Gas turbine engine combustor

Abstract

An annular combustor includes a liner, a case outside the liner, a first plurality of dilution ports, each of the first plurality of dilution ports defined by one or more internal sidewalls of the liner, and a second plurality of cold-side scoops, each of the second plurality of cold-side scoops respectively integrated with a corresponding dilution port of the first plurality of dilution ports, where each of the second plurality of cold-side scoops has a leading edge that is configured to be oriented perpendicular to a predetermined directional component of a compressor exit flow, and the annular combustor is configured to receive the compressor exit flow from a centrifugal compressor.

Description

Attorney Docket No. BEEHI-1028PCTGAS TURBINE ENGINE COMBUSTORCROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application for patent claims priority to and the benefit of provisional patent application number 63 / 739,406 entitled “GAS TURBINE ENGINE COMBUSTOR” filed in the United States Patent and Trademark Office on December 27, 2024, the entire content of which is incorporated herein by reference as if fully set forth below in its entirety and for all applicable purposes.TECHNICAL FIELD

[0002] Aspects described herein are generally related to gas turbine engines and are more particularly related to a gas turbine engine combustor.BACKGROUND

[0003] Each gas turbine engine includes a plurality of combustors. Each combustor includes an inlet and an outlet. The plurality of combustors encircles a shaft of the gas turbine engine. The shaft is centered on a longitudinal axis of the gas turbine engine and rotates about the longitudinal axis. Coupled to the shaft, ahead of the combustors, are a series of blades that are configured as an axial compressor. The blades that are coupled to the shaft spin with the shaft; these spinning blades are referred to as rotors herein. Between adjacent rotors there may be other blades that remain stationary relative to the spinning shaft and the rotors of the axial compressor. The blades that remain stationary relative to the shaft and the rotors are referred to as stators herein. The axial compressor compresses air flowing axially through the axial compressor, parallel to the longitudinal axis of the gas turbine engine. Ambient air enters the gas turbine engine at a first end of the compressor and is increasingly compressed as the air passes from rotor to stator to rotor and so on along the axis of the gas turbine engine. High-pressure compressed air exits the compressor at a second end of the compressor. The high-pressure compressed air is applied to the inlets of the plurality of combustors. After mixing with fuel, the high-pressure compressed air is ignited and burned in each of the plurality of combustors. The burning air in each combustor expands and is expelled from the outlet of each combustor. The expanded high-Attorney Docket No. BEEHI-1028PCTpressure exhaust gas from the outlet of each combustor is applied to the blades of a turbine. The turbine includes a plurality of rotating turbine blades and a plurality of stationary turbine blades (also referred to as nozzle guide vanes or turbine vanes) at a turbine inlet. The rotating blades of the turbine are coupled to the shaft following the combustors. The energy imparted to the rotating turbine blades spins the shaft, which, because they are also coupled to the shaft, spins the rotors of the axial compressor. The more complete the combustion of the fuel-air mixture in each combustor, the greater the efficiency of the gas turbine engine.

[0004] Combustors play an important role in maximizing the efficiency of the combustion process by mixing cold air with hot combustion gases. Scientists and engineers continue searching for more efficient mixing of the cold air with the hot combustion gases to improve the efficiency of gas turbine engines.BRIEF SUMMARY OF SOME EXAMPLES

[0005] The following summary is provided to facilitate an understanding of some of the innovative features unique to the embodiments disclosed and is not intended to be a full description. A full appreciation of the various aspects of the embodiments can be gained by taking the entire specification, claims, drawings, and abstract as a whole.

[0006] An annular combustor is described. The annular An annular combustor includes:a liner; a case outside the liner; a first plurality of dilution ports, each of the first plurality of dilution ports defined by one or more internal sidewalls of the liner; and a second plurality of cold-side scoops, each of the second plurality of cold-side scoops respectively integrated with a corresponding dilution port of the first plurality of dilution ports, wherein each of the second plurality of cold-side scoops has a leading edge that is configured to be oriented perpendicular to a predetermined directional component of a compressor exit flow, and the annular combustor is configured to receive the compressor exit flow from a centrifugal compressor.

[0007] An annular combustor is described. The annular combustor is configured to be fed with compressed air exiting a centrifugal compressor. The annular combustor includes: a plurality of dilution ports, one or more cold-side scoops, each formed with a dilution port of the plurality of dilution ports, wherein a leading edge of each of the one or more cold-side scoops is configured to be perpendicular to a compressor exit flow with a swirl induced by the centrifugal compressor, wherein the compressor exitAttorney Docket No. BEEHI-1028PCTflow with the swirl flows over a surface of the annular combustor, and wherein the leading edge of each of the one or more cold-side scoops associated with a respective dilution port is configured to be perpendicular to a directional component of the compressor exit flow with the swirl.BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The accompanying figures, in which like reference numerals refer to identical or functionally similar elements throughout the separate views and which are incorporated in and form an object of the specification, further illustrate the examples and, together with the detailed description, serve to explain the aspects disclosed herein.

[0009] FIG. 1 is a side view cross-section of a gas turbine engine according to some aspects of the disclosure.

[0010] FIG. 2 is a side view cross-section of a combustor, similar to any combustor of the plurality of combustors as illustrated and described in connection with FIG. 1, according to some aspects of the disclosure.

[0011] FIG. 3 is a side view cross-section of a combustor, similar to any combustor of the plurality of combustors as illustrated and described in connection with FIG. 1 and / or FIG. 2, according to some aspects of the disclosure.

[0012] FIG. 4 is a cut-away side view of the combustor of FIG. 3 according to some aspects of the disclosure.

[0013] FIG. 5 is a top-right perspective view of a section of a liner, including a dilution port and a cold-side scoop similar to the dilution port and cold-side scoop as shown and described in connection with FIGs. 3 and 4, according to some aspects of the disclosure.

