Knock combustion system

Abstract

An explosive combustion system includes an explosive combustor. The explosive combustor includes an explosive manifold and one or more explosive chamber walls defining an explosive chamber. The explosive manifold includes a plurality of explosive fluid paths defined by an overall structure of the explosive manifold, and a plurality of explosive port sets each including a plurality of explosive ports disposed about a surface of the explosive manifold. A respective one of the plurality of explosive port sets provides fluid communication from a corresponding one of the plurality of explosive fluid paths to the explosive chamber through the plurality of explosive ports corresponding to the respective one of the plurality of explosive port sets. The plurality of explosive ports can be symmetrically oriented about a reference element of the explosive combustor.

Description

[0001] Federal government-funded research

[0002] This invention was made with government support under contract number FA8650-19-D-2507 granted by the U.S. Air Force and the U.S. Navy. The U.S. government may hold certain rights to this invention. Technical Field

[0003] This disclosure generally relates to a knock combustion system for an engine (such as a turbine engine), and a method of operating the knock combustion system. More specifically, this disclosure generally relates to a knock combustion system. Background Technology

[0004] Combustion systems capable of operating under a wide range of operating conditions and heat load requirements are of interest in the art, such as those exhibiting good operating performance (including good combustion efficiency, good fuel consumption, and / or low emissions). There has been a growing interest in detonation combustion treatment in the art. Therefore, the art welcomes combustion systems constructed to perform detonation combustion treatment, including combustion systems that provide improved performance and / or the ability to operate under a wider range of operating conditions and heat load requirements. Attached Figure Description

[0005] The specification with reference to the accompanying drawings sets forth a complete and enabling disclosure for those skilled in the art, including its best mode, wherein:

[0006] Figure 1A A schematic cross-sectional view of an engine including a knock combustion system is shown;

[0007] Figure 1B A schematic cross-sectional view of an exemplary turbine engine including a knock combustion system is shown;

[0008] Figure 2 A schematic perspective view of an exemplary detonation combustion system is shown;

[0009] Figure 3A A schematic perspective view of an exemplary knock manifold that may be included in a knock combustion system is shown;

[0010] Figure 3B-3E They are shown respectively Figure 3A A schematic cross-sectional view of an exemplary detonation manifold;

[0011] Figure 4A A schematic perspective view of another exemplary knock manifold that may be included in a knock combustion system is shown;

[0012] Figure 4B-4E They are shown respectively Figure 4A A schematic cross-sectional view of an exemplary detonation manifold;

[0013] Figures 5A-5E An exemplary arrangement of detonation orifices that may be included in a detonation manifold is schematically depicted;

[0014] Figures 6A-6H Exemplary groupings and arrangements of detonation orifices that may be included in a detonation manifold are schematically depicted;

[0015] Figure 7 An exemplary control system that can be used to control a detonation combustion system is schematically depicted; and

[0016] Figure 8 A flowchart depicting an exemplary method for generating thrust is shown.

[0017] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0018] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Each example is provided as an explanation of the present disclosure and not as a limitation thereof. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present disclosure without departing from the scope or spirit thereof. For example, features shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations falling within the scope of the appended claims and their equivalents.

[0019] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0020] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0021] The terms “upper,” “lower,” “right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” “lateral,” “longitudinal,” etc., should be associated with this disclosure as they are oriented in the accompanying drawings. However, it should be understood that various alternative orientations may be assumed in this disclosure unless the opposite is explicitly stated. It should also be understood that the specific devices shown in the drawings and described in the following specification are merely exemplary embodiments of this disclosure. Therefore, the specific dimensions and other physical characteristics associated with the embodiments disclosed herein should not be considered limiting.

[0022] The terms "front" and "rear" refer to relative positions within a turbocharged engine, with "front" referring to the position closer to the engine inlet and "rear" referring to the position closer to the engine nozzle or exhaust port.

[0023] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0024] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0025] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to both direct connection, fixation, or attachment, and indirect connection, fixation, or attachment via one or more intermediate components or features.

[0026] As used throughout this specification and claims, approximate language is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by one or more terms such as “about,” “approximate,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to a margin of 1%, 2%, 4%, 10%, 15%, or 20%.

[0027] Throughout this specification and claims, scope limitations are combined and interchanged, and unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0028] Additionally, unless otherwise stated, the terms “low,” “high,” or their respective comparatives (e.g., lower, higher, where applicable) each refer to a relative speed within the engine. For example, a “low-pressure turbine” operates at pressures typically lower than a “high-pressure turbine.” Alternatively, unless otherwise stated, the above terms may be understood as their superlatives. For example, a “low-pressure turbine” may refer to the turbine with the lowest maximum pressure within the turbine section, and a “high-pressure turbine” may refer to the turbine with the highest maximum pressure within the turbine section.

[0029] The term "turbine" refers to a machine that includes a combustor section and a turbine section, the turbine section having one or more turbines that together generate thrust output and / or torque output. In some embodiments, the turbine may include a compressor section having one or more compressors that compress air or gas flowing to the combustor section.

[0030] As used herein, the term "turbo engine" refers to an engine that may include a turbine as a power source, in whole or in part. Examples of turbo engines include gas turbine engines and hybrid electric turbine engines, such as turbofan engines, turboprop engines, turbojet engines, turboshaft engines, etc.

[0031] One or more components of the engine described herein can be manufactured or formed using any suitable process, such as additive manufacturing or 3D printing. The use of such a process can allow such components to be integrally formed as a single, monolithic part, or formed as any suitable number of sub-parts. In particular, additive manufacturing processes can allow such components to be integrally formed and include a variety of features that are not possible using existing manufacturing methods. For example, the additive manufacturing methods described herein can allow the manufacture of unique features, constructions, thicknesses, materials, densities, fluid passages, manifolds and mounting structures, channels, conduits, cavities, openings, housings, manifolds, double walls, heat exchangers, or other components that are not possible or practical using existing manufacturing methods, or specific positioning and integration of such components. Some of these features are described herein.

[0032] Suitable additive manufacturing technologies according to this disclosure include, for example, selective laser melting (SLM), direct metal laser melting (DMLM), fused deposition modeling (FDM), selective laser sintering (SLS), 3D printing such as by inkjet, laser jetting and binder jetting, stereolithography (SLA), direct selective laser sintering (DSLS), electron beam sintering (EBS), electron beam melting (EBM), laser engineered net-shape (LENS), laser net-shape manufacturing (LNSM), direct metal deposition (DMD), digital light processing (DLP), direct selective laser melting (DSLM) and other known processes.

[0033] Suitable powder materials for manufacturing the structures provided herein as a single, monolithic structure include metal alloys, polymers, or ceramic powders. Exemplary metal powder materials are stainless steel alloys, cobalt-chromium alloys, aluminum alloys, titanium alloys, nickel-based superalloys, and cobalt-based superalloys. Furthermore, suitable alloys may include those designed to have good oxidation resistance, referred to as “superalloys,” which possess acceptable strength at elevated operating temperatures in turbine engines, such as Hastelloy, Inconel® alloys (e.g., IN 738, IN 792, IN 939), Rene alloys (e.g., Rene N4, Rene N5, Rene 80, Rene 142, Rene 195), Haynes alloys, Mar M, CM247, CM247 LC, C263, 718, X-850, ECY768, 282, X45, PWA 1483, and CMSX (e.g., CMSX-4) single-crystal alloys. The manufactured objects of this disclosure can be formed with one or more selected crystalline microstructures, such as directional solidification (“DS”) or single crystals (“SX”).

[0034] As used herein, the terms "monolithic," "single," or "integral" used to describe a structure refer to a structure formed integrally from a continuous material or group of materials without seams, joints, or other connections. The monolithic single structure described herein can be formed by additive manufacturing to have the structure, or alternatively by casting or the like.

[0035] This disclosure generally provides a combustion system configured to perform detonation combustion, and an engine including such a combustion system. Exemplary engines that can be configured to perform both detonation and detonation combustion include turbine engines, rocket engines, ramjet engines, or combinations thereof, such as turborocket engines, turboramjet engines, or rocket ramjet engines. Such a combustion system may include a detonation chamber configured to perform detonation combustion, and a detonation manifold configured to supply detonation fluid to the detonation chamber. The detonation manifold may include multiple separate detonation fluid paths, each configured to supply a different detonation fluid to the detonation chamber, and / or supply the detonation fluid to the detonation chamber with different fluid dynamics (e.g., volumetric flow rate, velocity, pressure, and / or pressure drop).

[0036] The currently disclosed detonation combustion system allows for a wider range of operating conditions and / or increased operational flexibility. For example, corresponding detonation fluid paths in a plurality of detonation fluid paths can be used for different operating conditions respectively. Each corresponding detonation fluid path can be in fluid communication with the detonation chamber via a plurality of detonation orifices disposed around the surface of a detonation manifold. The detonation orifices corresponding to the corresponding detonation fluid path can define a detonation orifice group. In some embodiments, the detonation combustion system may include a first detonation fluid path in fluid communication with the detonation chamber via a relatively small number of detonation orifices, for example, the first detonation fluid path being configured to operate at a lower flow rate, for example, to provide a lower thrust level. The detonation combustion system may include a second detonation fluid path in fluid communication with the detonation chamber via a relatively larger number of detonation orifices, for example, the second detonation fluid path being configured to operate at a higher flow rate, for example, to provide a higher thrust level.

[0037] In some embodiments, a plurality of detonation fluid paths and / or corresponding detonation orifice groups can be configured such that the flow rate of detonation fluid through a corresponding detonation fluid path is proportional to the number of detonation orifices in the corresponding detonation orifice group. For example, a corresponding detonation orifice group can be configured to provide detonation fluid through a corresponding detonation orifice under choke conditions.

[0038] In some embodiments, the detonation orifice may have a symmetrical orientation relative to a reference element of a detonation burner around which a plurality of detonation orifices are oriented. This symmetrical orientation can provide comparable and / or suitable hydrodynamics with respect to the detonation fluid introduced into the detonation chamber via a corresponding detonation fluid path, for example, since it may be desired and / or suitable for different operating conditions. Additionally or alternatively, the symmetrical orientation can provide comparable and / or suitable combustion dynamics (e.g., detonation dynamics) with respect to the detonation fluid introduced into the detonation chamber via a corresponding detonation fluid path, for example, since it may be desired and / or suitable for different operating conditions. The reference element of the detonation burner around which a plurality of detonation orifices may be oriented may include a reference element for the detonation chamber and / or a reference element for the detonation manifold.

[0039] As an example, a reference element for a knock burner may include a longitudinal axis of the knock chamber and / or knock manifold, a knock chamber wall circumferentially surrounding the longitudinal axis of the knock chamber, a knock manifold wall circumferentially surrounding the longitudinal axis of the knock manifold, an annular midplane, and / or a meridian located at a longitudinal position along the longitudinal axis, the meridian defining the periphery of at least one of the following: the knock chamber wall, the knock manifold wall, and the annular midplane. As used herein with reference to knock burners, the term "annular midplane" refers to one or more planes that are circumferentially surrounding the longitudinal axis of the knock chamber at a position corresponding to the volume center of the knock chamber and / or circumferentially surrounding the longitudinal axis of the knock manifold at a position corresponding to the volume center of the knock manifold. As an example, the annular midplane may include a cylindrical shape, an elliptical cylindrical shape, a curved shape, a polygonal shape, and combinations thereof. As an example, a meridian corresponding to such an annular midplane may include a circular line corresponding to the periphery of a cylindrical shape, an elliptical line corresponding to the periphery of an elliptical cylindrical shape, a curved line corresponding to the periphery of a curved cylindrical shape, or a polygonal line corresponding to the periphery of a polygonal shape.

[0040] By providing a symmetrical orientation of the detonation orifices within and / or between the respective detonation orifice groups, the operating variables associated with the location of the detonation fluid entering the detonation chamber can be normalized for multiple different operating conditions. Additionally or alternatively, such operating variables can be customized to suit different operating conditions. As an example, combustion dynamics may be affected by the location of the detonation fluid entering the detonation chamber with respect to one or more reference elements of the detonation chamber.

[0041] An exemplary knock manifold may include a plurality of knock orifices, which are symmetrically oriented relative to one or more such reference elements of a knock burner. As used herein with respect to a plurality of knock orifices, the term "symmetrical orientation" or "symmetrical orientation" means that a plurality of knock orifices that commonly define a geometric perimeter are symmetrical with respect to a reference element of a knock burner about which the plurality of knock orifices are oriented. As an example, the longitudinal axis of the knock chamber and / or the knock manifold, the knock chamber wall circumferentially surrounding the longitudinal axis of the knock chamber, the knock manifold wall circumferentially surrounding the longitudinal axis of the knock manifold, the annular midplane, and / or a meridian located at a longitudinal position along the longitudinal axis, the meridian defining the perimeter of at least one of the following: the knock chamber wall, the knock manifold wall, and the annular midplane. The plurality of knock orifices may be symmetrically adjacent to each other. As used herein with respect to a plurality of knock orifices, the term "symmetrically adjacent" means that a plurality of knock orifices that are respectively adjacent to each other and commonly define a geometric perimeter are symmetrically oriented relative to a reference element.

[0042] In some embodiments, the symmetrical orientation of the plurality of knock orifices may include an axisymmetric orientation. As used herein with respect to the plurality of knock orifices, the term "axisymmetric orientation" or "axisymmetric orientation" means that the plurality of knock orifices, which together define a geometric perimeter, are symmetrical with respect to an axis about which the plurality of knock orifices are oriented. For example, the axis about which the plurality of knock orifices are oriented may be the longitudinal axis of the knock chamber and / or the longitudinal axis of the knock manifold. The plurality of knock orifices may be axisymmetrically adjacent to each other. As used herein with respect to the plurality of knock orifices, the term "axisymmetrically adjacent" means that the plurality of knock orifices, which are adjacent to each other and together define a geometric perimeter, are axisymmetrically oriented with respect to a reference element of a knock burner about which the plurality of knock orifices are oriented.

[0043] In some embodiments, the symmetrical orientation of the plurality of knock orifices may include geometrical conformity of the plurality of knock orifices with respect to a reference element of a knock burner about which the plurality of knock orifices are oriented. As used herein with respect to the plurality of knock orifices, the term "geometric conformity" or "geometric alignment" means that the perimeter orientation of the geometric perimeter defined by the arrangement of the plurality of knock orifices coincides with the geometry of a reference element of a knock burner about which the plurality of knock orifices are oriented.

