through one or more openings in the first wall 1504). The second outer channel 1526B of the first wall 1504 is coupled to a second outer pilot oxidant-fuel supply 1529B through a second outer pilot fuel supply system 1528B. The second outer pilot oxidant-fuel supply 1529B can be coupled to the second outer channel 1526B in any suitable manner (e.g., through one or more openings defined in the first wall 1504). The third outer channel 1532B in the first wall 1504 is coupled to a third outer pilot oxidant-fuel supply 1535B through a third outer pilot fuel supply system 1534B. The third outer pilot oxidant-fuel supply 1535B may be coupled to the third outer channel 1532B in any suitable manner (e.g., through one or more openings in the first wall 1504).

[0197] In some approaches, the first external pilot oxidant-fuel supply 1523 , the second external pilot oxidant-fuel supply 1529 , and the third external pilot oxidant-fuel supply 1535 can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1507 .

[0198] The core 1502 of the burner system 1500 includes a center body 1540. The center body 1540 has an exterior surface 1544. The exterior surface 1544 of the center body 1540 includes a first inner channel 1512A and a second inner channel 1526A. The first inner channel 1512A of the center body 1540 is coupled to a first inner pilot oxidant-fuel supply 1523A through a first inner pilot fuel supply system 1522A. The first inner pilot oxidant-fuel supply 1523A can be coupled to the first inner channel 1512A in any suitable manner (e.g., through one or more openings in the exterior surface 1544 of the center body 1540). The second inner channel 1526A of the center body 1540 is coupled to a second inner pilot oxidant-fuel supply 1529A through a second inner pilot fuel supply system 1528A. The second inner pilot oxidant-fuel supply 1529A may be coupled to the second inner channel 1526A in any suitable manner (eg, via one or more openings defined in an outer surface 1544 of the center body 1540).

[0199] In some approaches, the first inner pilot oxidant-fuel supply 1523A, the second inner pilot oxidant-fuel supply 1529A, and the third inner pilot oxidant-fuel supply 1535A may be the same supply, and may be a mixture of fuel and oxidant present in the center body 1540, for example.

[0200] The center body 1540 has a cross-sectional area that decreases or contracts in size from upstream to downstream. In particular, the outer surface 1544 is stepped to define a plurality of stable structures therein (e.g., the first inner channel 1512A, the second inner channel 1526A). The first wall 1504 of the burner system 1500 is also stepped to define a plurality of stable structures therein (e.g., the first outer channel 1512B, the second outer channel 1526B, and the third outer channel 1532B). The first inner channel 1512A and the first outer channel 1512B are radially aligned (i.e., positioned along a common radius extending from the centerline X to the first wall 1504). The first inner channel 1512A is opposite to the first outer channel 1512B. That is, the first inner channel 1512A and the first outer channel 1512B are disposed at the same position along the length of the burner system 1500.

[0201] The burner system 1500 also includes a first RDC 1506, a second RDC 1508, and a third RDC 1510. The burner system 1500 has a core 1502 defined by a first wall 1504.

[0202] The first RDC 1506 includes a first detonation chamber 1520, a first inner channel 1512A, a first inner pilot fuel supply system 1522A, a first outer channel 1512B, and a first outer pilot fuel supply system 1522B. The first detonation chamber 1520 of the first RDC 1506 is at least partially defined by the first inner channel 1512A and the first outer channel 1512B. The first detonation chamber 1520 has a first width A1. The first inner channel 1512A includes a rearward step 1514A and a recessed portion 1518A. The recessed portion 1518A is recessed relative to an adjacent portion of the center body 1540. The first inner pilot fuel supply system 1522A is coupled to the first inner channel 1512A to deliver the pilot fuel from the center body to the first inner channel 1512A. First inner pilot fuel supply system 1522A is in fluid communication with a cavity within center body 1540 and first inner channel 1512A. First outer channel 1512B similarly includes a rearwardly facing step 1514B and a recessed portion 1518B. First outer pilot fuel supply system 1522B is coupled to first outer channel 1512B to deliver pilot fuel to first outer channel 1512B.

[0203] The second RDC 1508 includes a second detonation chamber 1524, a second inner channel 1526A, a second inner pilot fuel supply system 1528A, a second outer channel 1526B, and a second outer pilot fuel supply system 1528B. The second detonation chamber 1524, the second inner channel 1526A, the second outer channel 1526B, the second inner pilot fuel supply system 1528A and the second outer pilot fuel supply system 1528B are similar to the first detonation chamber 1520, the first inner channel 1512A, the first outer channel 1512B, and the first inner pilot fuel supply system 1522A, respectively. The second detonation chamber 1524 has a second width A2.

[0204] The third RDC 1510 includes a third detonation chamber 1530, a third inner pilot fuel supply system 1534A, a third outer channel 1532B, and a third outer pilot fuel supply system 1534B. The third detonation chamber 1530, the third outer channel 1532B, and the third outer pilot fuel supply system 1534B are similar to the first detonation chamber 1520, the first outer channel 1512B, and the first outer pilot fuel supply system 1522B, respectively. The third detonation chamber 1530 has a third width A3. Because the center body 1540 terminates upstream of the third RDC 1510, the third detonation chamber 1530 is center body-less and lacks an inner channel for guiding the reaction in the third detonation chamber 1530. Instead, the third inner pilot fuel supply system 1534A is disposed at the center of the center body 1540. The third inner pilot fuel supply system 1534 injects the pilot fuel into the center of the third detonation chamber 1530.

[0205] The center body 1540 extends through the first RDC 1506 and the second RDC 1508 and terminates upstream of the third RDC 1510. Due to the positioning of the center body 1540, the first detonation chamber 1520 of the first RDC 1506 and the second detonation chamber 1524 of the second RDC 1508 are annular. However, because the center body 1540 terminates upstream of the third RDC 1510, the third detonation chamber 1530 is center body-less.

[0206] Due to the relatively stepped configurations of the exterior surface 1544 of the center body 1540 and the first wall 1504, the first cross-sectional area A1 is smaller than the second cross-sectional area A2, and the second cross-sectional area A2 is smaller than the third cross-sectional area A3 (eg, A1 <A2<A3)。

[0207] In some embodiments, center body 1540 can be translatable and can move through at least a portion of core 1502. For example, center body 1540 can be mechanically or fluidically translated along centerline X in one or more of an upstream direction and a downstream direction.

[0208] Fig.16 A second embodiment of a burner system 1600 including a tandem RDC is shown. The burner system 1600 includes a tandem RDC having an expansion-contraction tandem RDC with staggered inner and outer pilots. Elements of the sixteenth embodiment similar to those of the fifteenth embodiment have been given similar reference numbers in the 1600 series, and only general differences will be discussed. For example, the first RDC 1506 described in the first embodiment is numbered as the first RDC 1606 in the sixteenth embodiment. The burner system 1600 is similar to the burner system 1500, except that the inner channels 1626A, 1632A formed in the outer surface 1644 of the center body 1640 are staggered with the outer channels 1612B, 1626B, 1632B formed in the first wall 1604. That is, the steps in the center body 1640 and the steps in the first wall 1604 are staggered or offset by one step or a portion thereof.

[0209] The burner system 1600 includes a first wall 1604 separated from a second wall 1605 by a space 1607. The first wall 1604 defines a core 1602. The core 1602 receives a core oxidant fuel mixture 1601. The core 1602 includes a first detonation chamber 1620, a second detonation chamber 1624, and a third detonation chamber 1630 arranged in series. The first wall 1604 is an inner wall of the burner system 1600. The second wall 1605 is an outer wall and can extend around the periphery of the burner system 1600.

[0210] The first wall 1604 of the burner system 1600 includes a first outer channel 1612B, a second outer channel 1626B, and a third outer channel 1632B. The first outer channel 1612B of the first wall 1604 is coupled to a first outer pilot oxidant-fuel supply 1623B through a first outer pilot fuel supply system 1622B. The first outer pilot oxidant-fuel supply 1623B can be coupled to the first outer channel 1612B in any suitable manner (e.g., through one or more openings in the first wall 1604). The second outer channel 1626B of the first wall 1604 is coupled to a second outer pilot oxidant-fuel supply 1629B through a second outer pilot fuel supply system 1628B. The second outer pilot oxidant-fuel supply 1629B can be coupled to the second outer channel 1626B in any suitable manner (e.g., through one or more openings defined in the first wall 1604). The third outer channel 1632B in the first wall 1604 is coupled to a third outer pilot oxidant-fuel supply 1635B through a third outer pilot fuel supply system 1634B. The third outer pilot oxidant-fuel supply 1635B may be coupled to the third outer channel 1632B in any suitable manner (e.g., through one or more openings in the first wall 1604).