[0014] FIG. 6 is a bottom-right perspective view of the section of a liner, including the dilution port as shown and described in connection with FIG. 5, and making visible a hot-side plunging, according to some aspects of the disclosure.

[0015] FIG. 7 is a top view of the section of the liner of FIG. 5 including the dilution port, and the cold-side scoop, as shown in FIGs. 5 and 6, according to some aspects of the disclosure.Attorney Docket No. BEEHI-1028PCT

[0016] FIG. 8 is a side view cross-section of the section of the liner depicted in FIGs. 5, 6, and 7, according to some aspects of the disclosure.

[0017] FIG. 9 is a bottom view of the section of the liner depicted in FIGs. 5, 6, 7, and 8 according to some aspects of the disclosure.

[0018] FIG. 10 is a side view of an outer surface of a liner of a foldback combustor of a gas turbine engine, according to some aspects of the disclosure.

[0019] FIG. 12 is a side view cross-section of an outside surface of a liner of an axial combustor of a gas turbine engine, according to some aspects of the disclosure.

[0020] FIG. 12 is a top view of the outside surface of the liner of the annular combustor of the gas turbine engine of FIG. 12, according to some aspects of the disclosure.

[0021] FIG. 13 is a side view cross-section of a portion of an annular combustor according to some aspects of the disclosure.

[0022] FIG. 14 is the side view cross-section of the portion of the annular combustor of FIG. 13 identifying a first row of dilution ports, a second row of dilution ports, and a row of primary ports, according to some aspects of the disclosure.

[0023] FIG. 15 is an enlarged view of a portion of the side view cross-section of the portion of the annular combustor of FIG. 13, according to some aspects of the disclosure.

[0024] FIG. 16 is a cut-away view of the annular combustor of FIG. 13, according to some aspects of the disclosure.DETAILED DESCRIPTION

[0025] The particular values and configurations discussed in the following non-limiting examples can be varied and are cited merely to illustrate one or more examples and are not intended to limit the scope thereof.

[0026] Examples will now be described more fully hereinafter with reference to the accompanying drawings. The examples disclosed herein can be modified within the scope of this disclosure and should not be construed as limiting; instead, these examples are provided so that this disclosure will be thorough and complete and fully convey the scope of the disclosure to persons of ordinary skill in the art. Like numbers refer to like elements throughout.

[0027] The detailed description set forth below in connection with the appended drawings is intended as a description of various configurations and is not intended to representAttorney Docket No. BEEHI-1028PCTthe only configurations in which the concepts described herein may be practiced. The detailed description includes specific details for the purpose of providing a thorough understanding of various concepts. However, it will be apparent to persons having ordinary skill in the art that these concepts may be practiced without these specific details. In some examples, well-known structures and components are shown in block diagram form in order to avoid obscuring such concepts.

[0028] The terminology used herein is for the purpose of describing particular examples only and is not intended to be limiting. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprise” and / or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and / or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0029] Throughout the specification and claims, terms may have nuanced meanings suggested or implied in context beyond an explicitly stated meaning. Likewise, the phrase “in one example” as used herein does not necessarily refer to the same example and the phrase “in another example” as used herein does not necessarily refer to a different example. It is intended that the scope of disclosure may encompass the subject matter of one or more examples in whole or in part.

[0030] Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art. It will be further understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning that is consistent with their meaning in the context of the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein.

[0031] It will be understood that particular examples described herein are shown by way of illustration and not as limitations. Aspects described herein can be employed in various examples without departing from the scope of the disclosure. Those skilled in the art will recognize or be able to ascertain using no more than routine experimentation, numerous equivalents to the specific aspects and procedures described herein. Such equivalents are considered to be within the scope of this disclosure and are covered by the claims.Attorney Docket No. BEEHI-1028PCT

[0032] The use of the word “a” or “an” when used in conjunction with the term “comprising” in the claims and / or the specification may mean “one,” but it is also consistent with the meaning of “one or more,” “at least one,” and “one or more than one.” The use of the term “or” in the claims is used to mean “and / or” (e.g., A and / or B contemplates A and B, or A, or B) unless explicitly indicated to refer to alternatives only or the alternatives are mutually exclusive, although the disclosure supports a definition that refers to only alternatives and “and / or.” Throughout this application, the term “about” is used to indicate that a value includes the inherent variation of error for the device, the method being employed to determine the value, or the variation that exists among the study subjects.

[0033] As used in this specification and claim(s), the words “comprising” (and any form of comprising, such as “comprise” and “comprises”), “having” (and any form of having, such as “have” and “has”), “including” (and any form of including, such as “includes” and “include”) or “containing” (and any form of containing, such as “contains” and “contain”) are inclusive or open-ended and do not exclude additional, unrecited elements or method steps.

[0034] The term “or combinations thereof” as used herein refers to all permutations and combinations of the listed items preceding the term. For example, “A, B, C, or combinations thereof” is intended to include at least one of: A, B, C, AB, AC, BC, or ABC, and if order is important in a particular context, also BA, CA, CB, CBA, BCA, ACB, BAC, or CAB. Continuing with this example, expressly included are combinations that contain repeats of one or more item or term, such as BB, AAA, AB, BBC, AAABCCCC, CBBAAA, CABABB, and so forth. The skilled artisan will understand that typically there is no limit on the number of items or terms in any combination, unless otherwise apparent from the context.