[0044] As an example, the circular geometric perimeter defined by multiple detonation orifices is geometrically consistent with the cylindrical annular midplane and the circular meridian of the cylindrical annular midplane. Furthermore, the circular geometric perimeter defined by the multiple detonation orifices is geometrically consistent with one or more detonation chamber walls defining a detonation chamber with a cylindrical structure and / or with one or more detonation manifold walls defining a detonation manifold with a cylindrical structure. As another example, the hexagonal geometric perimeter defined by multiple detonation orifices is geometrically consistent with the annular midplane having a hexagonal prism shape and the hexagonal meridian of the hexagonal annular midplane. Furthermore, the hexagonal geometric perimeter defined by the multiple detonation orifices is geometrically consistent with one or more detonation chamber walls defining a detonation chamber with a hexagonal prism shape and / or with one or more detonation manifold walls defining a detonation manifold with a hexagonal prism shape.

[0045] In some embodiments, a plurality of detonation orifices may be uniformly spaced around a geometric perimeter defined by the plurality of detonation orifices. This uniform spacing may depend at least in part on the construction of the geometric perimeter defined by the plurality of detonation orifices. In some embodiments, the plurality of detonation orifices may have a non-uniform spacing around the geometric perimeter defined by the plurality of detonation orifices. Additionally or alternatively, the plurality of detonation orifices may have a uniform spacing relative to one or more regions or portions of the geometric perimeter defined by the plurality of detonation orifices. For example, the spacing of the detonation orifices may differ between a first region or portion and a second region or portion of the geometric perimeter defined by the plurality of detonation orifices.

[0046] As used herein with respect to multiple knock orifices, the term "uniformly spaced" or "uniformly spaced apart" means that the knock orifices are uniformly spaced around a geometric perimeter defined by the multiple knock orifices, including equidistant and / or proportionally spaced knock orifices around such a geometric perimeter. As used herein with respect to multiple knock orifices, the term "equidistantly spaced" or "equidistantly spaced apart" means that the multiple knock orifices have equal perimeter distances between adjacent knock orifices. As an example, multiple knock orifices with equal spacing may collectively define a circular geometric perimeter with equal circumferential spacing between corresponding knock orifices. As used herein with respect to multiple knock orifices, the term "proportionally spaced" or "proportionally spaced apart" means that the multiple knock orifices have perimeter distances between adjacent knock orifices that are proportional to the distance between the corresponding knock orifice and the reference element of the knock burner around which the knock orifices are oriented. As an example, a plurality of detonation orifices with equal spacing can collectively define a geometric perimeter with an elliptical shape, wherein the arc length between corresponding detonation orifices is proportional to the radius of the geometric perimeter at corresponding positions between corresponding detonation orifices.

[0047] As used herein, the term "combustion" refers to an exothermic chemical reaction between fuel and oxidizer, producing combustion products and heat through the transformation of chemical substances. Engines can utilize the heat and kinetic energy generated by combustion to provide thrust. Typically, combustion can occur in one or both of two modes: detonation and knock. As used herein, the term "detonation" or "detonation combustion" refers to combustion that can be thermodynamically described as approximately isobaric. Typically, during a detonation combustion process, the pressure of the combustion products decreases slightly, and the specific volume of the combustion products increases significantly, generating a combustion wave with subsonic speeds. For example, the combustion wave generated by a detonation combustion process can have a speed of several meters per second (m / s) (e.g., from about 10 m / s to about 200 m / s). As used herein, the term "knock" or "knock combustion" refers to combustion that can be thermodynamically described as approximately isochoric. Typically, during a knock combustion process, the pressure and temperature of the combustion products increase abruptly, and the specific volume decreases slightly, generating a supersonic shock wave that immediately precedes the combustion wave, which also has supersonic speeds. For example, the combustion wave generated by detonation combustion treatment can have a speed of several kilometers per second (km / s) (e.g., about 1 km / s to about 6 km / s).

[0048] Compared to detonation, detonation typically offers faster heat release, lower entropy increase, and higher thermal efficiency. Exemplary detonation combustion processes can provide a pressure increase of approximately 5 to approximately 20 times. Further in contrast to detonation, detonation can propagate in lean fuel mixtures that result in relatively low NOx emissions. Detonation combustion has higher thermodynamic efficiency than detonation combustion, which translates into significantly improved specific impulse and / or specific fuel consumption. In some embodiments, gas turbine engines utilizing detonation combustion can have a reduced number of compressor stages and / or reduced compressor pressure requirements, attributed to, for example, the ability of detonation combustion to provide relatively large effective thrust at a relatively low overall compression ratio. Additionally or alternatively, detonation combustion can allow for engines with a higher thrust-to-weight ratio, which can allow for smaller, lighter engines for a given mission requirement. In an exemplary embodiment, the disclosed detonation combustion system can be configured to perform rotary detonation combustion. The rotary detonation combustion process can generate shock waves separately before the combustion wave propagating annularly through the detonation region of the detonation chamber. As the combustion products travel through the detonation chamber, the annularly propagating shock wave and combustion wave can be transformed into longitudinal waves.

[0049] Exemplary embodiments of this disclosure will now be described in further detail. References Figure 1A and Figure 1B An exemplary engine 50 including a knock combustion system 200 will be described. Figure 1A The engine 50 depicted can be any engine 50 including the detonation combustion system 200, such as a turbine engine, rocket engine, ramjet engine, or a combination thereof, such as a turbo-rocket engine, a turbo-ramjet engine, or a rocket-ramjet engine. As an example, Figure 1B An exemplary turbine engine 100 including a detonation combustion system 200 is shown. The exemplary engine 50 (e.g., turbine engine 100) can be mounted to an aircraft, for example, in an underwing configuration or a tail-mount configuration. Figure 1B The turbine engine 100 shown is provided as an example and not as a limitation, and the subject matter of this disclosure can be implemented with other suitable types of engines 50, including other suitable turbine engines 100.

[0050] For example, such as Figure 1AAs shown, an exemplary engine 50 may include an inlet section 52, a combustor section 54, and an outlet section 56 in a sequential flow relationship. The engine 50 may include an engine housing 58 that includes and / or defines at least a portion of the inlet section 52, the combustor section 54, and / or the outlet section 56. The inlet section 52 typically directs a flow of oxidant 60 (such as air or gas) to the combustor section 54. The inlet section 52 may compress the oxidant 60 before it enters the combustor section 54. For example, the inlet section 52 may define a reduced cross-sectional area leading downstream to the combustor section 54. At least a portion of the total oxidant 60 flow may be mixed with fuel 62 and may react in a combustion process to generate combustion products 64.

[0051] Exemplary oxidizer 60 may include air, oxygen, hydrogen peroxide, nitrogen tetroxide (dinitrogen tetroxide), nitric acid, anhydrous nitric oxide, and combinations thereof. In some embodiments, fuel 62 and oxidizer 60 may be combined to provide a self-igniting propellant. As used herein, the term "self-igniting propellant" refers to fuel 62 and oxidizer 60 spontaneously igniting when they come into contact with each other. As an example, a self-igniting propellant may include fuel 62, such as hydrazine, monomethylhydrazine, asymmetric dimethylhydrazine, triethylamine, dimethylamine, triethylborane, or triethylaluminum, and combinations thereof. Additionally or alternatively, a self-igniting propellant may include oxidizer 60, such as air, oxygen, hydrogen peroxide, nitrogen tetroxide (dinitrogen tetroxide), nitric acid, anhydrous nitric oxide, and combinations thereof.

[0052] Combustion section 54 may include a knock combustion system 200 constructed according to this disclosure. The knock combustion system 200 may include a knock burner 202 configured to perform knock combustion. In some embodiments, the knock burner 202 may be configured to perform both knock combustion and detonation combustion. For example, the knock burner 202 may switch from detonation to knock. Additionally or alternatively, the engine 50 may operate using detonation combustion to generate thrust before switching to knock. Combustion products 64 from combustor section 54 flow downstream to outlet section 56. In some embodiments, combustion products 64 may flow through turbine section 66 before entering outlet section 56. Turbine section 66 may include one or more turbine stages. In some embodiments, turbine section 66 may include a high-pressure turbine and / or a low-pressure turbine as described herein. Turbine section 66 may be disposed downstream of combustor section 54. Turbine section 66 may be located between combustor section 54 and outlet section 56. The outlet section 56 may typically define an increased cross-sectional area leading downstream of the combustor section 54 and / or downstream of the turbine section 66. In some embodiments, the turbine section 66 may define a portion of the outlet section 56. Additionally or alternatively, the outlet section 56 may include an outlet nozzle 68, etc. The expansion of the combustion products 64 typically provides thrust, which can be used as a direct power output in the form of thrust and / or for generating mechanical energy, for example, through the rotation of the turbine section 66.

[0053] like Figure 1B As shown, the engine 50, configured as a turbine engine 100, may include a fan section 102 and a core engine 104 disposed downstream of the fan section 102. The fan section 102 may include a fan 106 having any suitable configuration (e.g., variable pitch, single-stage configuration). The fan 106 may include a plurality of fan blades 108 spaced apart and coupled to a fan disk 110. The fan blades 108 may extend outward from the fan disk 110 in a generally radial direction. The core engine 104 may be directly or indirectly coupled to the fan section 102 to provide torque for driving the fan section 102.

[0054] The core engine 104 may include an engine housing 58 that surrounds one or more portions of the core engine 104, including a compressor section 114, a combustor section 54, and a turbine section 66. The engine housing 58 may define a core engine inlet 118, an outlet nozzle 68, and a core airflow path 122 between them. The core airflow path 122 may pass through the compressor section 114, combustor section 54, and turbine section 66 in a series flow relationship. The compressor section 114 may include one or more compressors, such as a first supercharger or LP compressor 124 and / or HP compressor 126. Each of the compressors may include one or more compressor stages. As an example, the compressor section 114, LP compressor 124, and / or HP compressor 126 may each have 1 to 16 compressor stages, such as 1 to 12 stages, 1 to 10 stages, 1 to 8 stages, 1 to 6 stages, or 1 to 4 stages. The turbine section 66 may include an HP turbine 128 and an LP turbine 130. The compressor section 114, burner section 54, turbine section 66, and outlet nozzle 68 can be arranged in a series flow relationship and can each define a portion of the core airflow path 122 through the core engine 104. In some embodiments, the inlet section 52 ( Figure 1A This may include at least a portion of the core engine inlet 118 and / or at least a portion of the compressor section 114. In some embodiments, the outlet section 56 ( Figure 1A It may include at least a portion of the outlet nozzle 68 and / or at least a portion of the turbine section 66.

[0055] The core motor 104 and fan section 102 can be coupled to a shaft driven by the core motor 104. As an example, such as... Figure 1B As shown, the core engine 104 may include a high-pressure (HP) shaft 132 and a low-pressure (LP) shaft 134. The HP shaft 132 can drive the HP turbine 128 to the HP compressor 126, and the LP shaft 134 can drive the LP turbine 130 to the LP compressor 124. In other embodiments, such as in the case of a turbine engine 100 including an intermediate-pressure turbine, the turbine engine 100 may have three shafts. The shafts of the core engine 104, together with the rotating portions of the core engine 104, may sometimes be referred to as "spools". The HP shaft 132, the rotating portion of the HP compressor 126 coupled to the HP shaft 132, and the rotating portion of the HP turbine 128 coupled to the HP shaft 132 may be collectively referred to as the high-pressure (HP) spool 136. The LP shaft 134, the rotating portion of the LP compressor 124 coupled to the LP shaft 134, and the rotating portion of the LP turbine 130 coupled to the LP shaft 134 may be collectively referred to as the low-pressure (LP) spool 138.

[0056] In some embodiments, fan section 102 can be directly connected to the shaft of core engine 104, for example, directly connected to LP shaft 134. Or, as Figure 1B As shown, fan section 102 and core engine 104 can be interconnected via a power gearbox 140 (e.g., a planetary reduction gearbox, a rotary gearbox, etc.). For example, power gearbox 140 can connect LP shaft 134 to fan 106, such as to fan disc 110 of fan section 102. Power gearbox 140 may include multiple gears for reducing the rotational speed of LP shaft 134 to a more efficient rotational speed for fan section 102.

[0057] Still referencing Figure 1B The fan section 102 of the turbine engine 100 may include a fan housing 142 that at least partially surrounds a fan 106 and / or a plurality of fan blades 108. The fan housing 142 may be supported by a core engine 104, for example by a plurality of outlet guide vanes 144 circumferentially spaced therebetween and extending substantially radially. The turbine engine 100 may include a nacelle 146. The nacelle 146 may be fixed to the fan housing 142. The nacelle 146 may include one or more sections that at least partially surround the fan section 102, the fan housing 142, and / or the core engine 104. For example, the nacelle 146 may include a nose cone, fan shroud, engine cowling, thrust reverser, etc. The inward portions of the fan housing 142 and / or the nacelle 146 may circumferentially surround the outward portions of the core engine 104. The inward portions of the fan housing 142 and / or the nacelle 146 may define a bypass passage 148. The bypass passage 148 may be arranged in a ring between the outer portion of the core engine 104 and the inner portion of the fan casing 142 and / or the nacelle 146 surrounding the outer portion of the core engine 104.

[0058] During operation of the turbine engine 100, inlet airflow 150 enters the turbine engine 100 through inlet 152 defined by nacelle 146 (e.g., the nose cone of nacelle 146). In some embodiments, inlet section 52 ( Figure 1AThe fan section 102 may include at least a portion of inlet 152, at least a portion of nacelle 146, and / or at least a portion of fan casing 142. Inlet airflow 150 passes through fan blades 108. Inlet airflow 150 is split into core airflow 154, which flows into and through core airflow path 122 of the core engine 104, and bypass airflow 156, which flows through bypass passage 148. Core airflow 154 is compressed by compressor section 114. The pressurized air from compressor section 114 flows downstream to combustor section 54, where fuel is introduced to generate combustion gases 158. Combustion gases 158 exit combustor section 54 and flow through turbine section 66, generating torque and / or thrust that rotates the compressor section to support combustion and also rotates the fan section 102. Rotation of fan section 102 causes bypass airflow 156 to flow through bypass passage 148, generating propulsive thrust. Core airflow exiting outlet nozzle 68 generates additional thrust.

[0059] In some exemplary embodiments, the turbine engine 100 may be a relatively high-power turbine engine 100, capable of generating a relatively large amount of thrust. For example, the turbine engine 100 may be configured to generate, for example, about 300 kN of thrust to about 700 kN of thrust at rated speed and / or at cruising speed, such as about 300 kN to about 500 kN of thrust, such as about 500 kN to about 620 kN of thrust, or such as about 620 kN to about 700 kN of thrust. In other embodiments, the turbine engine 100 may be configured to generate about 10 kN of thrust to about 300 kN of thrust, such as about 10 kN of thrust to about 50 kN of thrust, such as about 50 kN of thrust to about 150 kN of thrust, such as about 100 kN of thrust to about 300 kN of thrust, such as about 100 kN of thrust to about 200 kN of thrust. Reference Figure 1B The various features and properties of the turbine engine 100 described are provided by way of example only and are not limiting. In fact, this disclosure can be implemented for any desired turbine engine, including those turbine engines that have properties or features that differ from those of the turbine engine 100 described herein in one or more respects.