[0211] In some approaches, the first external pilot oxidant-fuel supply 1623B, the second external pilot oxidant-fuel supply 1629B, and the third external pilot oxidant-fuel supply 1635B can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1607.

[0212] The core 1602 of the burner system 1600 includes a center body 1640. The center body 1640 has an exterior surface 1644. The exterior surface 1644 of the center body 1640 includes a first inner channel 1612A and a second inner channel 1626A. The first inner channel 1612A of the center body 1640 is coupled to a first inner pilot oxidant-fuel supply 1623A through a first inner pilot fuel supply system 1622A. The first inner pilot oxidant-fuel supply 1623A can be coupled to the first inner channel 1612A in any suitable manner (e.g., through one or more openings in the exterior surface 1644 of the center body 1640). The second inner channel 1626A of the center body 1640 is coupled to a second inner pilot oxidant-fuel supply 1629A through a second inner pilot fuel supply system 1628A. The second inner pilot oxidant-fuel supply 1629A may be coupled to the second inner channel 1626A in any suitable manner (eg, via one or more openings defined in an outer surface 1644 of the center body 1640).

[0213] In some approaches, the first inner pilot oxidant-fuel supply 1623A, the second inner pilot oxidant-fuel supply 1629A, and the third inner pilot oxidant-fuel supply 1635A may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the center body 1640 .

[0214] The first inner channels 1612A are staggered with the first outer channels 1612B along the length of the burner system 1600. The second inner channels 1626A are staggered with the second outer channels 1626B along the length of the burner system 1600. The third inner channels 1632A are staggered with the third outer channels 1632B along the length of the burner system 1600.

[0215] The burner system 1600 also includes a first RDC 1606 , a second RDC 1608 , and a third RDC.

[0216] The first RDC 1606 includes a first detonation chamber 1620, a first outer channel 1612B, and a first outer pilot fuel supply system 1622B. An outer portion of the first detonation chamber 1620 is at least partially defined by the first outer channel 1612B. The first outer pilot fuel supply system 1622B delivers pilot fuel to the first outer channel 1612B.

[0217] The second RDC 1608 includes a second detonation chamber 1624, a second inner channel 1626A, a second inner pilot fuel supply system 1628A, a second outer channel 1626B, and a second outer pilot fuel supply system 1628B. The second RDC 1608 includes a second detonation chamber 1624. The second detonation chamber 1624 is defined by the second inner channel 1626A on the inside and the second outer channel 1626B on the outside. The second inner pilot fuel supply system 1628A delivers pilot fuel to the second inner channel 1626A. The second outer pilot fuel supply system 1628B delivers pilot fuel to the second outer channel 1626B.

[0218] The third RDC 1610 includes a third detonation chamber 1630, a third inner channel 1632A, a third inner pilot fuel supply system 1634A, a third outer channel 1632B, and a third outer pilot fuel supply system 1634B. The third detonation chamber 1630 is defined by the inner third inner channel 1632A and the outer third outer channel 1632B. The third inner pilot fuel supply system 1634A delivers pilot fuel to the third inner channel 1632A. The third outer pilot fuel supply system 1634B delivers pilot fuel to the third outer channel 1632B.

[0219] Due to the staggered configuration of the steps in the center body 1640 and the steps in the first wall 1604, the first detonation chamber 1620 lacks an inner channel and is defined only by the first outer channel 1612B. However, the second RDC 1608 includes a second inner channel 1626A and a second outer channel 1626B. Similarly, the third RDC 1610 includes a third inner channel 1632A and a third outer channel 1632B.

[0220] In addition, the burner system 1600 includes a core pilot fuel supply system 1660A downstream of the third RDC 1610. Depending on the injection scheme, the third RDC 1610 can be operated as an independently stabilized RDC or can be stabilized by an upstream RDC. The core pilot fuel supply system 1660A is disposed adjacent to the centerline X of the burner system 1600. The core pilot fuel supply system 1660A is configured to deliver pilot fuel from the center body 1640 to the core of the burner system 1600 downstream of the tandem RDC. The core pilot fuel supply system 1660A can serve as a pilot for the combustion reaction occurring in the core of the volume of the burner system 1600.

[0221] In some embodiments, center body 1640 can be translatable and can move through at least a portion of core 1602. For example, center body 1640 can be mechanically or fluidically translated along centerline X in one or more of an upstream direction and a downstream direction.

[0222] Fig.17A seventeenth embodiment of a burner system 1700 including a tandem RDC is shown. The burner system 1700 includes a tandem RDC having the same or similar cross-sectional area and having an inner pilot and an outer pilot. Elements of the seventeenth embodiment similar to elements in the first embodiment have been given similar reference numbers in the 1700 series, and only general differences will be discussed. For example, the first RDC 106 described in the first embodiment is numbered as a first RDC 1706 in the seventeenth embodiment. The burner system 1700 is similar to the burner system 100, except that the burner system 1700 includes a center body 1740, and in addition to being injected along the first wall 1704, the pilot fuel is also injected into the RDC via the center body 1740. In addition, in addition to the outer channel formed in the first wall 1704, the tandem RDC in the burner system 1700 also includes an inner channel formed in the outer surface 1744 of the center body 1740.

[0223] The burner system 1700 includes a first wall 1704 separated from a second wall 1705 by a space 1707. The first wall 1704 defines a core 1702. The core 1702 receives a core oxidant fuel mixture 1701. The core 1702 includes a first detonation chamber 1720, a second detonation chamber 1724, and a third detonation chamber 1730 arranged in series. The first wall 1704 is an inner wall of the burner system 1700. The second wall 1705 is an outer wall and can extend around the periphery of the burner system 1700.

[0224] The first wall 1704 of the burner system 1700 includes a first outer channel 1712B, a second outer channel 1726B, and a third outer channel 1732B. The first outer channel 1712B of the first wall 1704 is coupled to a first outer pilot oxidant-fuel supply 1723B through a first outer pilot fuel supply system 1722B. The first outer pilot oxidant-fuel supply 1723B can be coupled to the first outer channel 1712B in any suitable manner (e.g., through one or more openings in the first wall 1704). The second outer channel 1726B of the first wall 1704 is coupled to a second outer pilot oxidant-fuel supply 1729B through a second outer pilot fuel supply system 1728B. The second outer pilot oxidant-fuel supply 1729B can be coupled to the second outer channel 1726B in any suitable manner (e.g., through one or more openings defined in the first wall 1704). The third outer channel 1732B in the first wall 1704 is coupled to a third outer pilot oxidant-fuel supply 1735B through a third outer pilot fuel supply system 1734B. The third outer pilot oxidant-fuel supply 1735B may be coupled to the third outer channel 1732B in any suitable manner (e.g., through one or more openings in the first wall 1704).

[0225] In some approaches, the first external pilot oxidant-fuel supply 1723B, the second external pilot oxidant-fuel supply 1729B, and the third external pilot oxidant-fuel supply 1735B can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 1707.

[0226] The core 1702 of the burner system 1700 includes a center body 1740. The center body 1740 has an exterior surface 1744. The exterior surface 1744 of the center body 1740 includes a first inner channel 1712A, a second inner channel 1726A, and a third inner channel 1732A. The first inner channel 1712A of the center body 1740 is coupled to a first inner pilot oxidant-fuel supply 1723A through a first inner pilot fuel supply system 1722A. The first inner pilot oxidant-fuel supply 1723A can be coupled to the first inner channel 1712A in any suitable manner (e.g., through one or more openings in the exterior surface 1744 of the center body 1740). The second inner channel 1726A of the center body 1740 is coupled to a second inner pilot oxidant-fuel supply 1729A through a second inner pilot fuel supply system 1728A. The second inner pilot oxidant-fuel supply 1729A may be coupled to the second inner channel 1726A in any suitable manner (eg, via one or more openings defined in an outer surface 1744 of the center body 1740).