[0035] All of the aspects disclosed and claimed herein can be made and executed without undue experimentation in light of the present disclosure. While the aspects have been described in terms of preferred examples, it will be apparent to those of skill in the art that variations may be applied to the aspects described herein without departing from the concept, spirit, and scope of the disclosure and claims. All such similar substitutes and modifications apparent to those skilled in the art are deemed to be within the spirit, scope, and concept of the disclosure as defined by the appended claims.Attorney Docket No. BEEHI-1028PCT

[0036] Described herein are various examples of structures that may be configured to take advantage of a swirling motion of air to maximize a recapture of dynamic pressure from the swirling air (which is fed into a combustion chamber) according to some aspects of the disclosure. The scope if this disclosure includes combustors (and other components of a gas turbine engine that may be 3D printed using metal powder. In general, the combustor includes an outer casing and an inner liner within the outer casing. The combustor may be divided into three zones. A first zone may be referred to as a primary zone. A second zone may be referred to as an intermediate zone. A third zone may be referred to as a dilution zone. The primary zone begins at a snout of a combustor and receives compressed air from a compressor of a gas turbine engine. The dilution zone ends at the combustor outlet, which is coupled to a turbine inlet. The intermediate zone lies between the primary zone and the dilution zone. There are amorphous boundaries (e.g., having no definite form, invisible, non- physically defined (e.g., by a wall)) between the primary zone and the intermediate zone, and between the intermediate zone and the dilution zone. The three zones are useful in the discussion of processes occurring within them. Prior to discussing an exemplary combustor in more detail, it may be useful to identify where a combustor is situated in, for example, a gas-turbine engine.

[0037] FIG. 1 is a side view cross-section of a gas turbine engine 100 according to some aspects of the disclosure. Gas turbine engines may also be referred to as a jet engine or a turbojet engine. The gas turbine engine 100 of FIG. 1 is not drawn to scale, nor are all of the components of the gas turbine engine 100 presented. Those components that are presented are not necessarily shaped or even configured as the components they represent, rather, they are presented only for purposes of discussion and general identification of the components of a gas turbine engine.

[0038] A three axis coordinate system having an X axis (pointing into the plane of the figure) a Y axis (pointing up) and a Z axis (extending from an origin at a front of the gas turbine engine 100 and pointing toward a rear of the gas turbine engine 100) are shown for purposes of describing the orientation of the components of the gas turbine engine 100. The same three axis system is utilized in all the drawings attached hereto.

[0039] Air and exhaust gases, such as the ambient air 106, initial compressed air 140, high-pressure compressed air 142, and high-velocity, high-pressure engine exhaust gas 110, flowing into, through, and out of, respectively, the gas turbine engine 100 isAttorney Docket No. BEEHI-1028PCTrepresented in FIG. 1 using open ended arrows. The length, width, quantity, and density of the open ended arrows is not meant to indicate pressure or velocity. The open ended arrows are only provided to illustrate, in a non-limiting way for the purpose of discussion, a general direction of the air flowing in the vicinity of the open ended arrows. Closed ended arrows point toward areas, regions, zones, spaces, components, or aspects that are identified and described using reference numbers in the drawings.

[0040] The gas turbine engine 100 includes a housing 102 within which the components of the gas turbine engine 100 are enclosed. At a front of the housing 102 of the gas turbine engine 100 is a housing inlet 104. Ambient air 106 is ingested into the housing 102 through the housing inlet 104. At a rear of the housing 102, distal from the housing inlet 104, is a nozzle 109. High-velocity, high-pressure engine exhaust gas 110 exits the housing 102 through the nozzle 109.

[0041] Also enclosed within the housing 102 is an axial compressor 112, a centrifugal compressor 114, a plurality of combustors 126, a turbine 128, and a shaft 130. The axial compressor 112 may include a plurality of fan blades that include rotating axial compressor blades 132, which may be referred to as rotors, and stationary axial compressor blades 134, which may be referred to as stators. The plurality of rotating axial compressor blades 132 may be coupled to a spindle 136. The spindle 136 may be coupled to the shaft 130 at a shaft end that is proximal to the housing inlet 104. Nothing herein precludes any examples in which the spindle 136 and shaft 130 are integrally formed as one piece.

[0042] In the example of FIG. 1 , the spindle 136 may be coupled to the shaft 130 and may be free to rotate with the shaft 130 about a central longitudinal axis parallel to the Z axis. A cone 138 may cap the spindle 136 at a spindle end that is proximal to the housing inlet 104. The shape of the cone 138 may be selected based on a plurality of factors including, for example, aerodynamic factors. The stationary axial compressor blades 134 are stationary relative to the rotating axial compressor blades 132. Mounting structures to which the stationary axial compressor blades 134 are mounted are omitted to avoid cluttering the drawing.

[0043] The spindle 136 has a first diameter at a first spindle end proximal to the housing inlet 104 and a second diameter at a second spindle end distal from the housing inlet 104. The second diameter may be greater than the first diameter. As the diameterAttorney Docket No. BEEHI-1028PCTincreases, there is less space between an outer surface of the spindle 136 and an inner surface of the housing 102. The ambient air 106 that enters the housing inlet 104 is pulled into the axial compressor 112 by a first plurality of rotating axial compressor blades 132 and moved along toward the centrifugal compressor 114 through alternate ones of the plurality of stationary axial compressor blades 134 and the remaining plurality of rotating axial compressor blades 132. As each quantity of air is passed toward the centrifugal compressor 114, the spatial volume bounded by adjacent pairs of the rotating axial compressor blades 132 and the stationary axial compressor blades 134, the inner wall of the housing 102, and the outer wall of the spindle 136 grows smaller. As the spatial volume grows smaller the air within that volume is compressed. Ultimately, the ambient air 106 that entered axial compressor 112 at an end proximal to the housing inlet 104 is compressed into an initial compressed air 140 that exits the axial compressor 112 at the end distal from the housing inlet 104.