[0060] Now for reference Figure 2The exemplary detonation combustion system 200 is further described below. As shown, the detonation combustion system 200 may include a detonation burner 202. The detonation burner 202 may include one or more detonation chamber walls 204 defining a detonation chamber 206, within which detonation combustion may occur during operation of the detonation combustion system 200. Detonation combustion may include pulsed detonation combustion, continuous detonation combustion, and / or rotating detonation combustion. The detonation chamber 206 may be oriented relative to a longitudinal axis 250. The detonation chamber 206 may be circumferentially surrounding the longitudinal axis 250. The detonation chamber 206 may have an annular configuration, such as an elliptical annular configuration, a cylindrical annular configuration, or a polyhedral annular configuration. The detonation chamber may include an outward detonation chamber wall 204 and an inward detonation chamber wall 204. The outward and inward detonation chamber walls 204 may be coaxially oriented relative to the longitudinal axis 250. Other configurations are also contemplated. For example, the detonation chamber 206 may have a structure including a cylindrical structure, a polyhedral structure, a toroidal polyhedral structure, a truncated conical structure, a toroidal truncated conical structure, a polygonal structure or a toroidal polygonal structure, and combinations thereof.

[0061] The knock combustion system 200 may include a knock manifold 208 configured to supply knock fluid 209, such as fuel 62 and / or oxidizer 60, to a knock chamber 206. The knock manifold 208 may be oriented relative to a longitudinal axis 250. The knock manifold 208 may have a shape generally corresponding to the shape of the knock chamber 206. In some embodiments, the knock manifold 208 may have an annular configuration, such as an elliptical annular configuration, a circular annular configuration, or a polygonal annular configuration. Fuel 62 and oxidizer 60 may be mixed within the knock manifold 208. Additionally or alternatively, fuel 62 and oxidizer 60 may be mixed upstream of the knock manifold 208 and / or within the knock chamber 206. The knock manifold 208 may define a portion of a knock chamber wall 204. Additionally or alternatively, the knock manifold 208 may be coupled to one or more knock chamber walls 204. In some embodiments, the knock manifold 208 may be integrally integrated with one or more knock chamber walls 204. In some embodiments, one or more knock chamber walls 204 and knock manifolds 208 may define a single integral component. Additionally or alternatively, the knock manifold 208 may include multiple components, such as multiple integral components, that can be assembled or attached to each other, for example, by attaching hardware, welding, etc.

[0062] The knock combustion system 200 may include one or more knock manifold supply lines 210 in fluid communication with a knock manifold 208. The one or more knock manifold supply lines 210 may be configured to supply knock fluid 209, such as fuel 62 and / or oxidizer 60, to the knock manifold 208. The one or more knock manifold supply lines 210 may be coupled to the knock manifold 208. Additionally or alternatively, the one or more knock manifold supply lines 210 may be at least partially defined by the knock manifold 208, for example, by the overall structure of the knock manifold 208. Figure 2 As shown, the knock combustion system 200 may include multiple knock manifold supply lines 210, such as a first knock manifold supply line 212 and a second knock manifold supply line 214. The first knock manifold supply line 212 may be configured to supply a first knock fluid 211 to the knock manifold 208. The second knock manifold supply line 214 may be configured to supply a second knock fluid 213 to the knock manifold 208. Alternatively, or as an alternative to one or more knock manifold supply lines 210, the knock combustion system 200 may include one or more fuel supply lines 216 and / or one or more oxidizer supply lines 218. At least one fuel supply line 216 and / or at least one oxidizer supply line 218 may be in fluid communication with a corresponding knock manifold supply line 210. At least one fuel supply line 216 and / or at least one oxidizer supply line 218 may be coupled to a corresponding knock manifold supply line 210. Additionally or alternatively, at least one fuel supply line 216 and / or at least one oxidizer supply line 218 may define at least a portion of the corresponding knock manifold supply line 210. A first knock manifold supply line 212 may be configured to supply liquid and / or gaseous fuel 62 and / or oxidizer 60. A second knock manifold supply line 214 may be configured to supply liquid and / or gaseous fuel 62 and / or oxidizer 60. Additionally or alternatively, in some embodiments, the first knock manifold supply line 212 and / or the second knock manifold supply line 214 may be configured to supply coolant to the knock manifold 208. The coolant may include water, nitrogen, refrigerant, or oil, and combinations thereof. Coolant may be supplied to the knock manifold 208 during operation of the knock burner 202. Additionally or alternatively, coolant may be supplied to the knock manifold 208 to pre-condition the knock manifold and / or knock chamber 206 to a specific temperature.

[0063] In some embodiments, the first knock fluid 211 may include a first fuel 62 and / or a first oxidant 60. The second knock fluid 213 may include a second fuel 62 and / or a second oxidant 60. For example, during a particular operating state of the knock combustion system 200, the first knock fluid 211 and the second knock fluid 213 may be the same as or different from each other. For example, the first knock fluid 211 may include the first fuel 62 and the second knock fluid 213 may include the second fuel 62, and the first and second fuels 62 may have different compositions and / or different concentrations. Additionally or alternatively, the first knock fluid 211 may include the first oxidant 60 and the second knock fluid 213 may include the second oxidant 60, and the first and second oxidants 60 may have different compositions and / or different concentrations. Additionally or alternatively, for example, during a particular operating state of the knock combustion system 200, the first knock fluid 211 and the second knock fluid 213 may include the same fuel 62 and / or the same oxidant 60. For example, when the first detonation fluid 211 and the second detonation fluid 213 contain the same fuel 62 and / or the same oxidant 60, the concentrations of the fuel 62 and / or the oxidant 60 may be the same or different between the first detonation fluid 211 and the second detonation fluid 213.

[0064] The knock manifold 208 may include a plurality of knock orifices 220 through which knock fluids 209 (such as fuel 62 and / or oxidizer 60) can be supplied to the knock chamber 206. The plurality of knock orifices 220 may be at least partially defined by the structure of the knock manifold 208 (e.g., by the overall structure of the knock manifold 208). The plurality of knock orifices 220 may be configured to provide fluid communication between a corresponding knock manifold supply line 210 and the knock chamber 206. One or more knock fluids 209 (e.g., one or more types of fuel 62 and / or one or more types of oxidizer 60) may mix with each other within and / or upstream of the knock manifold 208 (e.g., within a corresponding knock manifold supply line 210). Additionally or alternatively, one or more knock fluids 209 may mix with each other within the knock chamber 206.

[0065] In some embodiments, the detonation manifold 208 may include a plurality of detonation fluid paths 201, each configured to supply a corresponding detonation fluid 209 to the detonation chamber 206. The respective detonation fluid paths 201 may be defined by the structure of the detonation manifold 208 (e.g., the overall structure of the detonation manifold 208). A corresponding detonation fluid path among the plurality of detonation fluid paths 201 may be configured to provide fluid communication between one or more detonation manifold supply lines 210 and the detonation chamber 206 via a plurality of detonation orifices 220 corresponding to a corresponding one of the plurality of detonation orifice groups 203. The respective detonation fluid paths 201 may be fluidly isolated from each other. The respective detonation fluid paths 201 may be configured to supply different detonation fluids 209 to the detonation chamber 206, and / or to supply one or more detonation fluids 209 to the detonation chamber 206 with one or more different fluid dynamics (e.g., volumetric flow rate, velocity, pressure, and / or pressure drop across the plurality of detonation orifices 220 in the respective detonation orifice group 203).

[0066] For example, such as Figure 2 As shown, the detonation manifold 208 may include a first detonation fluid path 205, which is in fluid communication with the detonation chamber 206 via a first detonation orifice group 222 including a plurality of first detonation orifices 220. Additionally or alternatively, the detonation manifold 208 may include a second detonation fluid path 207, which is in fluid communication with the detonation chamber 206 via a second detonation orifice group 224 including a plurality of second detonation orifices 220. The first detonation fluid path 205 may be configured to supply a first detonation fluid 211 to the detonation chamber 206. The first detonation fluid path 205 may include a first detonation manifold supply line 212 and / or may be in fluid communication with the first detonation manifold supply line 212. The second detonation fluid path 207 may be configured to supply a second detonation fluid 213 to the detonation chamber 206. The second knock fluid path 207 may include a second knock manifold supply line 214 and / or may be in fluid communication with the second knock manifold supply line 214. In some embodiments, the first knock fluid path 205 and the second knock fluid path 207 may each be defined by an integral structure of the knock manifold 208 (e.g., by a single integral component defining the knock manifold 208). Additionally or alternatively, the first knock fluid path 205 may be defined by a first component (e.g., a first integral component), and the second knock fluid path 207 may be defined by a second component (e.g., a second integral component). The first integral component and the second integral component may be assembled or attached to each other, for example, by attachment hardware, welding, etc.

[0067] In some embodiments, one or more of the plurality of detonation fluid paths 201 may be used individually or simultaneously, for example, depending on the operating state of the detonation combustion system 200. For example, a first detonation fluid path 205 may be used during a first operating state to supply first detonation fluid 211 to the detonation chamber 206, for example, through a plurality of first detonation orifices 220 in a first detonation orifice group 222. Additionally or alternatively, a second detonation fluid path 207 may be used during a second operating state to supply second detonation fluid 213 to the detonation chamber 206, for example, through a plurality of second detonation orifices 220 in a second detonation orifice group 224. Additionally or alternatively, the first detonation fluid path 205 and the second detonation fluid path 207 may be used simultaneously, for example, during a third operating state.

[0068] Additionally or alternatively, in some embodiments, the first knock fluid path 205 may be configured to supply first knock fluid 211 to the knock chamber 206 at a first flow rate through a plurality of knock orifices 220 in the first knock orifice group 222, and the second knock fluid path 207 may be configured to supply second knock fluid 213 to the knock chamber 206 at a second flow rate through a plurality of knock orifices 220 in the second knock orifice group 224. For example, the first flow rate and the second flow rate may be the same as or different from each other during a particular operating state of the knock combustion system 200. Additionally or alternatively, in some embodiments, the first knock fluid path 205 may be configured to supply first knock fluid 211 to the knock chamber 206 with a first pressure drop across the first knock orifice group 222, and the second knock fluid path 207 may be configured to supply second knock fluid 213 to the knock chamber 206 with a second pressure drop across a plurality of second knock orifice groups 224. For example, during a specific operating state of the detonation combustion system 200, the first pressure drop and the second pressure drop may be the same as or different from each other.

[0069] The knock combustion system 200 may include a control system 226 configured to control the operation of the knock burner 202. The knock combustion system 200 may include one or more control valves configured to control the flow of knock fluid 209 (e.g., fuel 62 and / or oxidizer 60) to the knock manifold 208, such as the flow of knock fluid 209 to a corresponding knock fluid path 201. The one or more control valves may be opened, closed, and / or modulated at least in part based on control commands generated by the control system 226. In some embodiments, the knock combustion system 200 may include one or more knock manifold supply valves 228 configured to control the flow of knock fluid 209 (e.g., fuel 62 and / or oxidizer 60) to the knock manifold 208, such as the flow of knock fluid 209 to a corresponding knock fluid path 201. Figure 2As shown, the detonation combustion system 200 may include a first detonation manifold supply valve 230 configured to control the flow of detonation fluid 209 to a first detonation fluid path 205, and a second detonation manifold supply valve 232 configured to control the flow of detonation fluid 209 to a second detonation fluid path 207.

[0070] Additionally or alternatively, the knock combustion system 200 may include one or more fuel supply valves 234 configured to control the flow of fuel 62 to one or more knock manifold supply lines 210 and / or to corresponding knock fluid paths 201. Figure 2 As shown, the knock combustion system 200 may include a first fuel supply valve 236 configured to control the flow of fuel 62 to a first knock fluid path 205, and a second fuel supply valve 238 configured to control the flow of fuel 62 to a second knock fluid path 207. Additionally or alternatively, the knock combustion system 200 may include one or more oxidizer supply valves 240 configured to control the flow of oxidizer 60 to one or more knock manifold supply lines 210 and / or to a corresponding knock fluid path 201. Figure 2 As shown, the detonation combustion system 200 may include a first oxidizer supply valve 242 configured to control the flow of oxidizer 60 to a first detonation fluid path 205, and a second oxidizer supply valve 244 configured to control the flow of oxidizer 60 to a second detonation fluid path 207.

[0071] When the detonation fluid 209 (such as fuel 62 and / or oxidizer 60) flows through multiple detonation orifices 220 in the corresponding detonation orifice group 203, detonation can occur under suitable operating conditions to generate combustion products 64. Figure 2 As shown, the detonation wave 246 preceding the shock wave 248 can propagate annularly through the detonation chamber 206. As illustrated, the shock wave 248 and the corresponding detonation wave 246 can propagate counterclockwise, while the combustion products 64 typically expand in three dimensions. Alternatively, the shock wave 248 and the corresponding detonation wave 246 can propagate clockwise. Although for illustrative purposes... Figure 2 The diagram depicts a shock wave 248 and a corresponding detonation wave 246, but the exemplary detonation burner 202 can be configured to continuously generate multiple shock waves 248 and corresponding detonation waves 246. For example, multiple shock waves 248 and corresponding detonation waves 246 can propagate simultaneously around the annular volume of the detonation chamber 206, for example, in a circumferentially spaced relationship. Although in Figure 2The detonation chamber 206, schematically shown, has a generally cylindrical annular shape; however, the detonation chamber 206 can include any shape that provides a continuous path for the shock wave 248 and the corresponding detonation wave 246 to follow. As an example, the detonation chamber 206 can include a toroidal shape, a trapezoidal shape, or an elliptical shape. The shock wave 248 and the corresponding detonation wave 246 can surround all or part of the annular perimeter defined by the detonation chamber 206.

[0072] like Figure 2 As shown, the region preceding the shock wave 248 and the corresponding detonation wave 246 may include a mixture of fuel 62 and oxidizer 60 at a concentration suitable for detonation. As the mixture of fuel 62 and oxidizer 60 detonates, the shock wave 248 generated by the detonation can temporarily prevent further fuel 62 and oxidizer 60 from entering the detonation chamber 206. The shock wave 248 and the corresponding detonation wave 246 can propagate around the annular volume of the detonation chamber 206, further consuming fuel 62 and oxidizer 60. As the shock wave 248 and the corresponding detonation wave 246 propagate around the annular volume, additional fuel 62 and oxidizer 60 can generally follow the shock wave 248 and the corresponding detonation wave 246 into the detonation chamber 206.