[0227] In some approaches, the first inner pilot oxidant-fuel supply 1723A, the second inner pilot oxidant-fuel supply 1729A, and the third inner pilot oxidant-fuel supply 1735A may be the same supply, and may be a mixture of fuel and oxidant present in the center body 1740, for example.

[0228] The center body 1740 extends axially through the core 1702 along the centerline X. The center body 1740 is at least partially defined by an exterior surface 1744. A cavity 1742 or opening extends through the center body 1740. A pilot fuel or a pilot fuel-oxidant mixture can be injected into the cavity 1742 of the center body 1740 to provide the RDC with a pilot fuel. The burner system 1700 also includes a first RDC 1706, a second RDC 1708, and a third RDC 1710 arranged in series within the core 1702.

[0229] The first RDC 1706 includes a first detonation chamber 1720, a first inner channel 1712A, a first inner pilot fuel supply system 1722A, a first outer channel 1712B, and a first outer pilot fuel supply system 1722B. The shape of the first detonation chamber 1720 is generally annular due to the center body 1740. The outer surface 1744 of the center body 1740 forms the inner wall of the first detonation chamber 1720, and the first wall 1704 forms the outer wall of the first detonation chamber 1720. The first detonation chamber 1720 is at least partially defined by the first inner channel 1712A formed in the outer surface 1744 of the center body 1740. The first detonation chamber 1720 is also at least partially defined by the first outer channel 1712B formed in the first wall 1704. Similar to the first outer channel 112, the first outer channel 1712B includes a rearward-facing step and a forward-facing step recessed in the first wall 1704 of the burner system 1700. The first outer pilot fuel supply system 1722B delivers fuel or a fuel-oxidant mixture to the first outer channel 1712B. Similarly, the first inner channel 1712A includes a rearward-facing step and a forward-facing step recessed in the outer surface 1744 of the center body 1740 and joined together by the recessed surface 1718. The first inner pilot fuel supply system 1722A is coupled to the first inner channel 1712A. The first inner pilot fuel supply system 1722A receives a first inner pilot oxidant-fuel supply 1723A from the cavity 1742 of the center body 1740 and delivers the first inner pilot oxidant-fuel supply 1723A to the first inner channel 1712A to support one or more reactions occurring therein.

[0230] The second RDC 1708 includes a second detonation chamber 1724, a second inner channel 1726A, a second inner pilot fuel supply system 1728A, a second outer channel 1726B, and a second outer pilot fuel supply system 1728B. The second detonation chamber 1724 is similar to the first detonation chamber 1720. The second inner channel 1726A, the second outer channel 1726B, the second inner pilot fuel supply system 1728A, and the second outer pilot fuel supply system 1728B are similar to the first inner channel 1712A, the first outer channel 1712B, the first inner pilot fuel supply system 1722A, and the first outer pilot fuel supply system 1722B, respectively.

[0231] The third RDC 1710 includes a third detonation chamber 1730, a third inner channel 1732A, a third inner pilot fuel supply system 1734A, a third outer channel 1732B, and a third outer pilot fuel supply system 1734B. The third detonation chamber 1730 is similar to the first detonation chamber 1720. The third inner channel 1732A, the third outer channel 1732B, the third inner pilot fuel supply system 1734A, and the third outer pilot fuel supply system 1734B are similar to the first inner channel 1712A, the first outer channel 1712B, the first inner pilot fuel supply system 1722A, and the first outer pilot fuel supply system 1722B, respectively.

[0232] The cross-sectional areas of the first RDC 1706 , the second RDC 1708 , and the third RDC 1710 are approximately the same and do not generally vary from an upstream portion of the burner system 1700 to a downstream portion of the burner system 1700 .

[0233] In some embodiments, center body 1740 can be translatable and can move through at least a portion of core 1702. For example, center body 1740 can be mechanically or fluidically translated along centerline X in one or more of an upstream direction and a downstream direction.

[0234] Fig.18 1 is an eighteenth embodiment showing a burner system 1800 including a tandem RDC. The burner system 1800 includes a tandem RDC having an inner pilot and an outer pilot and having a center body injection of a pilot fuel, the cross-sectional area of ​​the tandem RDC being increased. The eighteenth embodiment is similar to the seventeenth embodiment, and similar elements have been given similar reference numbers in the 1800 series, and only general differences will be discussed. For example, the first RDC 1706 described in the seventeenth embodiment is numbered as the first RDC 1806 in the eighteenth embodiment.

[0235] The burner system 1800 includes a first wall 1804 separated from a second wall 1805 by a space 1807. The first wall 1804 defines a core 1802. The core 1802 receives a core oxidant fuel mixture 1801. The core 1802 includes a first detonation chamber 1820, a second detonation chamber 1824, and a third detonation chamber 1430 arranged in series. The first wall 1804 is an inner wall of the burner system 1800. The second wall 1805 is an outer wall and may extend around the periphery of the burner system 1800. The first wall 1804 has a taper so that the cross-sectional area of ​​the core 1802 increases from the upstream end to the downstream end of the burner system 1800. Because the first wall is tapered, the cross-sectional area of ​​the first RDC 1806 (as viewed from the end of the burner system 1800) is smaller than the cross-sectional area of ​​the second RDC 1808, and the cross-sectional area of ​​the second RDC 1808 is smaller than the cross-sectional area of ​​the third RDC 1810.

[0236] The first wall 1804 of the burner system 1800 includes a first outer channel 1812B, a second outer channel 1826B, and a third outer channel 1832B. The first outer channel 1812B of the first wall 1804 is coupled to a first outer pilot oxidant-fuel supply 1823B through a first outer pilot fuel supply system 1822B. The first outer pilot oxidant-fuel supply 1823B can be coupled to the first outer channel 1812B in any suitable manner (e.g., through one or more openings in the first wall 1804). The second outer channel 1826B of the first wall 1804 is coupled to a second outer pilot oxidant-fuel supply 1829B through a second outer pilot fuel supply system 1828B. The second outer pilot oxidant-fuel supply 1829B can be coupled to the second outer channel 1826B in any suitable manner (e.g., through one or more openings defined in the first wall 1804). The third outer channel 1832B in the first wall 1804 is coupled to a third outer pilot oxidant-fuel supply 1835B through a third outer pilot fuel supply system 1834B. The third outer pilot oxidant-fuel supply 1835B may be coupled to the third outer channel 1832B in any suitable manner (e.g., through one or more openings in the first wall 1804).

[0237] In some approaches, the first external pilot oxidant-fuel supply 1823B, the second external pilot oxidant-fuel supply 1829B, and the third external pilot oxidant-fuel supply 1835B can be the same supply, and can be, for example, a mixture of fuel and oxidant present in space 1807.

[0238] The core 1802 of the burner system 1800 includes a center body 1840. The center body 1840 has an exterior surface 1844. The exterior surface 1844 of the center body 1840 includes a first inner channel 1812A, a second inner channel 1826A, and a third inner channel 1832A. The first inner channel 1812A of the center body 1840 is coupled to a first inner pilot oxidant-fuel supply 1823A through a first inner pilot fuel supply system 1822A. The first inner pilot oxidant-fuel supply 1823A can be coupled to the first inner channel 1812A in any suitable manner (e.g., through one or more openings in the exterior surface 1844 of the center body 1840). The second inner channel 1826A of the center body 1840 is coupled to a second inner pilot oxidant-fuel supply 1829A through a second inner pilot fuel supply system 1828A. The second inner pilot oxidant-fuel supply 1829A may be coupled to the second inner channel 1826A in any suitable manner (eg, via one or more openings defined in an outer surface 1844 of the center body 1840).

[0239] In some approaches, the first inner pilot oxidant-fuel supply 1823A, the second inner pilot oxidant-fuel supply 1829A, and the third inner pilot oxidant-fuel supply 1835A may be the same supply, and may be a mixture of fuel and oxidant present in the center body 1840, for example.

[0240] The combustor system 1800 includes a first RDC 1806 , a second RDC 1808 , and a third RDC 1810 arranged in series in the core 1802 .