[0044] The initial compressed air 140 that exits the axial compressor 112 is applied to an inlet 116 of the centrifugal compressor 114. The inlet 116 may be configured to guide the initial compressed air 140 into the impeller 118 of the centrifugal compressor 114. The rotating blades of the impeller 118 accelerate the initial compressed air 140 radially outward, increasing its kinetic energy and velocity. The higher velocity air exits the centrifugal compressor 114 via a centrifugal compressor outlet 122 and is passed through a diffuser 124. The diffuser 124 converts the high-velocity air from the impeller 118 into pressure by slowing the air. The diffuser 124 may be vaned (e.g., with stationary blades) or vaneless.

[0045] The high-pressure compressed air 142 exits the diffuser 124 and is fed to a combustor inlet 146 of a plurality of combustors 126. As used herein, the plurality of combustors 126 are represented individually or collectively by a combustor 144. In the example of FIG. 1 , the combustor 144 receives the high-pressure compressed air 142 generated by the series combination of the axial compressor 112 and the centrifugal compressor 114. The combustor 144 receives the high-pressure compressed air 142 through the combustor inlet 146. A system of ductwork / manifolds that guide the high- pressure compressed air 142 from the centrifugal compressor outlet 122 of the centrifugal compressor 114 through the diffuser 124 and to the combustor inlet 146 is omitted and / or simplified to avoid cluttering the drawing.Attorney Docket No. BEEHI-1028PCT

[0046] Some details related to combustors, which may be the same or similar to the combustor 144 as described and illustrated in connection with FIG. 1 , will be explained below. In general, the combustor 144 includes an outer casing (referred to herein as the casing 148) and an inner liner (referred to herein as the liner 150) within the casing 148. Some of the high-pressure compressed air 142 that enters the combustor inlet 146 enters a combustion zone 152 within the combustor 144 through a combustor snout 154. The high-pressure compressed air 142 that enters the combustion zone 152 may be mixed with fuel and ignited. The burning fuel-air mixture creates heat, expands, and exits the combustor 144 as high-velocity, high-pressure combustor exhaust gas 156 through a combustor outlet 111.

[0047] The combustor outlet 111 directs the high-velocity, high-pressure combustor exhaust gas 156 to the turbine 128 via a turbine inlet (not shown to avoid cluttering the drawing). The turbine 128 includes a plurality of turbine blades 160, including one or more turbine stationary blades 162 (also referred to as nozzle guide vanes or turbine vanes) and one or more turbine rotating blades 164. The one or more turbine rotating blades 164 are coupled to the shaft 130 via a turbine hub 166. The high-velocity, high- pressure combustor exhaust gas 156 passing through the plurality of turbine blades 160 causes the turbine rotating blades 164 to rotate the shaft 130 (via their coupling through the turbine hub 166 to the shaft 130). The high-velocity, high-pressure combustor exhaust gas 156 that has passed through the plurality of turbine blades 160 exits the housing 102 through the nozzle 109 as high-velocity, high-pressure engine exhaust gas 110.

[0048] FIG. 2 is a side view cross-section of a combustor 200, similar to any combustor of the plurality of combustors 126 as illustrated and described in connection with FIG.1 , according to some aspects of the disclosure. The combustor 200 includes an outer casing (referred to herein as the casing 202) and an inner liner (referred to herein as the liner 204) within the casing 202. The combustor 200 includes a combustor inlet 206 at a first side of the combustor 200 and a combustor outlet 211 at a second side of the combustor 200, distal from the combustor inlet 206. The combustor 200 is configured to receive high-pressure compressed air 210 (similar to the high-pressure compressed air 142 as shown and described in connection with FIG. 1) into the combustor inlet 206 and expel high-velocity, high-pressure combustor exhaust gas 212 (similar to the high-velocity, high-pressure combustor exhaust gas 156 as shownAttorney Docket No. BEEHI-1028PCTand described in connection with FIG. 1) from the combustor outlet 211. The high- velocity, high-pressure combustor exhaust gas 212 is directed toward a turbine inlet 216.

[0049] Air and gases flowing into, through, and out of the combustor 200 are represented in FIG. 2 using open ended arrows. The length, width, quantity, and density of the open ended arrows is not meant to indicate pressure or velocity. The open ended arrows are only provided to illustrate, in a non-limiting way for the purpose of discussion, a general direction of the air flowing in the vicinity of the open ended arrows. Closed ended arrows point toward areas, regions, zones, spaces, components, or aspects that are identified and described using reference numbers in the drawings.

[0050] Within the liner 204 there exists a combustion zone 214 in which a fuel-air mixture combusts. The liner 204 may include a dome 220 (e.g., a wall shaped as a dome or some other shape) spaced apart from but proximal to the snout 218. Circumferential edges of the dome 220 may be coupled to the circumference of the liner 204 (if the liner 204 has a cylindrical shape, for example). Thus, the combustion zone 214 may be defined by the interior surface (e.g., the interior wall) of the dome 220 and the interior surface (e.g., the interior wall) of the liner 204 beginning at a seam, border, or juxtaposition of the dome 220 and the liner 204 and extending along the longitudinal length of the liner 204 in the positive Z axis direction to an edge of the combustor outlet 211. The interior of the liner 204 may be divided into three zones.

[0051] A first zone may be referred to as a primary zone 222. A second zone may be referred to as an intermediate zone 224. A third zone may be referred to as a dilution zone 226. The primary zone 222 may begin at the snout 218 of the combustor 200 and may be configured to receive (e.g., accept) the high-pressure compressed air 210 that is received at the snout 218 according to some aspects. The dilution zone 226 may end at the combustor outlet 211, which is coupled to a turbine inlet 216. The intermediate zone 224 lies between the primary zone 222 and the dilution zone 226. There are amorphous boundaries (e.g., having no definite form, invisible, non- physically defined (e.g., by a wall)) between the primary zone 222 and the intermediate zone 224, and between the intermediate zone 224 and the dilution zone 226. Various processes may occur in each zone or in any combination of two or more of the threeAttorney Docket No. BEEHI-1028PCTzones. Dividing the liner 204 into three zones may be useful in the discussion of processes occurring within any one or any combination of two or three of the zones.