[0073] As the combustion products 64 expand as they propagate through the detonation chamber 206, at least a portion of the shock wave 248 can propagate out of the detonation chamber 206, thereby providing thrust. In some embodiments, as the shock wave 248 propagates through and / or out of the detonation chamber 206, the shock wave 248 can change from a generally rotational propagation direction to a helical or longitudinal propagation direction. In some embodiments, a longitudinal shock wave 248 can be generated that propagates through and / or out of the detonation chamber 206. The shock wave 248 (e.g., a longitudinal shock wave 248 propagating through and / or out of the detonation chamber 206) can surround at least a portion of the circumference of the detonation chamber 206. Although for illustrative purposes... Figure 2 A longitudinal shock wave 248 is depicted, but the exemplary detonation combustor 202 can be configured to continuously generate multiple longitudinal shock waves 248. For example, the multiple longitudinal shock waves 248 can propagate longitudinally from the detonation chamber 206 simultaneously, for example, in a circumferentially spaced relationship and / or at a detonation frequency. Additionally or alternatively, the multiple longitudinal shock waves 248 can have an annular configuration. The shock waves 248 can propagate into one or more turbine sections 66 of the engine 50, generate thrust through the engine outlet section 56, and / or through the engine outlet nozzle 68.

[0074] In some embodiments, the detonation burner 202 may include a pre-detonation device 252 configured to generate an explosion wave 254 suitable for initiating detonation within the detonation chamber 206. In some embodiments, detonation may be performed in the detonation chamber 206 prior to initiating detonation within the detonation chamber 206. For example, the detonation chamber 206 may be used for detonation during certain operating conditions. Detonation may be performed within the detonation chamber 206 by providing a fuel 62 and oxidizer 60 suitable for detonation (e.g., a mixture of fuel 62 and oxidizer 60 unsuitable for detonation).

[0075] Still referencing Figure 2 The detonation burner 202 may have an annular central plane 215. The annular central plane 215 may be circumferentially surrounding the longitudinal axis 250 of the detonation chamber 206 and / or the detonation manifold 208. The annular central plane 215 may be oriented parallel to the longitudinal axis 250. The annular central plane 215 may be circumferentially surrounding the longitudinal axis 250. The annular central plane 215 may be coaxially oriented relative to the longitudinal axis 250. For a detonation chamber 206 having an annular configuration, for example... Figure 2 As shown, the annular midplane 215 can be coaxially positioned relative to the outward detonation chamber wall 204 and / or the inward detonation chamber wall 204, for example, equidistantly positioned with respect to the outward detonation chamber wall 204 and the inward detonation chamber wall 204. In some embodiments, the annular midplane 215 can be equidistantly located between the outward detonation chamber wall 204 and the longitudinal axis 250. The annular midplane 215 can generally have a shape that coincides with the shape of the detonation chamber 206 and / or the detonation manifold 208. For example, as Figure 2 As shown, the detonation chamber 206 and / or detonation manifold 208, having an annular elliptical or cylindrical structure, may have an annular midplane 215 with a corresponding annular or cylindrical shape. The detonation chamber 206 and / or detonation manifold 208, having an annular polyhedral structure, may also have an annular midplane 215 with a corresponding polyhedral shape. The detonation manifold 208 may be coaxially oriented relative to the annular midplane 215 of the detonation chamber 206. The annular midplane 215 may include a meridian 217. The meridian 217 may be located longitudinally along the longitudinal axis 250, and the meridian 217 defines the periphery of at least one of the following: the detonation chamber wall 204, the detonation manifold wall 350, and the annular midplane 215.

[0076] For example, as shown, meridian 217 defines the periphery of annular midplane 215. In some embodiments, annular midplane 215 may include a cylindrical shape, an elliptical cylindrical shape, a curved shape, a polygonal shape, and combinations thereof. In some embodiments, meridian 217 corresponding to such annular midplane 215 may include a circular line corresponding to the periphery of a cylindrical shape, an elliptical line corresponding to the periphery of an elliptical cylindrical shape, a curved line corresponding to the periphery of a curved cylindrical shape, or a polygonal line corresponding to the periphery of a polygonal shape.

[0077] In some embodiments, the plurality of detonation orifices 220 may have a symmetrical and / or axisymmetric orientation relative to the meridian 217. For example, the first detonation orifice group 222 and the second detonation orifice group 224 may have a symmetrical and / or axisymmetric orientation relative to the meridian 217. The symmetrical and / or axisymmetric orientation of the plurality of detonation orifices 220 may include a plurality of detonation orifices 220 equidistant from the meridian 217. In some embodiments, the meridian 217 may intersect with the plurality of detonation orifices 220. Additionally or alternatively, the plurality of detonation orifices 220 may be equidistant from the meridian 217. Additionally or alternatively, the plurality of detonation orifices 220 may be coaxially oriented relative to the meridian 217 at a common coaxial plane. The common coaxial plane may coincide with the annular midplane 215. For example, the common coaxial plane may be aligned with the annular midplane 215, or the common coaxial plane may be coaxially inward or coaxially outward from the annular midplane 215.

[0078] Additionally or alternatively, the symmetrical and / or axisymmetric orientation of the plurality of detonation orifices 220 may include a plurality of detonation orifices 220 equidistant from one or more detonation chamber walls 204 (e.g., outward detonation chamber walls 204 and / or inward detonation chamber walls 204). For example, a first detonation orifice group 222 and a second detonation orifice group 224 may be equidistantly offset from one or more detonation chamber walls 204. Additionally or alternatively, the plurality of detonation orifices 220 may be coaxially oriented relative to one or more detonation chamber walls 204 in a common coaxial plane. Furthermore, or as an alternative to a plurality of detonation orifices 220 having a symmetrical orientation relative to meridian 217 and / or relative to one or more detonation chamber walls 204, the plurality of detonation orifices 220 may have an axisymmetric orientation relative to longitudinal axis 250. Additionally or alternatively, the plurality of detonation orifices 220 may be equidistantly offset from longitudinal axis 250.

[0079] In some embodiments, the plurality of detonation orifices 220 may have a perimeter orientation, for example, relative to a longitudinal axis 250, which is geometrically consistent with the shape of a meridian 217. The perimeter orientation of the plurality of detonation orifices 220 may collectively define a shape that is geometrically consistent with the shape of the meridian 217. The area of ​​the geometric perimeter 301 collectively defined by the arrangement of the plurality of detonation orifices 220 may be equal to, greater than or less than the area defined by the meridian 217.

[0080] Now for reference Figures 3A-3E and Figures 4A-4E The exemplary knock manifold 208 is further described below. The knock manifold 208 may be oriented relative to a longitudinal axis 250. For example... Figure 3A and Figure 4AAs shown, the detonation manifold 208 may have a circumferential annular structure surrounding the longitudinal axis 250. For example, the detonation manifold 208 may have an annular elliptical structure, an annular cylindrical structure, or an annular polyhedral structure. The detonation manifold 208 may include a plurality of detonation manifold walls 350, such as an outward annular detonation manifold wall 352, an inward annular detonation manifold wall 354, a proximal detonation manifold wall 356 located near the proximal end of the detonation chamber 206, and a distal detonation manifold wall 358 located far from the distal end of the detonation chamber 206. The detonation manifold 208 may include a plurality of detonation orifices 220 disposed around the manifold surface 300 of the detonation manifold 208, such as a plurality of detonation orifices 220 defining a first detonation orifice group 222 and / or a plurality of detonation orifices 220 defining a second detonation orifice group 224. The detonation manifold 208 may include a plurality of manifold conduits 302, which are defined by a structure (such as the overall structure of the detonation manifold 208) or otherwise disposed within the detonation manifold 208. The plurality of manifold conduits 302 may each define at least a portion of a corresponding one of a plurality of detonation fluid paths 201. A corresponding manifold conduit among the plurality of manifold conduits 302 may be configured to supply detonation fluid 209 to a corresponding one of a plurality of detonation orifice groups 203. The corresponding manifold conduits 302 may be fluidly isolated from each other, for example, by the overall structure of the detonation manifold 208.

[0081] like Figures 3A-3E and Figures 4A-4E As shown, the detonation manifold 208 may include a first manifold conduit 304 defined by a structure (such as the overall structure of the detonation manifold 208) and a second manifold conduit 306 defined by a structure (such as the overall structure of the detonation manifold 208). The first manifold conduit 304 may be at least partially defined by one or more first conduit walls 308. The first manifold conduit 304 may define at least a portion of a first detonation fluid path 205. The first manifold conduit 304 may be configured to pass through a first detonation orifice group 222 including a plurality of first detonation orifices 220 (e.g., through a first detonation manifold supply line 212). Figure 2 (Fluid communication) supplies the first detonation fluid 211 to the detonation chamber 206. The second manifold duct 306 may be at least partially defined by one or more second duct walls 310. The second manifold duct 306 may define at least a portion of the second detonation fluid path 207. The second manifold duct 306 may be configured to pass through a second detonation orifice group 224 including a plurality of second detonation orifices 220 (e.g., through a second detonation manifold supply line 214). Figure 2 (Fluid communication) supplies the second detonation fluid 213 to the detonation chamber 206. The first manifold duct 304 and the second manifold duct 306 may be fluidly isolated from each other, for example, by the overall structure of the detonation manifold 208 (e.g., by one or more first duct walls 308 and / or one or more second duct walls 310).

[0082] The manifold surface 300, including a plurality of detonation orifices 220, can have any desired orientation relative to the longitudinal axis 250. Additionally or alternatively, the plurality of detonation orifices 220 can have any desired orientation relative to the longitudinal axis 250, such as an orientation different from that of the manifold surface 300. The orientation of the manifold surface 300 and / or the plurality of detonation orifices 220 can be selected at least in part based on the desired discharge direction of the detonation fluid 209 flowing into the detonation chamber 206 from the plurality of detonation orifices 220. A plurality of detonation orifice groups 203 can coexist on the manifold surface 300. As shown, by way of example, the manifold surface 300 including the plurality of detonation orifices 220 can be oriented substantially perpendicular to the longitudinal axis 250, and the plurality of detonation orifices 220 can be oriented substantially parallel to the longitudinal axis 250. As shown, the manifold surface 300 including the plurality of detonation orifices 220 can define a radial plane relative to the longitudinal axis 250. Additionally or alternatively, the detonation manifold 208 may include a manifold surface 300 oriented generally parallel to the longitudinal axis 250, having a plurality of detonation orifices 220 oriented generally perpendicular to the longitudinal axis 250. Additionally or alternatively, the plurality of detonation orifices 220 may be located on the manifold surface 300 oriented obliquely to the longitudinal axis 250. The plurality of detonation orifices 220 may be oriented parallel to, perpendicular to, or oblique to the longitudinal axis 250. In some embodiments, the manifold surface 300 including the plurality of detonation orifices 220 may have an inward annular orientation relative to the longitudinal axis 250. Additionally or alternatively, the manifold surface 300 including the plurality of detonation orifices 220 may have an outward annular orientation relative to the longitudinal axis 250. Such a manifold surface 300 having an inward or outward annular orientation may define a tangential plane relative to the longitudinal axis 250.

[0083] For example, such as Figure 3A and Figure 4A As shown, the multiple detonation orifices 220 can be symmetrically oriented relative to the meridian 217 circumferentially surrounding the longitudinal axis 250. Further reference... Figure 2 , Figure 3A and Figure 4A The plurality of detonation orifices 220 shown, including a first detonation orifice group 222 and a second detonation orifice group 224, are symmetrically oriented relative to the inward detonation chamber wall 204 and the outward detonation chamber wall 204. The detonation manifold 208 can be connected to one or more detonation chamber walls 204 via a plurality of attachment points 312. Figure 2 As shown in the figure, multiple attachment points 312 are coaxially positioned relative to the meridian 217 and multiple detonation orifices 220. For example, the multiple detonation orifices 220 may have a symmetrical orientation relative to one or more detonation chamber walls 204 to which the detonation manifold 208 can be connected.

[0084] For example, such as Figure 3A and Figure 4A As further shown, the plurality of detonation orifices 220 may have an axisymmetric orientation relative to the longitudinal axis 250. As shown, the plurality of detonation orifices 220 may be equidistant from the meridian 217. In some embodiments, the meridian 217 may intersect the plurality of detonation orifices 220. As shown, the plurality of detonation orifices 220 may be equidistant from the meridian 217. Also as shown, the plurality of detonation orifices 220 may be coaxially oriented relative to the meridian 217 in a common coaxial plane. Figure 3A and Figure 4A The common coaxial plane shown is coaxially positioned inside meridian 217. In other embodiments, the common coaxial plane may be aligned with meridian 217, or it may be coaxially positioned outside meridian 217.

[0085] like Figures 3A-3E and Figures 4A-4E As shown, multiple detonation orifices 220 can be arranged to be symmetrically adjacent and / or axially symmetrically adjacent to each other. At least some detonation orifices 220 corresponding to the first detonation orifice group 222 can be symmetrically adjacent and / or axially symmetrically adjacent to corresponding detonation orifices 220 in the second detonation orifice group 224. Additionally or alternatively, at least some detonation orifices 220 corresponding to the first detonation orifice group 222 can be symmetrically adjacent and / or axially symmetrically adjacent to each other, and / or at least some detonation orifices 220 corresponding to the second detonation orifice group 224 can be symmetrically adjacent and / or axially symmetrically adjacent to each other.

[0086] For example, such as Figures 3A-3E As shown, a plurality of detonation orifices 220 having a symmetrical and / or axisymmetric orientation may include a plurality of first detonation orifices 220 of a first detonation orifice group 222 that are symmetrically and / or axisymmetrically adjacent to corresponding second detonation orifices 220 in a plurality of second detonation orifices 220 of ... Additionally or alternatively, for example, one or more detonation orifices 220 in the first detonation orifice group 222 may be disposed adjacent to each other, and at least some of the detonation orifices 220 in the second detonation orifice group 224 may be symmetrically adjacent to each other and / or axially symmetrically adjacent to each other.