[0241] The first RDC 1806 includes a first detonation chamber 1820, a first inner channel 1812A, a first inner pilot fuel supply system 1822A, a first outer channel 1812B, and a first outer pilot fuel supply system 1822B. The first detonation chamber 1820 is defined by the first inner channel 1812A on the inside and the first outer channel 1812B on the outside. The first detonation chamber 1820 has a first width A1. The first inner pilot fuel supply system 1822A delivers fuel to the first inner channel 1812A. The first outer pilot fuel supply system 1822B delivers pilot fuel to the first outer channel 1812B.

[0242] The second RDC 1808 includes a second detonation chamber 1824, a second inner channel 1826A, a second inner pilot fuel supply system 1828A, a second outer channel 1826B, and a second outer pilot fuel supply system 1828B. The second detonation chamber 1824 is defined by the second inner channel 1826A on the inner side and the second outer channel 1826B on the outer side. The second detonation chamber 1824 has a second width A2. The second inner pilot fuel supply system 1828A delivers pilot fuel to the second inner channel 1826A. The second outer pilot fuel supply system 1828B delivers pilot fuel to the second outer channel 1826B.

[0243] The third RDC 1810 includes a third detonation chamber 1830, a third inner channel 1832A, a third inner pilot fuel supply system 1834A, a third outer channel 1832B, and a third outer pilot fuel supply system 1834B. The third detonation chamber 1830 is defined by the inner third inner channel 1832A and the outer third outer channel 1832B. The third detonation chamber 1830 has a third width A3. The third inner pilot fuel supply system 1834A delivers pilot fuel to the third inner channel 1832A. The third outer pilot fuel supply system 1834B delivers pilot fuel to the third outer channel 1832B.

[0244] The center body 1840 has a taper such that the cross-sectional area of ​​the center body 1840 decreases from the upstream end to the downstream end of the center body 1840. Due to the taper of the first wall 1804 and the taper of the center body 1840, the cross-sectional area A1 of the first detonation chamber 1820 (as viewed from the end of the burner system 1800) is smaller than the cross-sectional area A2 of the second detonation chamber 1824. Similarly, the cross-sectional area A2 of the second detonation chamber 1824 is smaller than the cross-sectional area A3 of the third detonation chamber 1830.

[0245] In some embodiments, center body 1840 can be translatable and can move through at least a portion of core 1802. For example, center body 1840 can be mechanically or fluidically translated along centerline X in one or more of an upstream direction and a downstream direction.

[0246] Fig.1919 is a nineteenth embodiment showing a burner system 1900 including a tandem RDC. The burner system 1900 includes a core 1902, the core 1902 including a tandem RDC. The tandem RDC in the burner system 1900 has an inner pilot and an outer pilot and has a center body injection of a pilot fuel, the tandem RDC having a similar or constant cross-sectional area. The nineteenth embodiment is similar to the seventeenth embodiment, and similar elements have been given similar reference numbers in the 1900 series, and only general differences will be discussed. For example, the first RDC 1706 described in the seventeenth embodiment is numbered as the first RDC 1906 in the nineteenth embodiment.

[0247] The burner system 1900 includes a first wall 1904 separated from a second wall 1905 by a space 1907. The first wall 1904 defines a core 1902. The core 1902 receives a core oxidant fuel mixture 1901. The core 1902 includes a first detonation chamber 1920, a second detonation chamber 1924, and a third detonation chamber 1430 arranged in series. The first wall 1904 is an inner wall of the burner system 1900. The second wall 1905 is an outer wall and can extend around the periphery of the burner system 1900.

[0248] The first wall 1904 of the burner system 1900 includes a first outer channel 1912B, a second outer channel 1926B, and a third outer channel 1932B. The first outer channel 1912B of the first wall 1904 is coupled to a first outer pilot oxidant-fuel supply 1923B through a first outer pilot fuel supply system 1922B. The first outer pilot oxidant-fuel supply 1923B can be coupled to the first outer channel 1912B in any suitable manner (e.g., through one or more openings in the first wall 1904). The second outer channel 1926B of the first wall 1904 is coupled to a second outer pilot oxidant-fuel supply 1929B through a second outer pilot fuel supply system 1928B. The second outer pilot oxidant-fuel supply 1929B can be coupled to the second outer channel 1926B in any suitable manner (e.g., through one or more openings defined in the first wall 1904). The third outer channel 1932B in the first wall 1904 is coupled to a third outer pilot oxidant-fuel supply 1935B through a third outer pilot fuel supply system 1934B. The third outer pilot oxidant-fuel supply 1935B may be coupled to the third outer channel 1932B in any suitable manner (e.g., through one or more openings in the first wall 1904).

[0249] In some approaches, the first external pilot oxidant-fuel supply 1923B, the second external pilot oxidant-fuel supply 1929B, and the third external pilot oxidant-fuel supply 1935B can be the same supply, and can be, for example, a mixture of fuel and oxidant present in space 1907.

[0250] The core 1902 of the burner system 1900 includes a center body 1940. The center body 1940 has an exterior surface 1944. The exterior surface 1944 of the center body 1940 includes a first inner channel 1912A, a second inner channel 1926A, and a third inner channel 1932A. The first inner channel 1912A of the center body 1940 is coupled to a first inner pilot oxidant-fuel supply 1923A through a first inner pilot fuel supply system 1922A. The first inner pilot oxidant-fuel supply 1923A may be coupled to the first inner channel 1912A in any suitable manner (e.g., through one or more openings in the exterior surface 1944 of the center body 1940). The second inner channel 1926A of the center body 1940 is coupled to a second inner pilot oxidant-fuel supply 1929A through a second inner pilot fuel supply system 1928A. The second inner pilot oxidant-fuel supply 1929A may be coupled to the second inner channel 1926A in any suitable manner (eg, via one or more openings defined in an outer surface 1944 of the center body 1940).

[0251] In some approaches, the first inner pilot oxidant-fuel supply 1923A, the second inner pilot oxidant-fuel supply 1929A, and the third inner pilot oxidant-fuel supply 1935A may be the same supply, and may be a mixture of fuel and oxidant present in the center body 1940, for example.

[0252] The burner system 1900 includes a first RDC 1906 , a second RDC 1908 , and a third RDC 1910 .

[0253] The first RDC 1906 includes a first detonation chamber 1920, a first inner channel 1912A, a first inner pilot fuel supply system 1922A, a first outer channel 1912B, and a first outer pilot fuel supply system 1922B. The first detonation chamber 1980 is defined by the first inner channel 1912A on the inside and the first outer channel 1912B on the outside. The first inner channel 1912A is offset from the first outer channel 1912B so that the first outer channel 1912B is positioned further downstream than the first inner channel 1912A. The first inner pilot fuel supply system 1922A delivers fuel to the first inner channel 1912A. The first outer pilot fuel supply system 1922B delivers pilot fuel to the first outer channel 1912B.

[0254] The second RDC 1908 includes a second detonation chamber 1924, a second inner channel 1926A, a second inner pilot fuel supply system 1928A, a second outer channel 1926B, and a second outer pilot fuel supply system 1928B. The second detonation chamber 1924 is defined by the second inner channel 1926A on the inside and the second outer channel 1926B on the outside. The second inner channel 1926A is offset from the second outer channel 1926B so that the second outer channel 1926B is positioned further downstream than the second inner channel 1926A. The second inner pilot fuel supply system 1928A delivers pilot fuel to the second inner channel 1926A. The second outer pilot fuel supply system 1928B delivers pilot fuel to the second outer channel 1926B.

[0255] The third RDC 1910 includes a third detonation chamber 1930, a third inner channel 1932A, a third inner pilot fuel supply system 1934A, a third outer channel 1932B, and a third outer pilot fuel supply system 1934B. The third detonation chamber 1930 is defined by the third inner channel 1932A on the inside and the third outer channel 1932B on the outside. The third inner channel 1932A is offset from the third outer channel 1932B so that the third outer channel 1932B is positioned further downstream than the third inner channel 1932A. The third inner pilot fuel supply system 1934A delivers pilot fuel to the third inner channel 1932A. The third outer pilot fuel supply system 1934B delivers pilot fuel to the third outer channel 1932B.

[0256] In some embodiments, center body 1940 can be translatable and can move through at least a portion of core 1902. For example, center body 1940 can be mechanically or fluidically translated along centerline X in one or more of an upstream direction and a downstream direction.