[0052] Some of the high-pressure compressed air 210 received into the combustor inlet 206 may flow into the snout 218 (e.g., an opening defined by side walls of the mouth / entrance to the liner 204) that leads to the combustion zone 214. Before entering the combustion zone 214, the high-pressure compressed air 210 may be passed through a structure configured to cause the high-pressure compressed air 210 to swirl about within the primary zone 222. The swirling may be in a turbulent manner. The structure configured to cause the swirling may be referred to as a swirler 228.

[0053] Fuel 230 may be injected into the primary zone 222 from a fuel injector 232. Several types of fuel injectors are available, and all are within the scope of this disclosure. For example, and without limitation, the fuel injector 232 may be a pressure-atomizing injector, an air blast injector, a vaporizing injector, or a premix / pre-vaporizing injector. A fuel storage and delivery system associated with the fuel injector 232 is not shown to avoid cluttering the drawing.

[0054] The fuel 230 may mix with the swirling high-pressure compressed air 210 within the primary zone 222 within the liner 204. Counter rotating spiraling open ended arrows may be used herein to represent the swirling high-pressure compressed air 210, the swirling fuel 230, or the combination (the mixture) of the swirling high- pressure compressed air 210 and swirling fuel 230 according to some aspects of the disclosure. Additionally, the counter rotating spiraling open ended arrows may be used to represent the fuel-air mixture before or during ignition and burning of the fuel-air mixture.

[0055] The fuel-air mixture may be ignited and burned (or may be ensured to be maintained in an ignited and burning state) by a device referred to herein as an ignitor (not shown to avoid cluttering the drawing). According to some aspects, the ignitor (not shown) may protrude into the primary zone 222 (within the liner of the combustor 200). According to some aspects, the ignitor (not shown) may cause or may emit an electrical spark to ignite the fuel-air mixture or to ensure that the fuel-air mixture remains ignited.

[0056] The primary zone 222 may be configured to, among other things, encourage stable ignition of the swirling fuel-air mixture and efficient combustion of the fuel 230 within the fuel-air mixture. The temperature of the burning fuel-air mixture within the primaryAttorney Docket No. BEEHI-1028PCTzone 222 is very high. For example, unless the temperature of the high-velocity, high- pressure combustor exhaust gas 212 emitted from the dilution zone 226 through the combustor outlet 211 is reduced to a value that is less than the value of the temperature in the primary zone 222, the high-velocity, high-pressure combustor exhaust gas 212 passed into the turbine inlet 216 may reach levels that can damage the blades of a turbine (e.g., the turbine 128 of FIG. 1).

[0057] Not all of the high-pressure compressed air 210 entering the combustor inlet 206 is drawn into the snout 218 of the combustor 200. A portion of the high-pressure compressed air 210 that is drawn into the snout 218 of the combustor 200 may be drawn into the primary zone 222, and subsequently into the combustion zone 214, which may include the intermediate zone 224 and the dilution zone 226. A portion of the high-pressure compressed air 210 that is not drawn into the snout 218 may flow into a space 234 defined between facing walls of an interior surface of the casing 202 of the combustor 200 and an exterior surface of the liner 204 of the combustor 200. In the example of FIG. 2, the combustor 200 has axial symmetry around a central longitudinal axis (and parallel or coaxial with the Z-axis), where the central longitudinal axis is coaxial with a center of the combustor 200 in the X-Y plane perpendicular to the Z axis as illustrated in FIG. 2). Accordingly, while the space 234 is identified in the illustration of FIG. 2 in what may appear to be an upper corridor, due to the axial symmetry, the space 234 exists between the casing 202 and the liner 204 and surrounds the liner 204.

[0058] The air entering the space 234 is colder than any of the burning air in the primary zone 222, the intermediate zone 224, and the dilution zone 226 within the liner 204. According to some aspects, the cold air in the space 234 may be used to cool the interior walls of the liner 204 of the combustor 200. According to some aspects, the cold air in the space 234 may be used to generate swirling of any fuel-air mixture (burning or not burning) within the dilution zone 226. The inducing of swirling into the dilution zone 226 improves the mixing of unburnt fuel and air in the dilution zone 226 and may improve the degree to which all fuel is consumed in the combustor 200 by creating an area of high turbulence that may cause some combustion products to recirculate and be burnt.

[0059] According to some aspects, several openings that penetrate the liner 204 and are defined by sidewalls of the liner 204 within the openings, may be provided to introduceAttorney Docket No. BEEHI-1028PCTthe colder air of the space 234 into the relatively hotter interior of the liner 204 of the combustor 200.

[0060] For example, first openings in the liner 204 may be positioned within or adjacent to the primary zone 222 and may be referred to as primary ports 236 (or primary openings), where each primary port 236 is defined by sidewalls formed in a thickness dimension of the liner 204. The primary ports 236 may be configured to admit primary air (i.e. , the main combustor air) into the interior of the liner within the primary zone 222. The primary air may also be admitted into the primary zone 222 via a plurality of smaller openings (e.g., small holes) in the dome 220. The primary air may be considered as the main combustion air. The primary air is mixed with fuel in the primary zone 222 and then ignited. Although not illustrated to avoid cluttering the drawing, intermediate air may be admitted into the combustion zone 214 via intermediate ports located in wall of the liner 204 within the intermediate zone 224. The combustor 200 may use the intermediate air to further the combustion process. Additionally, the intermediate air may be used to cool the gases formed by the combustion of the fuelair mixture in the combustion zone 214.