[0087] For example, such as Figures 4A-4E As shown, a plurality of detonation orifices 220 having a symmetrical orientation and / or an axisymmetric orientation may include a plurality of detonation orifices 220 of a first detonation orifice group 222 coaxially oriented relative to corresponding detonation orifices in a plurality of detonation orifices 220 of a plurality of detonation orifices 220 of a plurality of detonation orifices 220 of a plurality of detonation orifices 220. The coaxial orientation of the plurality of detonation orifices 220 may include at least some detonation orifices 220 of a first detonation orifice group 222 circumferentially surrounding corresponding detonation orifices 220 of a second detonation orifice group 224. Additionally or alternatively, the coaxial orientation may include at least some detonation orifices 220 of a second detonation orifice group 224 circumferentially surrounding corresponding detonation orifices 220 of a first detonation orifice group 222. In addition to the detonation orifices 220 being coaxially oriented relative to each other, as Figures 4A-4E As shown, the first detonation orifice group 222 and the second detonation orifice group 224 may include a plurality of detonation orifices 220 oriented in an alternating sequence (e.g., an alternating sequence in which at least some detonation orifices 220 in the first detonation orifice group 222 are symmetrically adjacent and / or axially adjacent to detonation orifices 220 in the second detonation orifice group 224). Additionally or alternatively, the coaxially oriented plurality of detonation orifices 220 may include at least some detonation orifices 220 in the first detonation orifice group 222 that are symmetrically adjacent and / or axially adjacent to each other, and / or at least some detonation orifices 220 in the second detonation orifice group 224 that are symmetrically adjacent and / or axially adjacent to each other. For example, at least some of the detonation orifices 220 in the first detonation orifice group 222 may circumferentially surround a corresponding detonation orifice 220 in the second detonation orifice group 224, and may be symmetrically adjacent and / or axially symmetrically adjacent to a corresponding detonation orifice 220 in the first detonation orifice group 222 and / or another detonation orifice 220 in the second detonation orifice group 224. As another example, at least some of the detonation orifices 220 in the second detonation orifice group 224 may circumferentially surround a corresponding detonation orifice 220 in the first detonation orifice group 222, and may be symmetrically adjacent and / or axially symmetrically adjacent to a corresponding detonation orifice 220 in the second detonation orifice group 224 and / or another detonation orifice 220 in the first detonation orifice group 222. Alternatively or additionally, a plurality of detonation orifices 220 in a first detonation orifice group 222, which are circumferentially surrounded by detonation orifices 220 of the second detonation orifice group 224, may be symmetrically adjacent and / or axially symmetrically adjacent to another detonation orifice 220 in the first detonation orifice group 222. Alternatively or additionally, a plurality of detonation orifices 220 in a second detonation orifice group 224, which are circumferentially surrounded by detonation orifices 220 of the first detonation orifice group 222, may be symmetrically adjacent and / or axially symmetrically adjacent to another detonation orifice 220 in the second detonation orifice group 224.

[0088] For example, such as Figure 3A and Figure 4AAs shown, a plurality of detonation orifices 220 may be circumferentially surrounding the longitudinal axis 250 at radial distances equidistant from the longitudinal axis 250. The plurality of detonation orifices 220 may collectively define a geometric perimeter 301. For example, as shown, the plurality of detonation orifices 220 may collectively define a geometric perimeter 301 having an elliptical shape (e.g., a circular shape). As shown, the area of ​​the geometric perimeter 301 defined by the plurality of detonation orifices 220 is slightly smaller than the area defined by the meridian 217. In other embodiments, the geometric perimeter 301 defined by the plurality of detonation orifices 220 may be equal to or larger than the area defined by the meridian 217. As shown, the geometric perimeter 301 defined by the plurality of detonation orifices 220 has geometrical consistency with the circular shape of the meridian 217. Further reference is also made to... Figure 2 The multiple detonation orifices 220 have geometrical consistency with the elliptical or cylindrical shape of the annular central plane 215, and with the elliptical or cylindrical shape of the inward and outward detonation chamber walls 204.

[0089] Still referencing Figure 3A and Figure 4A Adjacent detonation orifices 220 in a plurality of detonation orifices 220 may be uniformly spaced around a geometric perimeter 301 defined by the plurality of detonation orifices 220. The uniformly spaced detonation orifices 220 may be spaced apart by perimeter intervals (e.g., intra-group perimeter intervals 303 between adjacent detonation orifices 220 in a corresponding detonation group, and / or inter-group perimeter intervals 305 between adjacent detonation orifices 220 from different detonation orifice groups). For example, at least some detonation orifices 220 in a first detonation orifice group 222 may be uniformly spaced apart by a first intra-group perimeter interval 307. Additionally or alternatively, at least some detonation orifices 220 in a second detonation orifice group 224 may be uniformly spaced apart by a second intra-group perimeter interval 309. Alternatively or additionally, at least some of the detonation holes 220 in the first detonation hole group 222 may be uniformly spaced from adjacent detonation holes 220 in the second detonation hole group 224 by an inter-group perimeter spacing 305. The intra-group perimeter spacing 303 may be the same or different between corresponding detonation hole groups. For example, the intra-group perimeter spacing 307 and the intra-group perimeter spacing 309 may be the same or different from each other. Alternatively or additionally, the inter-group perimeter spacing 305 may be the same or different between pairs of detonation hole groups.

[0090] In some embodiments, the uniformly spaced detonation orifices 220 may have equidistant spacing. Additionally or alternatively, in some embodiments, the uniformly spaced detonation orifices 220 may have proportional spacing. As an example, such as Figure 3A and Figure 4AAs shown, a plurality of knock orifices 220 are uniformly spaced circumferentially around an elliptical periphery (e.g., a circular periphery). Additionally or alternatively, the plurality of knock orifices 220 may be uniformly spaced circumferentially around an elliptical periphery at a proportional interval. In some embodiments, this proportional interval may be proportional to the distance of each knock orifice 220 from a reference element of the knock burner around which the plurality of knock orifices are oriented. The reference element may include a longitudinal axis 250 of the knock chamber 206 and / or the knock manifold 208, a knock chamber wall 204 circumferentially surrounding the longitudinal axis 250 of the knock chamber 206, a knock manifold wall circumferentially surrounding the longitudinal axis 250 of the knock manifold 208, an annular midplane 215, and / or a meridian 217 located at a longitudinal position along the longitudinal axis 250, the meridian 217 defining the periphery of at least one of the following: the knock chamber wall 204, the knock manifold wall, and the annular midplane 215.

[0091] For example, a plurality of detonation orifices 220 may be uniformly spaced around an elliptical perimeter at a proportional circumferential interval (e.g., proportional to the radial distance between the respective detonation orifice 220 and the longitudinal axis 250, proportional to the radial distance between the meridian 217 and the longitudinal axis 250, and / or proportional to the radial distance between the detonation chamber wall 204 and the longitudinal axis 250). As another example, a plurality of detonation orifices 220 may be uniformly spaced around a linear or curved portion of a geometric perimeter 301 defined by the respective detonation orifices among the plurality of detonation orifices 220, wherein the proportional spacing between the respective detonation orifices among the plurality of detonation orifices 220 is related to the distance between the respective detonation orifice 220 and at least one of the following: the longitudinal axis 250, the meridian 217, and the detonation chamber wall 204. Additionally or alternatively, the plurality of detonation orifices 220 may be uniformly spaced around a linear or curved portion of a perimeter defined by the respective detonation orifices among the plurality of detonation orifices 220, wherein the proportional spacing between the respective detonation orifices among the plurality of detonation orifices 220 is related to the linear distance between the respective detonation orifice 220 and the longitudinal axis 250, the linear distance between the meridian 217 and the longitudinal axis 250, and / or the linear distance between the detonation chamber wall 204 and the longitudinal axis 250.

[0092] Still referencing Figures 3A-3E and Figures 4A-4EIn some embodiments, a respective manifold among the plurality of manifolds 302 may include a distribution chamber 314 defined by the overall structure of the detonation manifold 208 or otherwise disposed within the detonation manifold 208. Detonation fluid 209 may be supplied to the distribution chamber 314 at one or more locations. The respective distribution chamber 314 may have annular or semi-annular configurations. As shown, a first manifold 304 may include a first distribution chamber 316, and / or a second manifold 306 may include a second distribution chamber 318. The first distribution chamber 316 may be defined by one or more first conduit walls 308. The second distribution chamber 318 may be defined by one or more second conduit walls 310. In some embodiments, the respective distribution chambers among the plurality of distribution chambers 314 may be concentrically adjacent to each other, for example, as shown in the figure. Figures 3A-3E As shown. Additionally or alternatively, the respective distribution chambers in the plurality of distribution chambers 314 may be longitudinally adjacent to each other, for example, as Figures 4A-4E As shown.

[0093] like Figures 3A-3E and Figures 4A-4E As further shown, the plurality of manifold conduits 302 may include a plurality of outlet conduits 320 leading to corresponding detonation orifices among the plurality of detonation orifices 220. The plurality of outlet conduits 320 may be defined by the overall structure of the detonation manifold 208 or otherwise disposed within the detonation manifold 208. The plurality of outlet conduits 320 may each define at least a portion of a corresponding one of the plurality of detonation fluid paths 201. The plurality of manifold conduits 302 may communicate with the detonation chamber 206 through the plurality of detonation orifices 220 corresponding to the corresponding outlet conduits among the plurality of outlet conduits 320. The first manifold conduit 304 may include a first outlet conduit group 322, which includes a first plurality of outlet conduits 320. The plurality of outlet conduits 320 in the first outlet conduit group 322 may lead to corresponding detonation orifices among the plurality of detonation orifices 220 in the first detonation orifice group 222. The plurality of outlet conduits 320 in the first outlet conduit group 322 may define at least a portion of a first detonation fluid path 205. Additionally or alternatively, the second manifold duct 306 may include a second outlet duct assembly 324, which includes a second plurality of outlet ducts 320. The plurality of outlet ducts 320 in the second outlet duct assembly 324 may lead to a corresponding detonation orifice among the plurality of detonation orifices 220 in the second detonation orifice assembly 224. The plurality of outlet ducts 320 in the second outlet duct assembly 324 may define at least a portion of the second detonation fluid path 207.

[0094] In some embodiments, at least some outlet conduits 320 corresponding to a respective manifold duct 302 may pass through a distribution chamber 314 corresponding to another of the plurality of manifolds 302. A portion of the plurality of outlet conduits 320 passing through such a distribution chamber 314 may be fluidly isolated from the distribution chamber 314 by the integral structure of the detonation manifold 208 (e.g., through the cross conduit wall 326). As an example, such as Figure 3B As shown, multiple outlet conduits 320 in the second outlet conduit group 324 can pass through the first distribution chamber 316. The overall structure of the detonation manifold 208, which fluidly isolates the multiple outlet conduits 320 in the second outlet conduit group 324 from the first distribution chamber 316, may include multiple intersecting conduit walls 326, each corresponding to a corresponding outlet conduit in one of the multiple outlet conduits 320 in the second outlet conduit group 324. As another example, such as... Figure 4C and Figure 4D As shown, multiple outlet conduits 320 in the first outlet conduit group 322 can pass through the second distribution chamber 318. The overall structure of the detonation manifold 208, which fluidly isolates the multiple outlet conduits 320 in the first outlet conduit group 322 from the second distribution chamber 318, may include multiple intersecting conduit walls 326, which correspond to the respective outlet conduits in the multiple outlet conduits 320 in the first outlet conduit group 322.

[0095] Now for reference Figures 5A-5E and Figures 6A-6H Further, an exemplary grouping and arrangement of the detonation orifices 220 are described. As shown, the detonation manifold 208 may include multiple detonation orifice groups 203, such as a first detonation orifice group 222 and a second detonation orifice group 224. Each of the multiple detonation orifice groups 203 may each include multiple detonation orifices 220 in fluid communication with a corresponding one of the multiple manifold conduits 302. The multiple detonation orifices 220 may be arranged to be symmetrically adjacent and / or axially adjacent to each other. Multiple detonation orifices 220 corresponding to a particular detonation orifice group 203 may be arranged to be symmetrically adjacent and / or axially adjacent to a detonation orifice 220 corresponding to another of the multiple detonation orifice groups 203. For example, a corresponding detonation orifice 220 corresponding to the first detonation orifice group 222 may be arranged to be symmetrically adjacent and / or axially adjacent to a detonation orifice 220 corresponding to the second detonation orifice group 224. For example, as... Figures 6A-6H As shown, the plurality of detonation orifice groups 203 may each include a plurality of detonation orifices 220 coaxially oriented relative to each other. The coaxially oriented detonation orifices 220 may be defined by the structure (e.g., integral structure) of the detonation manifold 208. As shown, the coaxially oriented detonation orifices 222 may be arranged symmetrically adjacent and / or axially symmetrically adjacent to each other. It should be understood that, for ease of explanation, Figures 5A-5E and Figures 6A-6HThe detonation orifice 220 shown is depicted as being arranged linearly, and according to this disclosure, the detonation orifice 220 may have any desired configuration (e.g., elliptical or circular configuration), such as having a geometrically consistent perimeter.

[0096] like Figures 5A-5E and Figures 6A-6H As shown, multiple detonation orifices 220 can be constructed and arranged in an alternating sequence. As an example, Figures 5A-5E Multiple detonation orifices 220 arranged in sequence are shown. The multiple detonation orifices 220 include multiple first detonation orifices 222 that are respectively arranged to be symmetrically adjacent and / or axially symmetrically adjacent to the corresponding detonation orifices in the multiple second detonation orifices 220 of the second detonation orifice group 224. Figure 5B and Figure 5C A plurality of detonation orifices 220 arranged in sequence are shown, including a third plurality of detonation orifices 220 corresponding to a third detonation orifice group 502, respectively configured to be symmetrically adjacent and / or axially symmetrically adjacent to corresponding detonation orifices in a plurality of first detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 220 of a plurality of second detonation orifices 502. The third plurality of detonation orifices 220 corresponding to the third detonation orifice group 502 can be configured, for example, to supply a third detonation fluid 209 to the detonation chamber 206 via a third manifold fluidly isolated from the first manifold 304 and / or the second manifold 306.

[0097] As another example, such as Figures 6A-6H As shown, the detonation manifold 208 may include a first detonation orifice group 222 and a second detonation orifice group 224 having coaxially oriented detonation orifices 220. The coaxially oriented detonation orifices 220 may be arranged symmetrically adjacent to each other and / or axially symmetrically adjacent. As shown, at least some of the detonation orifices 220 in the first detonation orifice group 222 may circumferentially surround a corresponding detonation orifice 220 in the second detonation orifice group 224. Additionally or alternatively, for example, as... Figure 6B As shown, at least some of the detonation orifices 220 in the first detonation orifice group 222 can circumferentially surround a corresponding detonation orifice 220 in the second detonation orifice group 224, and at least some of the detonation orifices 220 in the second detonation orifice group 224 can circumferentially surround a corresponding detonation orifice 220 in the first detonation orifice group 222. Figure 6C and Figure 6DA plurality of detonation orifices 220 arranged in sequence are shown, including a third plurality of detonation orifices 220 corresponding to a third detonation orifice group 502, which are coaxially oriented relative to corresponding detonation orifices in a first detonation orifice group 222. In other embodiments, at least some of the detonation orifices 220 in the third detonation orifice group 502 may be coaxially oriented relative to corresponding detonation orifices 220 in a second detonation orifice group 224. Figure 6D A plurality of detonation orifices 220 arranged in sequence are shown, including a fourth plurality of detonation orifices 220 corresponding to a fourth detonation orifice group 504, which are coaxially oriented relative to corresponding detonation orifices in a second detonation orifice group 220 of a plurality of detonation orifices ...