[0257] Fig. 20 2000 is a twentieth embodiment showing a burner system 2000 including a tandem RDC. The burner system 2000 includes a tandem RDC having staggered inner and outer pilots and having a center body injection of pilot fuel, the cross-sectional area of ​​the tandem RDC increasing. The twentieth embodiment is similar to the nineteenth embodiment, and similar elements have been given similar reference numbers in the 2000 series, and only general differences will be discussed. For example, the first RDC 1906 described in the nineteenth embodiment is numbered as the first RDC 2006 in the twentieth embodiment.

[0258] The burner system 2000 includes a first wall 2004 separated from a second wall 2005 by a space 2007. The first wall 2004 defines a core 2002. The core 2002 receives a core oxidant fuel mixture 2001. The core 2002 includes a first detonation chamber 2020, a second detonation chamber 2024, and a third detonation chamber 2030 arranged in series. The first wall 2004 is an inner wall of the burner system 2000. The second wall 2005 is an outer wall and may extend around the periphery of the burner system 2000. The first wall 2004 has a taper so that the cross-sectional area of ​​the core 2002 increases from the upstream end to the downstream end of the burner system 2000.

[0259] The first wall 2004 of the burner system 2000 includes a first outer channel 2012B, a second outer channel 2026B, and a third outer channel 2032B. The first outer channel 2012B of the first wall 2004 is coupled to a first outer pilot oxidant-fuel supply 2023B through a first outer pilot fuel supply system 2022B. The first outer pilot oxidant-fuel supply 2023B can be coupled to the first outer channel 2012B in any suitable manner (e.g., through one or more openings in the first wall 2004). The second outer channel 2026B of the first wall 2004 is coupled to a second outer pilot oxidant-fuel supply 2029B through a second outer pilot fuel supply system 2028B. The second outer pilot oxidant-fuel supply 2029B can be coupled to the second outer channel 2026B in any suitable manner (e.g., through one or more openings defined in the first wall 2004). The third outer channel 2032B in the first wall 2004 is coupled to a third outer pilot oxidant-fuel supply 2035B through a third outer pilot fuel supply system 2034B. The third outer pilot oxidant-fuel supply 2035B may be coupled to the third outer channel 2032B in any suitable manner (e.g., through one or more openings in the first wall 2004).

[0260] In some approaches, the first external pilot oxidant-fuel supply 2023B, the second external pilot oxidant-fuel supply 2029B, and the third external pilot oxidant-fuel supply 2035B can be the same supply, and can be, for example, a mixture of fuel and oxidant present in the space 2007.

[0261] The core 2002 of the burner system 2000 includes a center body 2040. The center body 2040 has an exterior surface 2044. The exterior surface 2044 of the center body 2040 includes a first inner channel 2012A, a second inner channel 2026A, and a third inner channel 2032A. The first inner channel 2012A of the center body 2040 is coupled to a first inner pilot oxidant-fuel supply 2023A through a first inner pilot fuel supply system 2022A. The first inner pilot oxidant-fuel supply 2023A can be coupled to the first inner channel 2012A in any suitable manner (e.g., through one or more openings in the exterior surface 2044 of the center body 2040). The second inner channel 2026A of the center body 2040 is coupled to a second inner pilot oxidant-fuel supply 2029A through a second inner pilot fuel supply system 2028A. The second inner pilot oxidant-fuel supply 2029A may be coupled to the second inner channel 2026A in any suitable manner (eg, via one or more openings defined in an outer surface 2044 of the center body 2040).

[0262] In some approaches, the first inner pilot oxidant-fuel supply 2023A, the second inner pilot oxidant-fuel supply 2029A, and the third inner pilot oxidant-fuel supply 2035A may be the same supply, and may be, for example, a mixture of fuel and oxidant present in the center body 2040 .

[0263] The burner system 2000 also includes a first RDC 2006 , a second RDC 2008 , and a third RDC 2010 .

[0264] The first RDC 2006 includes a first detonation chamber 2020, a first inner channel 2012A, a first inner pilot fuel supply system 2022A, a first outer channel 2012B, and a first outer pilot fuel supply system 2022B. The first detonation chamber 2080 is defined by the first inner channel 2012A on the inside and the first outer channel 2012B on the outside. The first inner channel 2012A is offset from the first outer channel 2012B so that the first outer channel 2012B is positioned more downstream than the first inner channel 2012A. The first inner pilot fuel supply system 2022A delivers fuel to the first inner channel 2012A. The first outer pilot fuel supply system 2022B delivers pilot fuel to the first outer channel 2012B.

[0265] The second RDC 2008 includes a second detonation chamber 2024, a second inner channel 2026A, a second inner pilot fuel supply system 2028A, a second outer channel 2026B, and a second outer pilot fuel supply system 2028B. The second detonation chamber 2024 is defined by the second inner channel 2026A on the inside and the second outer channel 2026B on the outside. The second inner channel 2026A is offset from the second outer channel 2026B so that the second outer channel 2026B is positioned more downstream than the second inner channel 2026A. The second inner pilot fuel supply system 2028A delivers pilot fuel to the second inner channel 2026A. The second outer pilot fuel supply system 2028B delivers pilot fuel to the second outer channel 2026B.

[0266] The third RDC 2010 includes a third detonation chamber 2030, a third inner channel 2032A, a third inner pilot fuel supply system 2034A, a third outer channel 2032B and a third outer pilot fuel supply system 2034B. The third detonation chamber 2030 is defined by the third inner channel 2032A on the inside and the third outer channel 2032B on the outside. The third inner channel 2032A is offset from the third outer channel 2032B so that the third outer channel 2032B is positioned further downstream than the third inner channel 2032A. The third inner pilot fuel supply system 2034A delivers pilot fuel to the third inner channel 2032A. The third outer pilot fuel supply system 2034B delivers pilot fuel to the third outer channel 2032B.

[0267] In addition, the burner system 2000 includes a center body 2040 extending axially through the core 2002. The center body 2040 also has a taper such that the cross-sectional area of ​​the center body 2040 decreases from the upstream end to the downstream end of the center body 2040. Due to the taper of the first wall 2004 and the taper of the center body 2040, the cross-sectional area A1 of the first detonation chamber 2020 (as viewed from the end of the burner system 2000) is smaller than the cross-sectional area A2 of the second detonation chamber 2024. Similarly, the cross-sectional area A2 of the second detonation chamber 1824 is smaller than the cross-sectional area A3 of the third detonation chamber 2030.

[0268] In some embodiments, the center body 2040 can be translatable and can move through at least a portion of the core 2002. For example, the center body 2040 can be mechanically or fluidically translated along the center line X in one or more of an upstream direction and a downstream direction.

[0269] In some approaches, the burner systems described herein may be made of high temperature resistant materials such as metals.

[0270] It is contemplated that any features of the embodiments of the burner systems described herein and depicted in Figures 1-20 may be combined in any manner.Any aspects of the various illustrated embodiments may be combined to form new combinations.

[0271] Reference now Fig.21 , a gas turbine engine 2100 compatible with many of these teachings will now be presented. The gas turbine engine 2100 may incorporate any combustor system having a tandem RDC as described herein. In some embodiments, the gas turbine engine 2100 may include any tandem RDC as described herein in the combustor 2118. In other embodiments, the gas turbine engine 2100 may include a tandem RDC as described herein in the enhancer 2112. It should be understood that Fig.21 The gas turbine engine 2100 depicted in and described below is provided as an example only. In other embodiments, the gas turbine engine 2100 may have any other suitable configuration. For example, in other exemplary embodiments, the gas turbine engine 2100 may include any suitable number of compressors, turbines, shafts, or combinations thereof. In addition, the gas turbine engine 2100 may not include every feature described herein, or alternatively, may include one or more features not described herein. In addition, the gas turbine engine 2100 may be configured as any other suitable ducted gas turbine engine (e.g., a turbofan engine), or used in conjunction with a ramjet or scramjet. In a ramjet or scramjet configuration, the turbomachinery will be bypassed due to excessive temperature.

[0272] As a reference frame, the gas turbine engine 2100 defines an axial direction 2102 , a radial direction 2104 , and a circumferential direction 2106 (ie, directions extending about the axial direction 2102 ).