[0061] Second openings in the liner 204 may be positioned within or adjacent to the intermediate zone 224 and may each be referred to as a cooling slot 240, where each cooling slot 240 is defined by the walls of an upper embossment 238 and a lower embossment 242. Cooling air admitted through the cooling slot 240 may form a thin film or layer of cooling air adjacent to the inner surface of the liner 204. This thin film or layer of cooling air admitted through the cooling slot 240 may act as a protective layer to protect the surfaces of the liner 204 from the heat of combustion in the combustion zone 214 (and within at least the intermediate zone 224). The use of the cooling slot 240 and the admission of cooling air to form the protective layer is carefully implemented so that the cooling air does not interact with the combustion air (i.e., primary air and intermediate air) or interact with the combustion process in the combustion zone 214. The physical implementation of the cooling slot 240 represents one non-limiting example of a way to introduce cooling air to protect the interior surface of the liner 204 (and not to affect, interfere with, or interact with the combustion air).

[0062] Third openings in the liner 204 may be positioned within or adjacent to the dilution zone 226 and may each be referred to as a dilution port 244 (or dilution openings), where each dilution port 244 is defined by sidewalls formed in the thickness dimensionAttorney Docket No. BEEHI-1028PCTof the liner 204. Each dilution port 244 may admit dilution air to the dilution zone 226. The dilution air may be used to cool the flue gas (e.g., the high-velocity, high-pressure combustor exhaust gas 212) before it reaches the turbine inlet 216. Therefore, rather than serving to improve the mixing of unburnt combustion products in the combustion zone 214, the dilution air may be used to produce a desired temperature profile associated with the high-velocity, high-pressure combustor exhaust gas 212 output from the combustor 200.

[0063] In the example of FIG. 2, the spiral counter rotating solid closed arrows depict a turbulent quality of the fuel-air mixture in the primary zone 222, which transitions to a less turbulent more linear flow of the combustion gases as they are burnt in the combustion zone 214 and receive additional primary air through the primary ports 236 (and intermediate air through the intermediate ports, not shown) all as the combustion process proceeds toward the combustor outlet 211. The example of FIG. 2 also illustrates the use of cooling air admitted through cooling slots 240 to form a thin protective layer of cooling air adjacent to the interior surfaces of the liner 204, to protect the interior surfaces of the liner 204, at least within the intermediate zone 224, from the hot combustion gases in the combustion zone 214. In the illustration, the cooling air admitted through the cooling slots 240 is deliberately illustrated to show the lack of interaction between the cooling air adjacent to the interior surfaces of the liner 204 and the combustion air within the greater interior volume of the liner 204 in the combustion zone 214. Finally in the example of FIG. 2, the dilution air admitted into the combustion zone 214 through each dilution port 244 is also depicted as not inducing a turbulent flow of the hot combustion gases in the combustion zone 214 and, although not depicted graphically, are in fact serving to produce a desired temperature profile associated with the high-velocity, high-pressure combustor exhaust gas 212 output from the combustor outlet 211.

[0064] In the example of FIG. 2, projections referred to herein as hot-side plungings 246 are depicted as extending circumferentially around each dilution port 244 and inwardly toward the center axis of the combustor 200.

[0065] In some examples, the combustor 200, including at least the casing 202, the liner 204, the dome 220, the primary port 236, the cooling slot 240, the dilution port 244, and the hot-side plunging 246 may be integrally fabricated as one unit (e.g., fabricatedAttorney Docket No. BEEHI-1028PCTas a continuous single unit) utilizing a 3D printing process performed by a 3D printer according to some aspects of the disclosure.

[0066] FIG. 3 is a side view cross-section of a combustor 300, similar to any combustor of the plurality of combustors as illustrated and described in connection with FIG. 1 and / or FIG. 2, according to some aspects of the disclosure. The reference numbers in FIG. 3 that correspond to the reference numbers in FIG. 2 describe the same or similar hardware and functions. Their descriptions will not be repeated for the sake of brevity.

[0067] Air and gases flowing into, through, and out of the 300 combustor are represented in FIG. 3 using open ended arrows. The length, width, quantity, and density of the open ended arrows is not meant to indicate pressure or velocity. The open ended arrows are only provided to illustrate, in a non-limiting way for the purpose of discussion, a general direction of the air flowing in the vicinity of the open ended arrows. Closed ended arrows point toward areas, regions, zones, spaces, components, or aspects that are identified and described using reference numbers in the drawings.

[0068] In FIG. 3, the plurality of dilution ports are represented by a dilution port 302 (as opposed to the dilution port 244 in FIG. 2). The dilution port 302 includes a hot-side plunging 306 (the same or similar to the hot-side plunging 246 as shown and described in connection with FIG. 2). A height, measured from a base of a hot-side plunging 306 toward a longitudinal axis of the combustor 300, may be shorter than or longer than the height represented in FIG. 3.

[0069] The dilution port 302 also includes a structure, referred to herein as a cold-side scoop 308. The identifier “cold-side” is used to reflect the location of the structure, which is located adjacent to the dilution port 302 on the outer or exterior surface of the liner 204, within the space 234 into which cold air (relative in temperature to the hot combustion gases in the interior of the liner 204) from a compressor (not shown, but similar to the axial compressor 112 and / or the centrifugal compressor 114, both as shown and described in connection with FIG. 1) is received. Accordingly, the structure (i.e., the cold-side scoop 308) is located outside of the liner 204, on the “cold-side” of the liner 204, as opposed to being located inside of the liner 204, on the (relatively) “hot-side” of the liner 204.