[0098] like Figures 5A-5E and Figures 6A-6H As shown, at least some of the plurality of detonation orifices 220 can be uniformly spaced around a geometric perimeter 301 defined by the plurality of detonation orifices 220. As shown, the plurality of detonation orifices 220 in the first detonation orifice group 222 can be uniformly spaced from each other by a first set of inner perimeter spacing 307. The plurality of detonation orifices 220 in the second detonation orifice group 224 can be uniformly spaced from each other by a second set of inner perimeter spacing 309. For example, as... Figure 5B and 5C As shown in 6C, 6D, 6F, and 6G, the multiple detonation orifices 220 in the fourth detonation orifice group 504 can be uniformly spaced apart from each other by the inner perimeter spacing 311 of the third group. For example, as... Figure 6D and Figure 6H As shown, the plurality of detonation orifices 220 in the fourth detonation orifice group 504 can be uniformly spaced apart from each other by the inner perimeter spacing 313 of the fourth group. In some embodiments, such as... Figures 5A-5D and Figure 6A , 6B As shown in 6D, the first set of inner perimeter spacing 307 can be equal to the second set of inner perimeter spacing 309. Additional or alternative grounds, such as... Figure 5E and Figure 6C As shown, the first group of inner perimeter spacing 307 may differ from the second group of inner perimeter spacing 309. The third group of inner perimeter spacing 311 may be the same as or different from the first group of inner perimeter spacing 307 and / or the second group of inner perimeter spacing 309, for example, as shown in the figure. Figure 5B and 5C , Figure 6C and 6D ,as well as Figure 6G and 6H As shown.

[0099] like Figures 5A-5E and Figures 6A-6H As shown, in some embodiments, the detonation orifices 220 in the plurality of detonation orifice groups 203 can be uniformly spaced apart from each other by the inter-group perimeter spacing 305. For example, as Figures 5A-5C and Figures 6A-6H As shown, the detonation orifices 220 in the first detonation orifice group 222 can be uniformly spaced from adjacent detonation orifices 220 in the second detonation orifice group 224 by the inter-group perimeter spacing 305. Additionally or alternatively, such as... Figures 5A-5C As shown, the detonation holes 220 in the first detonation hole group 222 and / or the detonation holes 220 in the second detonation hole group 224 can be evenly spaced apart from the adjacent detonation holes 220 in the third detonation hole group 502 and / or the fourth detonation hole group 504 by the inter-group perimeter spacing 305.

[0100] Additional or alternative land, such as Figure 5D and Figure 5E As shown, the plurality of detonation wells 220 in a corresponding detonation well group 203 may have inconsistent inter-group boundary spacing 506. As used herein, the term "inconsistent inter-group boundary spacing" refers to different inter-group boundary spacings between adjacent detonation wells 220 in a corresponding detonation well group within a plurality of detonation wells 203. For example, as Figure 5D and Figure 5E As shown, the detonation orifice 220 in the first detonation orifice group 222 may have an inter-group perimeter spacing 506 that is inconsistent with that between adjacent detonation orifices 220 in the second detonation orifice group 224.

[0101] For example, such as Figure 6E-6H As shown, the detonation orifice 220 in a corresponding detonation orifice group of multiple detonation orifice groups 203 uniformly spaced by different group perimeter intervals 303 may include multiple coaxially oriented detonation orifices 220 and combinations of multiple detonation orifices lacking corresponding coaxially oriented detonation orifices 220. For example, as Figure 6E-6HAs shown, the plurality of detonation orifices 220 in the first detonation orifice group 222 can be uniformly spaced apart from each other by a first group of inner perimeter intervals 307, and the plurality of detonation orifices 220 in the second detonation orifice group 224 can be uniformly spaced apart from each other by a second group of inner perimeter intervals 309. The first group of inner perimeter intervals 307 and the second group of inner perimeter intervals 309 can have a common multiple. The detonation orifices 220 in the corresponding detonation orifice group 203 can be coaxially oriented to a common multiple of the corresponding group of inner perimeter intervals 303. For multiples of the corresponding group of inner perimeter intervals 303 that do not coincide with each other, the detonation orifices 220 in the corresponding detonation orifice group 203 may lack a corresponding detonation orifice 220 coaxially oriented from another detonation orifice group 203. Such multiples of the corresponding group of inner perimeter intervals 303 that do not coincide with each other are sometimes referred to as non-coinciding multiples. Additionally or alternatively, the corresponding detonation orifice groups 203 lacking a common multiple may not coincide with each other, such that the detonation orifice in the corresponding detonation orifice group 203 may lack a corresponding detonation orifice 220 coaxially oriented from another detonation orifice group 203.

[0102] As an example, such as Figure 6E-6H As shown, for a common multiple of the first group's inner perimeter spacing 307 and the second group's inner perimeter spacing 309, the detonation orifice 220 in the second detonation orifice group 224 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222. For a non-overlapping multiple of the first group's inner perimeter spacing 307 and the second group's inner perimeter spacing 309, the detonation orifice 220 in the second detonation orifice group 224 may lack a corresponding detonation orifice 220 coaxially oriented from the first detonation orifice group 222. For example, as... Figure 6E As shown, the first group of inner perimeter spacing 307 can be a multiple of two, and the second group of inner perimeter spacing 309 can be a multiple of one. For a common multiple of two, the detonation orifices 220 in the second detonation orifice group 224 can be coaxially oriented with the detonation orifices 220 in the first detonation orifice group 222, for example, the detonation orifices 220 located at positions 1, 3, 5, 7, etc., or the detonation orifices 220 located at positions 2, 4, 6, 8, etc. As another example, such as Figure 6F As shown, the first group of inner perimeter spacing 307 can be a multiple of four, and the second group of inner perimeter spacing 309 can be a multiple of one. For a common multiple of four, the detonation orifice 220 in the second detonation orifice group 224 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222, for example, the detonation orifices 220 located at positions 1, 4, 8, 12, etc., or the detonation orifices 220 located at positions 2, 5, 7, 7, etc.

[0103] In some embodiments, such as Figure 6GAs shown, for offset multiples of the corresponding non-overlapping perimeter spacing 303 within the same group, the detonation orifice in the corresponding detonation orifice group 203 may lack a corresponding detonation orifice 220 coaxially oriented from another detonation orifice group 203. Such offset multiples can include even and odd multiples that do not overlap. Such offset multiples can include the offset of one or more detonation orifice elements. For example, as... Figure 6G As shown, the first group of inner perimeter spacing 307 and the second group of inner perimeter spacing 309 can each be an odd multiple of two, and the third group of inner perimeter spacing 311 can be an even multiple of two. The second group of inner perimeter spacing 309 can be offset by zero detonation orifice units. The third group of inner perimeter spacing 311 can be offset by one detonation orifice unit. The second group of inner perimeter spacing 309 can have a common multiple of two with the first group of inner perimeter spacing 307. For a common multiple of two (e.g., an odd multiple of two, or a multiple of two), the detonation orifice 220 in the second detonation orifice group 224 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222, offset by zero detonation orifice units, located at positions 1, 3, 5, 7, etc. The detonation orifice 220 in the third detonation orifice group 502 lacks a corresponding detonation orifice 220 with coaxial orientation because the inner perimeter spacing 311 of the third group, which is offset by one detonation orifice unit, lacks a common multiple with the inner perimeter spacing 307 of the first group and the inner perimeter spacing 309 of the second group. The detonation orifices 220 in the third detonation orifice group 502 are located at even multiples of two (e.g., multiples of two), offset by one detonation orifice unit, at positions 2, 4, 6, 8, etc. This even multiple of two does not coincide with the odd multiples of two corresponding to the first detonation orifice group 222 and the second detonation orifice group 224.

[0104] As another example, such as Figure 6H As shown, the first detonation orifice group 222 may have a first inner perimeter interval 307, which is a multiple of three, and has an offset of zero detonation orifice units; the second detonation orifice group 224 may have a second inner perimeter interval 309, which is a multiple of four, and has an offset of two detonation orifice units; the third detonation orifice group 502 may have a third inner perimeter interval 311, which is a multiple of four detonation orifice units, and has an offset of zero detonation orifice units; and the fourth detonation orifice group 504 may have a fourth inner perimeter interval 313, which is a multiple of two, and has an offset of one detonation orifice unit. Figure 6HAs shown, as an example, the second group of inner perimeter spacing 309 and the first group of inner perimeter spacing 307 have a common multiple of twelve. For a common multiple of twelve, the detonation orifice 220 in the second detonation orifice group 224 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222, offset by six detonation orifice units. The third group of inner perimeter spacing 311 and the first group of inner perimeter spacing 307 have a common multiple of twelve. For a coincident multiple of twelve, the detonation orifice 220 in the third detonation orifice group 502 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222, offset by zero detonation orifice units. The fourth group of inner perimeter spacing 313 and the first group of inner perimeter spacing 307 have a common multiple of six. For a multiple of six, the detonation orifice 220 in the fourth detonation orifice group 504 can be coaxially oriented with the detonation orifice 220 in the first detonation orifice group 222, offset by three detonation orifice units.

[0105] like Figure 6H As further illustrated, as another example, the second group of inner perimeter spacing 309, the third group of inner perimeter spacing 311, and the fourth group of inner perimeter spacing 313 are, for example, lacking a common multiple of each other due to their respective offsets. Thus, the detonation orifices 220 in the second detonation orifice group 224, the third detonation orifice group 502, and the fourth detonation orifice group 504 do not overlap. For example, the second group of inner perimeter spacing 309 can have an odd multiple of four, offset by two detonation orifice units; the third group of inner perimeter spacing 311 can have an odd multiple of four, offset by zero detonation orifice units; and the fourth group of inner perimeter spacing 313 can have an even multiple of two, offset by one detonation orifice unit. Thus, the detonation orifice 220 in the fourth detonation orifice group 504 does not coincide with the detonation orifice 220 in the second detonation orifice group 224 and the third detonation orifice group 502, and the detonation orifice 220 in the second detonation orifice group 224 does not coincide with the detonation orifice 220 in the third detonation orifice group 502.

[0106] An exemplary knock manifold 208 may include any desired number of manifold conduits 302 in fluid communication with a plurality of knock orifices 220, each corresponding to a knock orifice group 203 associated with a respective manifold conduit 302. As an example, the knock manifold 208 may include 2 to 6 manifold conduits 302, such as 2 to 4 manifold conduits 302, or 2 or 3 manifold conduits 302. An exemplary knock manifold 208 may include 2 to 6 knock orifice groups 203, such as 2 to 4 knock orifice groups 203, or 2 or 3 knock orifice groups 203, each corresponding to a respective one of the plurality of manifold conduits 302.

[0107] The detonation combustion system 200 can be configured to supply one or more detonation fluids 209 to the detonation chamber 206 using one or more of corresponding detonation fluid paths 201 having any desired hydrodynamics (e.g., volumetric flow rate, velocity, pressure, and / or pressure drop across the corresponding detonation orifice 220 in the detonation orifice group 203). In some embodiments, the plurality of detonation fluid paths 201 can be configured to supply detonation fluids 209 at respectively different flow rates and have the same or similar pressures and / or pressure drops across the corresponding plurality of detonation orifices 220. By providing a plurality of detonation fluid paths 201 having similar pressures and / or pressure drops at respectively different flow rates, the detonation chamber 206 can receive detonation fluids 209 with comparable hydrodynamics at respectively different flow rates. For example, at respectively different flow rates of detonation fluids 209, detonation fluids 209 can interact comparably with shock waves 248 and corresponding detonation waves 246 during detonation. Different flow rates allow for corresponding thrust levels, for example, to be applicable to different operating conditions. Additionally or alternatively, in some embodiments, the plurality of detonation fluid paths 201 may be configured to provide detonation fluid 209 at different pressures and / or pressure drops across the corresponding plurality of detonation orifices 220, and have the same or similar flow rates. By providing a plurality of detonation fluid paths 201 with similar flow rates at different pressures and / or pressure drops, the detonation chamber 206 can receive detonation fluid 209 with corresponding hydrodynamics at selected flow rates, which can provide different combustion dynamics (e.g., detonation dynamics) that may be desirable for different operating conditions.

[0108] In some embodiments, the number of detonation orifices 220 in a respective detonation orifice group 203 may be proportional to the mass flow rate of detonation fluid 209 through the detonation orifices 220 in the respective detonation orifice group 203. The number of detonation orifices 220 in the detonation orifice group 203 corresponding to the respective manifold 302 may be selected at least partially to provide the desired hydrodynamics of the detonation fluid 209 flowing through the respective detonation orifices 220 from the respective manifold 302 to the detonation chamber 206. Additionally or alternatively, the surface area of ​​the detonation orifices 220 in the detonation orifice group 203 corresponding to the respective manifold 302 may be selected at least partially to provide the desired hydrodynamics of the detonation fluid 209 flowing through the respective detonation orifices 220 from the respective manifold 302 to the detonation chamber 206.

[0109] In some embodiments, the first detonation orifice group 222 corresponding to the first manifold duct 304 may include a first detonation orifice group 222 configured to provide a flow rate to the detonation chamber 206 that is from about 1% to about 100% of the flow rate of the second detonation orifice group 224 corresponding to the second manifold duct 306. For example, the flow rate of the first detonation orifice group 222 may be from about 10% to about 90% of the flow rate of the second detonation orifice group 224, for example, from about 20% to about 30%, for example, from about 30% to about 40%, for example, from about 40% to about 60%, for example, from about 60% to about 70%, for example, from about 70% to about 80%, or for example, from about 80% to about 90%.

[0110] In some embodiments, a first knock orifice group 222 corresponding to a first manifold duct 304 may include a first knock orifice group 222 configured to provide pressure and / or pressure drop that is about 1% to about 100% of the pressure and / or pressure drop across a second knock orifice group 224 corresponding to a second manifold duct 306. For example, the pressure and / or pressure drop across the first knock orifice group 222 may be about 10% to about 90% of the pressure and / or pressure drop across the second knock orifice group 224, for example, about 20% to about 30% of the pressure and / or pressure drop across the second knock orifice group 224, for example, about 30% to about 40%, for example, about 40% to about 60%, for example, about 60% to about 70%, for example, about 70% to about 80%, or for example, about 80% to about 90%.

[0111] In some embodiments, the flow rate from the respective manifold duct 302 to the detonation chamber 206 for the respective detonation orifice group 203 can be determined under choke conditions. As used herein, the term "choke" refers to a constraint in which, for a given upstream pressure and temperature, the mass flow rate through the plurality of detonation orifices 220 of the detonation orifice group 203 will not increase with a further decrease in downstream pressure. In some embodiments, the respective detonation orifice groups 203 in the plurality of detonation orifice groups 203 can be configured, for example, to provide a substantially uniform pressure drop between the respective detonation orifice groups 203 under the respective choke conditions, and / or, for example, to have upstream pressures and temperatures within suitable ranges for the desired operating conditions. By providing a substantially uniform pressure drop between the respective detonation orifice groups 203, the operating variables associated with the pressure of the detonation fluid 209 can be normalized for a plurality of different operating conditions. Additionally or alternatively, such operating variables can be tailored to suit separately different operating conditions. As an example, combustion dynamics may be affected by the pressure drop of the detonation fluid 209 entering the detonation chamber 206.