[0273] Gas turbine engine 2100 includes a fan 2108, followed by a core section 2110, an enhancer 2112, and an exhaust system 2114. Core section 2110 includes a compressor 2116, followed by a combustor 2118 and a turbine 2120. Enhancer 2112 is positioned downstream of core section 2110 and upstream of exhaust system 2114. Shaft 2122 is coupled to several components throughout gas turbine engine 2100, including compressor 2116 and turbine 2120. In addition, shaft 2122 is coupled to a load (not shown).

[0274] The fan 2108 draws the oxidant into the gas turbine engine 2100. It is contemplated that the fan 2108 may be any suitable type of oxidant intake device, such as a cold oxidant intake. The fan 2108 draws the oxidant into the gas turbine engine 2100. The turbine 2120 may drive the rotation of the blades of the fan. The fan 2108 is in fluid communication with the bypass oxidant flow channel 2126 and the core oxidant path 2128.

[0275] The compressor 2116 is positioned downstream of the fan 2108 and upstream of the turbine 2120. The compressor 2116 includes blades rigidly mounted to a rotor that is coupled to a shaft 2122. The combustor 2118 is positioned downstream of the compressor 2116. The combustor 2118 is configured to burn an oxidant-fuel mixture and includes a passage that directs the combustion gases into the turbine 2120. The combustor 2118 may incorporate a rotating detonation architecture to generate a rotating detonation wave. The rotating detonation architecture of the combustor 2118 may be any of the architectures shown in FIGS. 1-20.

[0276] Turbine 2120 includes one or more stators having fixed vanes or blades, and one or more rotors having blades that rotate relative to the stators. Turbine 2120 includes a turbine rotor coupled to shaft 2122.

[0277] The enhancer 2112 is constructed to burn a mixture of fuel and oxidant in a certain volume thereof, and is combined with a rotating detonation architecture to generate a rotating detonation wave. The rotating detonation architecture of the enhancer 2112 can be any architecture shown in Figures 1-20. The enhancer 2112 includes one or more fuel supply systems 2121. One or more fuel supply systems 2121 can supply liquid fuel or gaseous fuel, such as jet fuel, methane, ethylene or H2. The fuel type may depend on one or more of the engine architecture, engine size and thrust level. It is contemplated that one or more separate fuel delivery systems can be used to deliver fuel to the enhancer 2112. The enhancer 2112 is positioned downstream of the turbine 2120 of the gas turbine engine 2100 and upstream of the exhaust system 2114.

[0278] As will be appreciated, the shaft 2122 may be coupled to a load. The load may be any suitable device that can use the power of the rotational output of the gas turbine engine 2100, such as an external mechanical load or a generator. For example, the load may include a propeller of an aircraft or a generator.

[0279] In operation, oxidant enters gas turbine engine 2100 through fan 2108. A portion of oxidant enters bypass oxidant flow channel 2126 to provide bypass oxidant flow to enhancer 2112. Another portion of oxidant enters core section 2110 and flows through core oxidant path 2128 as core oxidant. Core oxidant enters compressor 2116. When core oxidant passes through rotating blades of compressor 2116, pressure increases, thereby providing enough oxidant for combustion in burner 2118. Burner 2118 receives core oxidant from compressor 2116 and fuel from fuel supply to form oxidant-fuel mixture. Burner 2118 ignites and burns oxidant-fuel mixture, and causes hot pressurized gas to enter turbine 2120. Burner 2118 can burn oxidant-fuel mixture in rotating detonation reaction. Hot pressurized gas passes through rotor blades of turbine 2120, thereby driving turbine rotor to rotate. The connection between turbine rotor and shaft 2122 causes shaft 2122 to rotate. The rotor of compressor 2116 is driven to rotate by shaft 2122.

[0280] The booster 2112 receives core oxidant from the turbine 2120 via a core oxidant path 2128. The booster 2112 also receives bypass oxidant from the fan 2108 via a bypass oxidant flow channel 2126. Fuel is provided to the booster 2112 via one or more fuel supply systems 2121. The booster 2112 ignites a mixture of bypass oxidant and fuel in a rotating detonation reaction. The rotating detonation reaction supports a combustion reaction that consumes the mixture of core oxidant and fuel in the booster 2112. Products from the reactions occurring within the booster 2112, including hot pressurized gases, enter the exhaust system 2114, thereby enhancing thrust. The products leave the gas turbine engine 2100 through the outlet of the exhaust system 2114 to generate thrust for the gas turbine engine 2100.

[0281] Reference now Fig. 22 , a ramjet / scramjet 2200 is shown. It should be understood that the ramjet / scramjet 2200 is only an example. In other embodiments, the ramjet / scramjet 2200 may have any other suitable configuration.

[0282] The oxidizer enters the ramjet / scramjet 2200 through the air inlet 2208. The ramjet / scramjet 2200 lacks a compressor. The forward speed of the vehicle (e.g., aircraft) compresses the oxidizer. The oxidizer then enters the burner 2218. The fuel is injected into the burner 2218 via a fuel injector and mixed with the oxidizer, and ignited via an igniter (such as a flame stabilizer) (not shown). The products of the reactions occurring in the burner 2218 and the tandem RDC 2212 (including hot pressurized gases) enter the exhaust nozzle 2214, thereby enhancing thrust. The combustion and detonation products expand and are released to the surrounding environment through the exhaust nozzle 2214.

[0283] The ramjet / scramjet engine can have three operating modes: ramjet mode, dual mode ramjet (DMRJ) mode, and scramjet mode (e.g., supersonic combustion ramjet). In ramjet mode, the velocity of the oxidant flow entering the burner 2218 is less than Mach 1. In ramjet mode, the minimum velocity of the flow (e.g., including combustion reactants, products, etc.) in the burner 2218 and the exhaust nozzle 2214 is less than Mach 1. In DMRJ mode, the velocity of the oxidant flow entering the burner 2218 is greater than Mach 1. In DMRJ mode, the minimum velocity of the flow (e.g., including combustion reactants, products, etc.) in the burner 2218 and the exhaust nozzle 2214 is less than Mach 1. In scramjet mode, the velocity of the oxidant flow entering the burner 2218 is greater than Mach 1. In scramjet mode, the minimum velocity of the flow (e.g., including combustion reactants, products, etc.) in the burner 2218 and the exhaust nozzle 2214 is also greater than Mach 1.

[0284] Fig.23 A ramjet / scramjet engine including a tandem RDC is shown in three different operating modes: ramjet mode 2300A, dual mode ramjet (DMRJ) mode 2300B, and scramjet mode 2300C. Fig.23 In the ramjet / scramjet of FIG. 23, a tandem RDC 2312 is disposed downstream of the isolator 2318. The combustion products leave the isolator 2318 and are released to the tandem RDC 2312. The tandem RDC 2312 includes at least two RDCs arranged in series. The architecture of the tandem RDC 2312 may be any of the architectures shown in FIGS. 1-20. The tandem RDC 2312 ignites a mixture of residual oxidant and fuel from the combustion products in a rotating detonation reaction. The rotating detonation reaction supports a combustion reaction that consumes the unreacted fuel and oxidant from the isolator 2318.

[0285] In ramjet mode 2300A, the oxidizer enters the ramjet / scramjet at the inlet 2308 at a speed less than Mach 1. Combustion and detonation also occur at less than Mach 1 in the tandem RDC 2312. Expansion of the combustion and detonation products also occurs at less than Mach 1 in the exhaust nozzle 2314.

[0286] In DMRJ mode 2300B, the oxidizer enters the ramjet / scramjet at the inlet 2308 at a speed above Mach 1. In the tandem RDC 2312, combustion and detonation also occur above Mach 1. In the exhaust nozzle 2314, expansion of the combustion and detonation products occurs below Mach 1.

[0287] In scramjet mode 2300C, combustion is supersonic. The oxidizer enters the ramjet / scramjet at the inlet 2308 at a supersonic speed of greater than Mach 1. In the tandem RDC 2312, combustion and detonation also occur at greater than Mach 1. In addition, in the exhaust nozzle 2314, expansion of the combustion and detonation products occurs at greater than Mach 1.