[0070] The term “scoop” may be used to describe a function of the structure, which “scoops” (e.g., captures, collects) the high-pressure compressed air 210 travelingAttorney Docket No. BEEHI-1028PCTlongitudinally within the space 234 and converts a longitudinal velocity of the high- pressure compressed air 210 into a tangential velocity (e.g. , a velocity of the air moving along the curved path in the interior of the cold-side scoop 308 structure, a directional component of the velocity that is tangent to the internal curvature of the cold-side scoop 308 structure) and then into a linearly inward velocity that is directed toward (e.g., perpendicular to) the longitudinal axis (the Z axis) of the combustor 300. The linearly inward velocity vector may be likened to a “radial,” which as used herein may be analogized to a spoke of a bicycle wheel. Thus, as used herein, a radial velocity does not refer to a velocity along a radius, but instead refers to a velocity along a ray projecting from the circumferential inner surface of the liner 204 (or, for example, a center of a dilution port 302) toward the longitudinal axis of the combustor 300.

[0071] The cold-side scoop 308 may be configured in any shape that effectively redirects a longitudinal velocity vector of the high-pressure compressed air 210 traveling in the space 234 (e.g., traveling in a direction parallel to the Z axis), in the proximity of or adjacent to the dilution port 302, into a velocity vector directed toward the interior of the liner 204, perpendicular to both the longitudinal axis of the combustor 300 and the longitudinal velocity vector of the high-pressure compressed air 210 traveling in the space 234, in the proximity of or adjacent to the dilution port 302. Accordingly, the cold-side scoop 308 may be configured as structure that effectively causes the direction of the high-pressure compressed air 210 traveling in the space 234, in the proximity of or adjacent to the dilution port 302, to turn by substantially 90 degrees toward the interior of the liner 204.

[0072] According to some aspects, for example to minimize turbulence caused by the substantially right-angle turn, a wall of the cold-side scoop 308 that deflects the high- pressure compressed air 210, in the proximity of or adjacent to the dilution port 302 inward toward the longitudinal axis of the combustor may be a curved wall. The curved wall may convert the longitudinal velocity of the high-pressure compressed air 210 in the space 234, in the proximity of or adjacent to the dilution port 302, to a tangential (curved) velocity traveling in the direction of the curved wall, and then convert the tangential velocity into a direction that is substantially perpendicular to the original longitudinal velocity of the high-pressure compressed air 210.

[0073] In the example of FIG. 3, the cold-side scoop 308 has a shape that is a segment of a sphere. The segment of the sphere may be referred to as a sphere cap. The shapeAttorney Docket No. BEEHI-1028PCTmay have been obtained by dividing the sphere into four equal spherical quadrants using two perpendicular great circles. However, the segment of the sphere is not limited to a quarter of the sphere (not limited to 90 degrees of inclined angle). Any number of degrees of inclined angle is within the scope of the disclosure. In some examples, the cold-side scoop 308 may be configured with 90 degrees or less of inclined angle. Moreover, any shape that converts a longitudinally directed flow of air to a tangentially directed flow of air and then to an inwardly directed flow of air (substantially perpendicular to the longitudinal direction), is within the scope of the disclosure. Additionally, or alternatively, any shape that converts a longitudinally directed flow of air to an inwardly directed flow of air substantially perpendicular to the longitudinal direction with a minimal amount of turbulence, is within the scope of the disclosure.

[0074] The cold air captured by the cold-side scoop 308 is injected into the combustion zone 214 via the dilution port 302. Because of the shape of the cold-side scoop 308, the cold air received in the dilution zone 226 is directed both toward the intermediate zone 224 of the liner 204 and the axial center of the combustor 300 before being turned toward the combustor outlet 211 by the force of the combustion gases traveling toward the combustor outlet 211 from the intermediate zone 224. The inward and rearward (i.e., toward the intermediate zone 224 in the positive direction along the Z-axis) injection of cold air may cause a turbulent flow of the combustion gases in the intermediate zone 224 and the dilution zone 226. The turbulence in the dilution zone 226 may improve the mixing of unburnt combustion products in the dilution zone and promote a complete burning of the compressed air-fuel mixture within the dilution zone 226. The more complete the combustion the greater the engine efficiency.

[0075] In greater detail, the cold-side scoops, represented by the cold-side scoop 308, may convert a longitudinal velocity of air in the space 234 between the interior side of the casing 202 and the exterior side of the liner 204 into a velocity that is perpendicular to the longitudinal velocity and directed toward a longitudinal axis of the combustor 300 (e.g., an axis that runs lengthwise through the center of the combustor 300). According to some aspects, the direction that is perpendicular to the longitudinal velocity may be referred to as a radial velocity. Directing (or redirecting) the longitudinal velocity of air in the space 234 between the interior side of the casing 202 and the exterior side of the liner 204 into a velocity that is perpendicular to theAttorney Docket No. BEEHI-1028PCTlongitudinal velocity and directed toward the longitudinal axis of the combustor 300 may achieve improved mixing of cold air with hot combustion gas in the combustion zone 214 within the dilution zone 226 of the combustor 300. Without improved mixing of the cold air with the hot combustion gas, the combustor 300 may run with poor efficiency, visible smoke, and hot streaks at the turbine inlet 216.

[0076] In some examples, the combustor 300, including at least the casing 202, the liner 204, the dome 220, the primary port 236, the cooling slot 240, the dilution port 302, the hot-side plunging 306, and the cold-side scoop 308 may be integrally fabricated as one unit (e.g., fabricated as a continuous single unit) utilizing a 3D printing process performed by a 3D printer according to some aspects of the disclosure.

[0077] FIG. 4 is a cut-away side view of the combustor 300 of FIG. 3 according to some aspects of the disclosure. The reference numbers in FIG. 4 that correspond to the reference numbers in FIG. 2 and / or FIG. 3 describe the same or similar hardware and functions. Their descriptions will not be repeated for the sake of brevity.