[0112] In some embodiments, the ratio of the number of detonation orifices 220 in the first detonation orifice group 222 to the number of detonation orifices 220 in the second detonation orifice group 224 may be 1:20 to 1:1, for example 1:20 to 1:10, for example 1:10 to 1:5, for example 1:5 to 1:1, for example 1:4 to 1:1, for example 1:3 to 1:1, for example 2:3 to 1:1, or for example 3:4 to 1:1. Additionally or alternatively, in some embodiments, the ratio of the number of detonation orifices 220 in the first detonation orifice group 222 to the total number of detonation orifices 220 in a plurality of additional detonation orifice groups 203 (e.g., the total number of detonation orifices in the second detonation orifice group 224 and the third detonation orifice group 502) may be 1:20 to 1:1, for example 1:20 to 1:10, for example 1:10 to 1:5, for example 1:5 to 1:1, for example 1:4 to 1:1, for example 1:3 to 1:1, for example 2:3 to 1:1, or for example 3:4 to 1:1. Additionally or alternatively, in some embodiments, the ratio of the total surface area of ​​the detonation orifices 220 in the first detonation orifice group 222 to the total surface area of ​​the detonation orifices 220 in the second detonation orifice group 224 may be 1:20 to 1:1, for example 1:20 to 1:10, for example 1:10 to 1:5, for example 1:5 to 1:1, for example 1:4 to 1:1, for example 1:3 to 1:1, for example 2:3 to 1:1, or for example 3:4 to 1:1.

[0113] The detonation combustion system 200 can be configured to use individual or collective manifolds among a plurality of manifolds 302 at a given time. As an example, in some embodiments, the detonation manifold 208 can be configured to provide 100% proportional flow when using the first manifold 304 corresponding to the first detonation orifice group 222 and the second manifold 306 corresponding to the second detonation orifice group 224. In one embodiment, the detonation manifold 208 can be configured to provide 25% proportional flow when using the first manifold 304 corresponding to the first detonation orifice group 222. Additionally or alternatively, the detonation manifold 208 can be configured to provide 75% proportional flow when using the second manifold 306 corresponding to the second detonation orifice group 224. In another embodiment, the detonation manifold 208 can be configured to provide 33% proportional flow when using the first manifold 304 corresponding to the first detonation orifice group 222 and 66% proportional flow when using the second manifold 306 corresponding to the second detonation orifice group 224. In another embodiment, the detonation manifold 208 may be configured to provide a 50% proportional flow rate when using the first manifold conduit 304 corresponding to the first detonation orifice group 222, and a 50% proportional flow rate when using the second manifold conduit 306 corresponding to the second detonation orifice group 224. In yet another embodiment, the detonation manifold 208 may be configured to provide a 33% proportional flow rate when using the first manifold conduit 304 corresponding to the first detonation orifice group 222, a 33% proportional flow rate when using the second manifold conduit 306 corresponding to the second detonation orifice group 224, and a 33% proportional flow rate when using the third manifold conduit corresponding to the third detonation orifice group 502.

[0114] The exemplary fuel 62 that may be included in the detonation fluid 209 includes liquid fuels and / or gaseous fuels. In some embodiments, at least some of the plurality of detonation fluid paths 201 may be configured to supply different fuels to the detonation chamber 206. Additionally or alternatively, at least some of the plurality of detonation fluid paths 201 may be configured to supply fluids different from the fuels to the detonation chamber 206, such as oxidant 60 that can be mixed with fuel 62, and / or purge air for purging the detonation fluid paths 201 and / or the detonation chamber 206.

[0115] Now for reference Figure 7An exemplary control system 226 for controlling a knock combustion system 200 is described. The operation of the knock combustion system 200 can be controlled by the control system 226, for example, based at least in part on inputs from one or more sensors 700 (e.g., one or more temperature sensors, pressure sensors, engine speed sensors, etc.) associated with the engine 50 and / or the knock combustion system 200. The control system 226 can be configured to receive electronic inputs from one or more sensors 700 and to provide control commands to one or more controllable components 702, such as one or more knock manifold supply valves 228, one or more fuel supply valves 234, and / or one or more oxidizer supply valves 240, based at least in part on the electronic inputs from one or more sensors. Figure 2 Additionally or alternatively, the control system 226 may actuate one or more controllable components 702, such as one or more knock manifold supply valves 228, one or more fuel supply valves 234, and / or one or more oxidizer supply valves 240, at least in part based on electronic input from the user. Figure 2 ).

[0116] like Figure 7 As shown, the exemplary control system 226 may include a controller 704, such as an electronic engine controller, a full authority digital engine control (FADEC) device, etc. The controller 704 may include one or more computing devices 706 configured to perform one or more control operations associated with the knock combustion system 200 and / or the engine 50. The one or more computing devices 706 may be located locally or remotely relative to the engine 50 and / or the knock combustion system 200. Control operations may include determining and / or outputting control commands associated with one or more controllable components 702 of the knock combustion system 200, such as control commands configured to actuate one or more knock manifold supply valves 228, one or more fuel supply valves 234, and / or one or more oxidizer supply valves 240. The computing devices 706 may be communicatively coupled to one or more sensors 700 and / or to one or more controllable components 702. The computing devices 706 may include one or more control modules 708 configured to cause the controller 704 to perform one or more control operations, for example, based at least in part on inputs from one or more sensors 700. In some embodiments, the control module 708 may be configured to determine a threshold or setpoint for starting, stopping, increasing, and / or decreasing the flow of fuel 62 and / or oxidizer 60 to the knock manifold 208. Additionally or alternatively, the control module 708 may be configured to determine and / or output control commands to one or more controllable components 702 based at least in part on such threshold or setpoint (e.g., at least in part on deviations from such threshold and / or setpoint).

[0117] One or more computing devices 706 may include one or more processors 710 and one or more memory devices 712. The one or more processors 710 may include any suitable processing means, such as a microprocessor, microcontroller, integrated circuit, logic device, and / or other suitable processing means. The one or more memory devices 712 may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, RAM, ROM, hard disk drives, flash drives, and / or other memory devices 712. One or more control modules 708 may be implemented at least in part by one or more processors 710 and / or one or more memory devices 712.

[0118] As used herein, the terms “processor” and “computer”, as well as related terms (e.g., “processing device” and “computing device”), are not limited to those integrated circuits referred to in the art as computers, but broadly refer to microcontrollers, microcomputers, programmable logic controllers (PLCs), application-specific integrated circuits (ASICs), and other programmable circuits, and these terms are used interchangeably herein. Memory device 712 may include, but is not limited to, non-transitory computer-readable media (e.g., random access memory (RAM)) and computer-readable non-volatile media such as hard disk drives, flash memory, and other memory devices. Alternatively, floppy disks, read-only optical disc drives (CD-ROMs), magneto-optical discs (MODs), and / or digital universal discs (DVDs) may also be used.

[0119] As used herein, the term "non-transitory computer-readable medium" is intended to refer to any tangible computer-based device implemented with any method or technique for the short-term and long-term storage of information (e.g., computer-readable instructions, data structures, program modules and submodules, or other data in any device). The methods described herein can be encoded as executable instructions embodied in a tangible non-transitory computer-readable medium (including, but not limited to, storage devices and / or memory devices). When executed by a processor, such instructions cause the processor to perform at least a portion of the methods described herein. Furthermore, as used herein, the term "non-transitory computer-readable medium" includes all tangible computer-readable media, including but not limited to non-transitory computer storage devices, including but not limited to volatile and non-volatile media, and removable and non-removable media (e.g., firmware, physical and virtual storage devices, CD-ROMs, DVDs, and any other digital resources (e.g., networks or the Internet)), and undeveloped digital means, with the sole exception of transient propagation signals.

[0120] One or more memory devices 712 may store information accessible by one or more processors 710, including computer-executable instructions 714 executable by one or more processors 710. Instructions 714 may include any set of instructions that, when executed by one or more processors 710, cause one or more processors 710 to perform operations, including control operations associated with engine 50 and / or knock combustion system 200. One or more memory devices 712 may store data 716 accessible by one or more processors 710, such as data associated with engine 50, knock combustion system 200, sensor 700, and / or controllable component 702. Data 716 may include current or real-time data 716, past data 716, or a combination thereof. Data 716 may be stored in a database 718. Data 716 may also include other datasets, parameters, outputs, and information associated with engine 50 and / or knock combustion system 200.

[0121] One or more computing devices 706 may also include a communication interface 720 configured to communicate with various nodes on a communication network 722 via a wired or wireless communication line 724. The communication interface 720 may include any suitable components for interfacing with one or more networks, including, for example, a transmitter, receiver, port, controller, antenna, and / or other suitable components. The communication network 722 may include, for example, a local area network (LAN), a wide area network (WAN), a SATCOM network, a VHF network, an HF network, a Wi-Fi network, a WiMAX network, a gatelink network, and / or any other suitable communication network 722 for transmitting messages to and / or from the computing device 706 via the communication line 724. The communication line 724 of the communication network 722 may include a data bus or a combination of wired and / or wireless communication links.

[0122] Control system 226 may include a management system 726 located locally or remotely relative to engine 50 and / or knock combustion system 200. Management system 726 may include server 728 and / or data warehouse 730. As an example, at least a portion of data 716 may be stored in data warehouse 730, and server 728 may be configured to transfer data 716 from data warehouse 730 to one or more computing devices 706, and / or receive data 716 from one or more computing devices 706 and store the received data 716 in data warehouse 730 for further purposes. Server 728 and / or data warehouse 730 may be implemented as part of one or more computing devices 706 and / or as part of management system 726. Control system 226 may also include user interface 732, which is configured to allow a user to interact with various features of control system 226, for example, via communication interface 720. The communication interface 720 allows one or more computing devices 706 to communicate with various nodes associated with the engine 50 and / or the knock combustion system 200, the management system 726 and / or the user interface 732.

[0123] Now for reference Figure 8 The exemplary methods according to this disclosure are further described below. As an example, the exemplary method may include a method for generating thrust. Additionally or alternatively, the exemplary method may include a method for burning fuel. Additionally or alternatively, the exemplary method may include a method for operating engine 50 (e.g., turbine engine 100, rocket engine, ramjet engine, or combinations thereof, such as a turborocket engine, turboramjet engine, or rocket ramjet engine).

[0124] like Figure 8 As shown, exemplary method 800 may include, at block 802, detonating in the detonation chamber 206 of the detonation burner 202 using detonation fluid 209 flowing through a first detonation fluid path 205 to the detonation chamber 206. The first detonation fluid path 205 may be at least partially defined by the overall structure of the detonation manifold 208. The first detonation fluid path 205 may be in fluid communication with the detonation chamber 206 via a first detonation orifice group 222 including a plurality of first detonation orifices 220. Detonation occurring while the detonation fluid 209 flows through the first detonation fluid path may occur during a first operating state. Detonation occurring while the detonation fluid flows through the first detonation fluid path may generate a first thrust level.

[0125] At block 804, exemplary method 800 may include detonation in detonation chamber 206 using detonation fluid 209 flowing through a second detonation fluid path 207 to detonation chamber 206. The second detonation fluid path 207 may be at least partially defined by the overall structure of detonation manifold 208. The second detonation fluid path 207 may be in fluid communication with detonation chamber 206 via a second detonation orifice group 224 including a plurality of second detonation orifices 220. The plurality of first detonation orifices 220 and the plurality of second detonation orifices 220 may be symmetrically oriented about a reference element of detonation burner 202. Detonation occurring while detonation fluid 209 flows through the second detonation fluid path 207 may occur during a second operating state different from the first operating state. Detonation occurring while detonation fluid 209 flows through the second detonation fluid path 207 may generate a second thrust level different from the first thrust level.

[0126] Therefore, the currently disclosed systems and methods can utilize detonation combustion systems to provide different thrust levels suitable for various operating conditions. Corresponding detonation fluid paths and corresponding detonation groups can be constructed and arranged to provide comparable and / or suitable hydrodynamics regarding the detonation fluid introduced into the detonation chamber. For example, operating variables associated with the pressure of the detonation fluid can be normalized and / or customized for multiple different operating conditions. Additionally or alternatively, operating variables associated with the location of the detonation fluid entering the detonation chamber can be normalized and / or customized for multiple different operating conditions.

[0127] Further aspects of this disclosure are provided by the subject matter of the following clauses:

[0128] A combustion system includes: a knock burner, the knock burner including a knock manifold and one or more knock chamber walls defining a knock chamber; wherein the knock manifold includes a plurality of knock fluid paths defined by an integral structure of the knock manifold, and a plurality of knock orifice groups, each including a plurality of knock orifices disposed around a surface of the knock manifold; wherein a corresponding knock orifice group in the plurality of knock orifice groups provides fluid communication from a corresponding one of the plurality of knock fluid paths to the knock chamber through the plurality of knock orifices corresponding to a corresponding one of the plurality of knock orifice groups; and wherein the plurality of knock orifices are symmetrically oriented about a reference element of the knock burner.

[0129] The combustion system according to any clause of this document, wherein the plurality of detonation orifices are oriented axisymmetrically about the longitudinal axis of the detonation chamber and / or the detonation manifold.

[0130] According to any provision of this document, the combustion system comprising the plurality of knock orifice groups includes: a first knock orifice group and a second knock orifice group, wherein the first knock orifice group includes a plurality of first knock orifices and the second knock orifice group includes a plurality of second knock orifices; wherein at least some of the plurality of first knock orifices are symmetrically adjacent to or axially symmetrically adjacent to a corresponding one of the plurality of second knock orifices.

[0131] According to any clause of this document, in a combustion system, at least some of the plurality of first detonation orifices are oriented in an alternating sequence with corresponding second detonation orifices of the plurality of second detonation orifices.

[0132] According to any clause of this document, in a combustion system, at least some of the plurality of first detonation orifices are coaxially oriented relative to a corresponding second detonation orifice among a plurality of second detonation orifices.

[0133] According to any clause of this document, in a combustion system, some of the plurality of first detonation orifices are circumferentially surrounding a corresponding one of the plurality of second detonation orifices, and / or some of the plurality of second detonation orifices are circumferentially surrounding a corresponding one of the plurality of first detonation orifices.

[0134] According to any clause of this document, the combustion system wherein the plurality of knock orifices have geometrical consistency with respect to the reference element of the knock burner about which the plurality of knock orifices are oriented.

[0135] According to any clause of this document, the reference element of the knock burner includes: a longitudinal axis of the knock chamber and / or the knock manifold; a corresponding one of the one or more knock chamber walls circumferentially surrounding the longitudinal axis; a knock manifold wall circumferentially surrounding the longitudinal axis; an annular midplane; or a meridian located at a longitudinal position along the longitudinal axis, the meridian defining the periphery of at least one of the following: the knock chamber wall, the knock manifold wall, and the annular midplane.

[0136] According to any clause of this document, the combustion system wherein the plurality of detonation orifices are geometrically consistent with at least one of: an annular midplane and a meridian defining the periphery of the annular midplane at a longitudinal position along the annular midplane.