[0288] Go to Fig.24 , a rocket engine 2400 compatible with many of these teachings is presented. The rocket engine 2400 can incorporate any burner system having a tandem RDC as described herein. The rocket engine 2400 includes an oxidizer tank 2408 and a fuel tank 2410. The oxidizer tank 2408 and the fuel tank 2410 supply oxidizer and fuel to a combustion chamber 2418. A tandem RDC 2412 is positioned downstream of the combustion chamber 2418. The tandem RDC 2412 consumes unreacted oxidizer, fuel, or a combination thereof from the combustion chamber 2418 and further enhances engine thrust. The combustion and detonation products are released from an exhaust nozzle 2420 of the rocket engine to generate thrust.

[0289] Fig.25 is a flow chart of a method for supporting a combustion reaction using at least two RDCs arranged in series. The method may employ one or more of the rotating detonation architectures of FIGS. 1-20. Furthermore, it is contemplated that the method may be used to enhance thrust in various types of engines, such as gas turbine engines, scramjets, ramjets, or rocket engines.

[0290] At block 2510, the method includes supplying a core oxidant-fuel mixture to a burner system having a first RDC and at least one additional RDC arranged in series. The core oxidant-fuel mixture may be a mixture of a fuel and any type of gaseous oxidant, liquid oxidant, solid oxidant, or combination thereof. In some embodiments, the core oxidant-fuel mixture may include unreacted reactants from a combustion reaction such as that occurring in a gas turbine engine combustor, a ramjet / scramjet combustion chamber, or a rocket combustion chamber.

[0291] At block 2520, the method includes supplying a first pilot oxidant-fuel mixture to a first RDC. The first RDC includes a first detonation chamber having a first channel to stabilize a rotating detonation wave. The first pilot oxidant-fuel mixture may be supplied using any suitable pilot fuel supply system.

[0292] At box 2530, the method includes supplying a second pilot oxidant-fuel mixture to at least one additional RDC. The at least one additional RDC includes a second detonation chamber having a second channel to stabilize the rotating detonation wave. The second pilot oxidant-fuel mixture can be supplied using any suitable pilot fuel supply system.

[0293] At box 2540, the method includes igniting a first pilot oxidant-fuel mixture in the first RDC, and igniting a second pilot oxidant-fuel mixture in at least one additional RDC to generate a rotating detonation wave, which consumes at least a portion of the core oxidant-fuel mixture to support the combustion reaction within the volume. It should be understood that the ignition of the first RDC and at least one additional RDC can occur in any order. When a series RDC is included in the burner system, the ignition does not have to occur sequentially from upstream to downstream (for example, ignite the first RDC, then ignite at least one additional RDC, etc.). For example, in some cases, the RDC positioned sequentially as the second can be ignited first, and then the RDC positioned sequentially as the first can be ignited. The ability to ignite the series RDC in any order contributes to the operational flexibility of the system including the series RDC. For example, if there is a possibility of the detonation wave propagating upstream, the RDC positioned sequentially as the second (or even the third or fourth) may be ignited before the RDC positioned sequentially as the first. In some cases, less than all series RDCs may be used in operation, or even only one series RDC may be used. In addition, one RDC can be used to ignite another RDC. For example, a first RDC can be used to ignite at least one additional RDC.

[0294] In some embodiments, the method further includes stabilizing the rotating detonation wave via a first channel in the first rotating detonation combustor and a second channel in the second rotating detonation combustor.

[0295] Further aspects of the disclosure are provided by the subject matter of the following clauses:

[0296] A burner system comprises: a volume that receives a core oxidant-fuel mixture, the volume comprising: a first detonation chamber, the first detonation chamber being at least partially defined by a peripheral wall and at least partially defined by a first channel extending circumferentially around a centerline of the burner system, wherein the first detonation chamber receives a first pilot oxidant-fuel mixture; and at least one additional detonation chamber, the at least one additional detonation chamber being disposed downstream of the first detonation chamber and at least partially defined by a second channel extending circumferentially around the centerline of the burner system, wherein the at least one additional detonation chamber receives a second pilot oxidant-fuel mixture; wherein the first pilot oxidant-fuel mixture reacts in the first detonation chamber and the second pilot oxidant-fuel mixture reacts in the at least one additional detonation chamber to generate a rotating detonation combustion wave, the rotating detonation combustion wave being guided by the first channel and the second channel to support a reaction that consumes the core oxidant-fuel mixture.

[0297] The burner system of any preceding clause, wherein the first channel is a first outer channel formed in the peripheral wall, and wherein the second channel is a second outer channel formed in the peripheral wall.

[0298] A burner system according to any of the preceding clauses, wherein the outer peripheral wall further comprises: a first external pilot fuel supply system, which produces the first pilot oxidant-fuel mixture in the first external channel; and a second external pilot fuel supply system, which produces the second pilot oxidant-fuel mixture in the second external channel.

[0299] The combustor system of any preceding clause, further comprising a center body defined by an exterior surface, wherein the exterior surface of the center body includes first and second interior channels formed therein.

[0300] A burner system according to any preceding clause, wherein the center body further comprises: a first internal pilot fuel supply system, the first internal pilot fuel supply system producing the first pilot oxidant-fuel mixture; and a second internal pilot fuel supply system, the second internal pilot fuel supply system producing the second pilot oxidant-fuel mixture.

[0301] The burner system of any preceding clause, wherein the first inner channel is opposite the first outer channel, and wherein the second inner channel is opposite the second outer channel.

[0302] The burner system of any preceding clause, wherein the first and second inner channels are interleaved with the first and second outer channels.

[0303] The burner system of any preceding clause, further comprising a center body defined by an exterior surface, wherein the first channel is a first interior channel formed in the exterior surface of the center body, and wherein the second channel is a second interior channel formed in the exterior surface of the center body.

[0304] A burner system according to any preceding clause, wherein the center body further comprises: a first internal pilot fuel supply system, the first internal pilot fuel supply system producing the first pilot oxidant-fuel mixture; and a second internal pilot fuel supply system, the second internal pilot fuel supply system producing the second pilot oxidant-fuel mixture.

[0305] The burner system of any preceding clause, wherein at least a portion of the burner system lacks a center body.

[0306] The burner system of any preceding clause, wherein at least a portion of the burner system comprises a center body.

[0307] A combustor system as in any preceding clause, wherein the center body has a tapered shape increasing in size from upstream to downstream.

[0308] A combustor system as in any preceding clause, wherein the center body has a tapered shape that decreases in size from upstream to downstream.

[0309] A burner system as claimed in any preceding clause, wherein the peripheral wall has a taper that decreases in size from upstream to downstream.

[0310] The burner system of any preceding clause, wherein the first detonation chamber has a first cross-sectional area and the at least one additional detonation chamber has a second cross-sectional area, the second cross-sectional area being smaller than the first cross-sectional area.

[0311] The burner system of any preceding clause, wherein the first detonation chamber has a first cross-sectional area and the at least one additional detonation chamber has a second cross-sectional area, the second cross-sectional area being greater than the first cross-sectional area.

[0312] A method comprising: supplying a core oxidant-fuel mixture to a burner system comprising a first rotating detonation burner and at least one additional rotating detonation burner arranged in series; supplying a first pilot oxidant-fuel mixture to the first rotating detonation burner; supplying a second pilot oxidant-fuel mixture to the at least one additional rotating detonation burner; and igniting the first pilot oxidant-fuel mixture in the first rotating detonation burner and igniting the second pilot oxidant-fuel mixture in the at least one additional rotating detonation burner to generate a rotating detonation wave that consumes at least a portion of the core oxidant-fuel mixture.

[0313] A method as in any preceding clause, further comprising stabilizing the rotating detonation wave via a first channel in the first rotating detonation combustor and a second channel in the at least one additional rotating detonation combustor.

[0314] An engine includes a combustion system, the combustion system comprising: a first rotating detonation burner, the first rotating detonation burner including a first detonation chamber, a first channel surrounding at least a portion of the first detonation chamber, and a first pilot fuel supply system configured to deliver pilot fuel to the first channel; and at least one additional rotating detonation burner, the at least one additional rotating detonation burner being arranged in series with the first rotating detonation burner, the at least one additional rotating detonation burner including a second detonation chamber, a second channel surrounding at least a portion of the second detonation chamber, and a second pilot fuel supply system configured to deliver pilot fuel to the second channel.

[0315] An engine as described in any preceding clause, wherein the engine is a ramjet, a scramjet, a gas turbine engine or a rocket engine.

[0316] A burner system comprises: a first wall, which at least partially defines a core for receiving a core oxidant-fuel mixture, the core comprising a first detonation chamber and at least one additional detonation chamber, the first wall comprising a first outer channel extending circumferentially around the first detonation chamber and at least one additional outer channel extending circumferentially around the at least one additional detonation chamber; and at least one external pilot oxidant-fuel supply system, which supplies a pilot oxidant-fuel mixture to the first outer channel and the at least one additional outer channel; wherein the pilot oxidant-fuel mixture is configured to ignite to generate a rotating detonation wave, which is guided by the first outer channel and the at least one additional outer channel to support a reaction that consumes the core oxidant-fuel mixture.

[0317] A burner system according to any preceding clause, wherein the first wall includes a first rearward-facing step and a first forward-facing step recessed in the first wall, the first rearward-facing step and the first forward-facing step being joined together by a first recessed surface, and wherein the first rearward-facing step, the first forward-facing step and the first recessed surface define the first outer channel.

[0318] A burner system according to any preceding clause, wherein the first wall includes a second rearward-facing step and a second forward-facing step recessed in the first wall, the second rearward-facing step and the second forward-facing step being joined together by a second recessed surface, and wherein the second rearward-facing step, the second forward-facing step and the second recessed surface define the at least one additional external channel.

[0319] The burner system of any preceding clause, further comprising a center body defined by an exterior surface, wherein the exterior surface of the center body includes a first interior channel and at least one additional interior channel formed therein.

[0320] A burner system according to any preceding clause, wherein the center body further comprises: at least one internal pilot fuel supply system, the at least one internal pilot fuel supply system supplying at least one internal pilot oxidant-fuel mixture to the first internal channel and the at least one additional internal channel.

[0321] A burner system as described in any preceding clause, wherein the first inner channel and the first outer channel are disposed at the same position along the length of the burner system, and wherein the at least one additional inner channel and the at least one additional outer channel are disposed at the same position along the length of the burner system.

[0322] The burner system of any preceding clause, wherein the first inner channel is staggered with the first outer channel along the length of the burner system, and wherein the at least one additional inner channel is staggered with the at least one additional outer channel along the length of the burner system.

[0323] The combustor system of any preceding clause, wherein the outer surface of the center body includes a first rearwardly facing step and a first concave surface recessed in the outer surface, and wherein the first rearwardly facing step and the first concave surface define the first inner channel.

[0324] The combustor system of any preceding clause, wherein the outer surface of the center body includes a second rearwardly facing step and a second concave surface recessed in the outer surface, and wherein the second rearwardly facing step and the second concave surface define the at least one additional internal channel.

[0325] The combustor system of any preceding clause, wherein at least a portion of the core comprises a movable center body.

[0326] The combustor system of any preceding clause, wherein at least one of the first detonation chamber or the at least one additional detonation chamber is devoid of a center body.

[0327] The combustor system of any preceding clause, wherein at least one of the first detonation chamber or the at least one additional detonation chamber comprises a center body.

[0328] A combustor system as in any preceding clause, wherein the center body has a tapered shape increasing in size from upstream to downstream.

[0329] The combustor system of any preceding clause, wherein the combustor system is configured for use in at least one of a ramjet engine, a scramjet engine, a gas turbine engine, or a rocket engine.

[0330] The burner system of any preceding clause, wherein at least a portion of the first wall has a tapered thickness that decreases in dimension from upstream to downstream.

[0331] The burner system of any preceding clause, wherein the first detonation chamber has a first cross-sectional area and the at least one additional detonation chamber has a second cross-sectional area, the second cross-sectional area being different from the first cross-sectional area.

[0332] A method comprising: supplying a core oxidant-fuel mixture to a burner system comprising a first rotating detonation burner and at least one additional rotating detonation burner arranged in series; supplying a first pilot oxidant-fuel mixture to the first rotating detonation burner; supplying a second pilot oxidant-fuel mixture to the at least one additional rotating detonation burner; and igniting at least one of the first pilot oxidant-fuel mixture in the first rotating detonation burner or the second pilot oxidant-fuel mixture in the at least one additional rotating detonation burner to generate a rotating detonation wave that consumes at least a portion of the core oxidant-fuel mixture.

[0333] A method as in any preceding clause, further comprising stabilizing the rotating detonation wave via a first channel in the first rotating detonation combustor and a second channel in the at least one additional rotating detonation combustor.

[0334] A burner system comprises: a first wall, which at least partially defines a core that receives a core oxidizer-fuel mixture, the core including a first detonation chamber and at least one additional detonation chamber; a center body, which is disposed in the core, the center body having an outer surface, the outer surface including a first inner channel extending circumferentially around the first detonation chamber and at least one additional inner channel extending circumferentially around the at least one additional detonation chamber; at least one internal pilot oxidizer-fuel supply system, the at least one internal pilot oxidizer-fuel supply system supplies a pilot oxidizer-fuel mixture to the first inner channel and the at least one additional inner channel; and wherein the pilot oxidizer-fuel mixture ignites to generate a rotating detonation wave, the rotating detonation wave is guided by the first inner channel and the at least one additional inner channel to support a reaction that consumes the core oxidizer-fuel mixture.

[0335] A burner system according to any preceding clause, wherein the outer surface of the center body includes a first rearward facing step and a first concave surface recessed in the outer surface, and wherein the first rearward facing step and the first concave surface define the first internal channel; and wherein the outer surface of the center body includes a second rearward facing step and a second concave surface recessed in the outer surface, and wherein the second rearward facing step and the second concave surface define the at least one additional internal channel.

Claims

1. A burner system, characterized in that: include: a first wall at least partially defining a core for receiving a core oxidant-fuel mixture, the core including a first detonation chamber and at least one additional detonation chamber, the first wall including a first outer channel extending circumferentially about the first detonation chamber and at least one additional outer channel extending circumferentially about the at least one additional detonation chamber; as well as at least one external pilot oxidant-fuel supply system, the at least one external pilot oxidant-fuel supply system supplying a pilot oxidant-fuel mixture to the first external channel and the at least one additional external channel; The pilot oxidant-fuel mixture is configured to ignite to generate a rotating detonation wave directed by the first outer channel and the at least one additional outer channel to support a reaction that consumes the core oxidant-fuel mixture.

2. The burner system according to claim 1, characterized in that in, The first wall includes a first rearward-facing step and a first forward-facing step recessed in the first wall, the first rearward-facing step and the first forward-facing step being joined together by a first recessed surface, and wherein the first rearward-facing step, the first forward-facing step and the first recessed surface define the first outer channel.

3. The burner system according to claim 2, characterized in that in, The first wall includes a second rearward-facing step and a second forward-facing step recessed in the first wall, the second rearward-facing step and the second forward-facing step being joined together by a second recessed surface, and wherein the second rearward-facing step, the second forward-facing step and the second recessed surface define the at least one additional outer channel.

4. The burner system according to claim 1, characterized in that Further included is a center body defined by an exterior surface, wherein the exterior surface of the center body includes a first interior channel and at least one additional interior channel formed therein.

5. The burner system according to claim 4, characterized in that in, The centrosome further comprises: At least one internal pilot fuel supply system supplies at least one internal pilot oxidant-fuel mixture to the first internal channel and the at least one additional internal channel.

6. The burner system according to claim 4, characterized in that in, The first inner channel and the first outer channel are disposed at a same location along a length of the burner system, and wherein the at least one additional inner channel and the at least one additional outer channel are disposed at a same location along the length of the burner system.

7. The burner system according to claim 4, characterized in that in, The first inner channel is staggered with the first outer channel along a length of the burner system, and wherein the at least one additional inner channel is staggered with the at least one additional outer channel along the length of the burner system.

8. The burner system according to claim 4, characterized in that in, The exterior surface of the center body includes a first rearwardly facing step and a first concave surface recessed in the exterior surface, and wherein the first rearwardly facing step and the first concave surface define the first inner channel.

9. The burner system according to claim 8, characterized in that in, The exterior surface of the center body includes a second rearwardly facing step and a second concave surface that are concave in the exterior surface, and wherein the second rearwardly facing step and the second concave surface define the at least one additional internal channel.

10. The burner system according to claim 1, characterized in that in, At least a portion of the core includes a movable central body.

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