[0137] According to any provision of this document, the combustion system wherein the annular midplane comprises a cylindrical shape and the meridian comprises a circular line, or wherein the annular midplane comprises an elliptical cylindrical shape and the meridian comprises an elliptical line, or wherein the annular midplane comprises a curved cylindrical shape and the meridian comprises a curved line, or wherein the annular midplane comprises a polyhedral prism shape and the meridian comprises a polygonal line.

[0138] According to any clause of this document, the combustion system wherein the plurality of knock orifices have geometrical conformity with respect to at least one of: a corresponding one of the one or more knock chamber walls, the corresponding one of the one or more knock chamber walls being circumferentially about the longitudinal axis of the knock chamber; a knock manifold wall, the knock manifold wall being circumferentially about the longitudinal axis of the knock chamber; and a meridian, the meridian defining the periphery of a corresponding one of the one or more knock chamber walls or defining the periphery of the knock manifold wall.

[0139] According to any clause of this document, the plurality of knock orifices are uniformly spaced around a geometric perimeter defined by the plurality of knock orifices, and the uniformly spaced plurality of knock orifices include at least one of the following: equidistant spacing and proportional spacing.

[0140] According to any provision of this document, the combustion system comprises a plurality of detonation orifice groups including a first detonation orifice group containing a plurality of first detonation orifices and a second detonation orifice group containing a plurality of second detonation orifices; and wherein the plurality of first detonation orifices are uniformly spaced apart from each other by a first set of inner perimeter intervals, and the plurality of second detonation orifices are uniformly spaced apart from each other by a second set of inner perimeter intervals, the second set of inner perimeter intervals being different from the first set of inner perimeter intervals.

[0141] According to any clause of this document, in a combustion system, a corresponding first detonation orifice among the plurality of first detonation orifices is uniformly spaced from an adjacent second detonation orifice among the plurality of second detonation orifices by an intergroup perimeter spacing.

[0142] According to any provision of this document, the combustion system includes a knock manifold comprising a plurality of manifold conduits defined by an integral structure of the knock manifold, wherein each of the plurality of manifold conduits defines at least a portion of a corresponding one of the plurality of knock fluid paths; wherein each of the plurality of manifold conduits comprises at least one of: a distribution chamber defined by the integral structure of the knock manifold, the distribution chamber having an annular or semi-annular configuration; and a plurality of outlet conduits leading to a corresponding knock orifice among the plurality of knock orifices corresponding to a corresponding one of the plurality of knock fluid paths.

[0143] The combustion system according to any clause of this document, wherein the detonation chamber and / or the detonation manifold has a configuration including at least one of the following: annular elliptical configuration, annular cylindrical configuration, and annular polyhedral configuration.

[0144] According to any provision of this document, the combustion system wherein the plurality of knock fluid paths include: a first knock fluid path, the first knock fluid path being in fluid communication with the knock chamber via a plurality of first knock orifices corresponding to a first knock orifice group in the plurality of knock orifice groups; and a second knock fluid path, the second knock fluid path being in fluid communication with the knock chamber via a plurality of second knock orifices corresponding to a second knock orifice group in the plurality of knock orifice groups.

[0145] According to any clause of this document, in a combustion system, the first knock fluid path is configured to supply a first knock fluid to the knock chamber through the plurality of first knock orifices, and the second knock fluid path is configured to supply a second knock fluid to the knock chamber through the plurality of second knock orifices, wherein the first knock fluid is different from the second knock fluid, and wherein the first knock fluid and the second knock fluid each comprise at least one of the following: oxidizer, fuel, coolant, and purge air.

[0146] A knock manifold includes: a plurality of knock fluid paths defined by an overall structure of the knock manifold; and a plurality of knock orifice groups, each including a plurality of knock orifices disposed around a surface of the knock manifold; wherein a corresponding knock orifice group in the plurality of knock orifice groups provides fluid communication with a corresponding one of the plurality of knock fluid paths through a plurality of knock orifices corresponding to a corresponding one of the plurality of knock orifice groups; and wherein the plurality of knock orifices are symmetrically oriented around a reference element of the knock burner.

[0147] An engine includes: an inlet section; a combustor section; and an outlet section; wherein the combustor section includes the combustion system described in any clause herein and / or the knock manifold described in any clause herein.

[0148] The engine described in any of the clauses herein includes: a turbine engine, a rocket engine, a ramjet engine, a turborocket engine, a turboramjet engine, or a rocket ramjet engine.

[0149] An engine as described in any clause of this document, wherein the engine includes a turbine engine, the turbine engine including a turbine section disposed downstream of the combustor section.

[0150] An engine according to any clause of this document, wherein the turbocharger engine includes a compressor section disposed upstream of the combustor section.

[0151] A method for generating thrust, the method comprising: detonating in the detonation chamber of a detonation burner using detonation fluid flowing to a detonation chamber via a first detonation fluid path defined at least partially by an integral structure of a detonation manifold of the detonation burner, the first detonation fluid path being in fluid communication with the detonation chamber via a first detonation orifice group comprising a plurality of first detonation orifices; and detonating in the detonation chamber using detonation fluid flowing to the detonation chamber via a second detonation fluid path defined at least partially by the integral structure of the detonation manifold, the second detonation fluid path being in fluid communication with the detonation chamber via a second detonation orifice group comprising a plurality of second detonation orifices; wherein the plurality of first detonation orifices and the plurality of second detonation orifices are symmetrically oriented about a reference element of the detonation burner.

[0152] According to any of the methods described herein, the detonation that occurs while the detonation fluid flows through the first detonation fluid path is performed during a first operating state, and the detonation that occurs while the detonation fluid flows through the second detonation fluid path is performed during a second operating state, which is different from the first operating state.

[0153] According to any of the methods described herein, the detonation generates a first thrust level while the detonation fluid flows through the first detonation fluid path, and the detonation generates a second thrust level while the detonation fluid flows through the second detonation fluid path, the second thrust level being different from the first thrust level.

[0154] According to any of the methods described herein, detonation within the detonation chamber comprises: generating a plurality of primary shock waves that propagate in a ring through the detonation chamber.

[0155] According to any of the methods described herein, performing a detonation within the detonation chamber includes: generating multiple shock waves that propagate longitudinally through the detonation chamber and generating thrust.

[0156] According to any of the methods described herein, the detonation chamber includes a detonation nozzle, and the detonation combustion products have a velocity of 1,000 m / s to 5,000 m / s downstream of the detonation nozzle.

[0157] The method described in any clause of this document is performed using either the combustion system or the engine described in any clause of this document.

[0158] This written description uses exemplary embodiments to describe the subject matter currently disclosed, including best practices, and also enables any person skilled in the art to practice such subject matter, including making and using any apparatus or system and methods of making any combination. The patentable scope of the subject matter currently disclosed is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A detonation combustion system, characterized in that, include: A detonation burner, the detonation burner including a detonation manifold and one or more detonation chamber walls defining a detonation chamber; The detonation manifold includes: Multiple detonation fluid paths, the multiple detonation fluid paths being defined by the overall structure of the detonation manifold; and Multiple detonation port groups, each group comprising multiple detonation ports, the multiple detonation ports being arranged around the surface of the detonation manifold; Among them, a corresponding detonation orifice group in the plurality of detonation orifice groups provides fluid communication from a corresponding one of the plurality of detonation fluid paths to the detonation chamber through a plurality of detonation orifices corresponding to a corresponding one in the plurality of detonation orifice groups; and The plurality of detonation orifices are symmetrically oriented around a reference element of the detonation burner, the reference element comprising at least one of the following: (i) the longitudinal axis of the detonation chamber or the detonation manifold; (ii) a corresponding one of the one or more detonation chamber walls; (iii) the detonation manifold wall; (iv) an annular midplane; and (v) a meridian located at a longitudinal position along the longitudinal axis of the detonation chamber or the detonation manifold, the meridian defining the periphery of at least one of the following: a corresponding one of the one or more detonation chamber walls; the detonation manifold wall; and the annular midplane.

2. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifices are oriented symmetrically around the longitudinal axis of the detonation chamber and / or the detonation manifold.

3. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifice groups include: A first detonation orifice group and a second detonation orifice group, wherein the first detonation orifice group includes a plurality of first detonation orifices and the second detonation orifice group includes a plurality of second detonation orifices; At least some of the plurality of first detonation orifices are symmetrically adjacent to or axially symmetrically adjacent to a corresponding one of the plurality of second detonation orifices.

4. The detonation combustion system according to claim 3, characterized in that, in, At least some of the plurality of first detonation orifices are oriented in an alternating sequence with their corresponding second detonation orifices among the plurality of second detonation orifices.

5. The detonation combustion system according to claim 3, characterized in that, in, At least some of the plurality of first detonation orifices are coaxially oriented relative to the corresponding second detonation orifices in the plurality of second detonation orifices.

6. The detonation combustion system according to claim 5, characterized in that, in, Some of the plurality of first detonation orifices circumferentially surround a corresponding one of the plurality of second detonation orifices, and / or some of the plurality of second detonation orifices circumferentially surround a corresponding one of the plurality of first detonation orifices.

7. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifices have geometrical consistency with respect to the reference element of the detonation burner about which the plurality of detonation orifices are oriented.

8. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifices are geometrically consistent with at least one of the following: (i) the annular midplane and (ii) the meridian.

9. The detonation combustion system according to claim 8, characterized in that, in, The annular midplane includes a cylindrical shape and the meridian includes a circular line, or wherein the annular midplane includes an elliptical cylindrical shape and the meridian includes an elliptical line, or wherein the annular midplane includes a curved cylindrical shape and the meridian includes a curved line, or wherein the annular midplane includes a polyhedral prism shape and the meridian includes a polygonal line.

10. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifices are geometrically consistent with at least one of the following: A corresponding one of the one or more detonation chamber walls, the corresponding one of the one or more detonation chamber walls circumferentially surrounding the longitudinal axis of the detonation chamber; The detonation manifold wall is circumferentially surrounding the longitudinal axis of the detonation chamber; as well as The meridian.

11. The detonation combustion system according to claim 1, characterized in that, in, The plurality of detonation orifices are uniformly spaced around a geometric perimeter defined by the plurality of detonation orifices, the uniform spacing including at least one of the following: equidistant spacing and proportional spacing.

12. The detonation combustion system according to claim 11, characterized in that, in, The plurality of detonation orifice groups include a first detonation orifice group comprising a plurality of first detonation orifices and a second detonation orifice group comprising a plurality of second detonation orifices; and The plurality of first detonation orifices are evenly spaced apart from each other by a first set of inner perimeter intervals, and the plurality of second detonation orifices are evenly spaced apart from each other by a second set of inner perimeter intervals, wherein the second set of inner perimeter intervals is different from the first set of inner perimeter intervals.

13. The detonation combustion system according to claim 12, characterized in that, in, The corresponding first detonation orifice in the plurality of first detonation orifices is evenly spaced from the adjacent second detonation orifices in the plurality of second detonation orifices by the inter-group perimeter interval.

14. The detonation combustion system according to claim 1, characterized in that, in, The detonation manifold includes a plurality of manifold conduits defined by the overall structure of the detonation manifold, wherein the plurality of manifold conduits respectively define at least a portion of a corresponding one of the plurality of detonation fluid paths; The respective manifold catheters in the plurality of manifold catheters include at least one of the following: A distribution chamber, the distribution chamber being defined by the overall structure of the detonation manifold, the distribution chamber having an annular or semi-annular structure; as well as Multiple outlet conduits, the multiple outlet conduits leading to a corresponding detonation orifice among the multiple detonation fluid paths corresponding to a corresponding one of the multiple detonation fluid paths.

15. The detonation combustion system according to claim 1, characterized in that, in, The detonation chamber and / or the detonation manifold have a structure including at least one of the following: annular elliptical structure, annular cylindrical structure, and annular polyhedral structure.

16. The detonation combustion system according to claim 1, characterized in that, in, The multiple detonation fluid paths include: A first detonation fluid path, wherein the first detonation fluid path is in fluid communication with the detonation chamber through a plurality of first detonation orifices corresponding to a first detonation orifice group in the plurality of detonation orifice groups; and The second detonation fluid path is in fluid communication with the detonation chamber through a plurality of second detonation orifices corresponding to the second detonation orifice group in the plurality of detonation orifice groups.

17. The detonation combustion system according to claim 16, characterized in that, in, The first detonation fluid path is configured to supply a first detonation fluid to the detonation chamber through the plurality of first detonation orifices, and wherein the second detonation fluid path is configured to supply a second detonation fluid to the detonation chamber through the plurality of second detonation orifices, wherein the first detonation fluid is different from the second detonation fluid, and wherein the first detonation fluid and the second detonation fluid each comprise at least one of the following: oxidant, fuel, coolant, and purge air.

18. A detonation manifold for a detonation burner, characterized in that, The detonation manifold includes: Multiple detonation fluid paths defined by the overall structure of the detonation manifold, and multiple detonation orifice groups, each including multiple detonation orifices disposed around the surface of the detonation manifold; Wherein, a corresponding detonation orifice group in the plurality of detonation orifice groups provides fluid communication with a corresponding one of the plurality of detonation fluid paths through a plurality of detonation orifices corresponding to a corresponding one of the plurality of detonation orifice groups; and The plurality of detonation orifices are symmetrically oriented around a reference element of the detonation burner, the reference element comprising at least one of the following: (i) the longitudinal axis of the detonation manifold, (ii) a detonation manifold wall circumferentially surrounding the longitudinal axis, (iii) an annular midplane, and (iv) a meridian located at a longitudinal position along the longitudinal axis, the meridian defining the periphery of at least one of the following: the detonation manifold wall and the annular midplane.

19. A method for generating thrust, characterized in that, The method includes: Detonation is performed in the detonation chamber of the detonation burner by detonation fluid flowing through a first detonation fluid path defined at least partially by the integral structure of the detonation manifold of the detonation burner, the detonation chamber being defined by one or more detonation chamber walls, the first detonation fluid path being in fluid communication with the detonation chamber through a first detonation orifice group comprising a plurality of first detonation orifices; and Detonation is performed in the detonation chamber using detonation fluid flowing to the detonation chamber through a second detonation fluid path defined at least partially by the integral structure of the detonation manifold, the second detonation fluid path being in fluid communication with the detonation chamber through a second detonation orifice group comprising a plurality of second detonation orifices; The plurality of first detonation orifices and the plurality of second detonation orifices are symmetrically oriented about a reference element of the detonation burner, the reference element comprising at least one of the following: (i) the longitudinal axis of the detonation chamber or the detonation manifold, (ii) a corresponding one of the one or more detonation chamber walls, (iii) the detonation manifold wall, (iv) an annular midplane, and (v) a meridian located at a longitudinal position along the longitudinal axis of the detonation chamber or the detonation manifold, the meridian defining the periphery of at least one of the one or more detonation chamber walls, the detonation manifold wall, and the annular midplane.

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