[0078] Air and gases flowing into, through, and out of the combustor 300 is represented in FIG. 4 using open ended arrows. The length, width, quantity, and density of the open ended arrows is not meant to indicate pressure or velocity. The open ended arrows are only provided to illustrate, in a non-limiting way for the purpose of discussion, a general direction of the air flowing in the vicinity of the open ended arrows. Closed ended arrows point toward areas, regions, zones, spaces, components, or aspects that are identified and described using reference numbers in the drawings.

[0079] In the example of FIG. 4, the casing 202 is cut-away to reveal the outer surface of the liner 204. A plurality of primary ports 236 is depicted as surrounding the circumference of, and penetrating through, the liner 204. A plurality of cooling slots 240, each including an upper embossment 238 and a lower embossment 242, is depicted as surrounding the circumference of, and penetrating through, the liner 204. A plurality of dilution ports, including dilution port 302, dilution port 404, and dilution port 406, is depicted as surrounding the circumference of, and penetrating through, the liner 204. A leading edge 402 of the cold-side scoop 308 is depicted as being oriented perpendicular to the longitudinal axis of the combustor 300. High-pressure compressed air 210 is depicted as entering dilution port 302 and dilution port 406; of course, the high-pressure compressed air 210 is also entering the remaining dilutionAttorney Docket No. BEEHI-1028PCTports including dilution port 404, but the path of the high-pressure compressed air 210 entering the remaining dilution ports is omitted to avoid cluttering the drawing.

[0080] In some examples, the combustor 300, including at least the casing 202, the liner 204, the dome 220, the plurality of primary ports represented by the primary port 236, the plurality of cooling slots represented by the cooling slot 240, the plurality of dilution ports represented by the dilution ports 302, 404, and 406, the plurality of hot-side plungings (not visible in the illustration of FIG. 4, but represented in the singular by the hot-side plunging 246 in FIG. 2 and the hot-side plunging 306 in FIG. 3), and the plurality of cold-side scoops represented by the cold-side scoop 308 may be integrally fabricated as one unit (e.g., fabricated as a continuous single unit) utilizing a 3D printing process performed by a 3D printer according to some aspects of the disclosure.

[0081] It is noted that each of the plurality of primary ports, including the primary port 236, are illustrated as having a circular circumference or border; however, other shapes including, but not limited to, an oval or a polygon are within the scope of the disclosure. It is noted that each of the plurality of cooling slots, such as the exemplary cooling slot 240 (including the upper embossment 238 and the lower embossment 242) are illustrated as having rectilinear border; however, other shapes including, but not limited to, a circular, semi-circular, oval, semi-oval, polygonal, or semi-polygonal shape are within the scope of the disclosure. It is noted that each of the plurality of dilution ports, including the dilution port 302 and the dilution port 404 are illustrated as having a circular circumference or border; however, other shapes including, but not limited to, an oval or a polygon are within the scope of the disclosure.

[0082] FIG. 5 is a top-right perspective view of a section of a liner 500, including a dilution port 502 and a cold-side scoop 508, similar to the dilution port 302 and cold-side scoop 308 as shown and described in connection with FIGs. 3 and 4, according to some aspects of the disclosure. The liner 500, including the dilution port 502 and the coldside scoop 508, may be similar to the same components in any of the plurality of combustors 126 of FIG. 1 or the combustor 300 of FIGs. 3 and 4, according to some aspects of the disclosure. The dilution port 502 is defined by the sidewall 506 encircling the dilution port 502. The exterior surface 504 of the liner 500 is depicted as being adjacent to the cold-side scoop 508. A leading edge 510 of the cold-side scoop 508 isAttorney Docket No. BEEHI-1028PCTdepicted as being oriented perpendicular to the Z axis (perpendicular to the longitudinal axis of the combustor (not shown)).

[0083] FIG. 6 is a bottom-right perspective view of the section of the liner 500, including the dilution port 502 as shown and described in connection with FIG. 5, and making visible a hot-side plunging 600, according to some aspects of the disclosure. The hot- side plunging 600 may be similar to the hot-side plunging 246 of FIG. 2 and / or the hot- side plunging 306 of FIG. 3, according to some aspects of the disclosure. The hot-side plunging 600 may project away (e.g., extend in depth) from the interior surface 602 of the liner 500 to a greater or lesser amount than shown in FIG. 6. Any change to the depth of the hot-side plunging 600 is within the scope of the disclosure. Additionally, although depicted as being circular, any shape including, but not limited to, rectilinear, circular, semi-circular, oval, semi-oval, polygonal, or semi-polygonal shape is within the scope of the disclosure, The dilution port 502 is defined by the sidewall 506 encircling the dilution port 502. A portion of the cold-side scoop 508 and a portion of the leading edge 510 of the cold-side scoop 508 is visible through the opening of the dilution port 502. The interior surface 602 of the liner 500 is depicted as being adjacent to the hot-side plunging 600, all according to some aspects of the disclosure.

[0084] FIG. 7 is a top view of the section of the liner 500 of FIG. 5 including the dilution port 502, and the cold-side scoop 508 (encircling the dilution port 502 and defined by an interior sidewall 506 of the liner 500) as shown in FIGs. 5 and 6, according to some aspects of the disclosure. The exterior surface 504 of the liner 500 is depicted as being adjacent to the cold-side scoop 508. The leading edge 510 of the cold-side scoop 508 is depicted as being oriented perpendicular to the Z axis (perpendicular to the longitudinal axis of the combustor (not shown)).

[0085] FIG. 8 is a side view cross-section of the section of the liner 500 depicted in FIGs.5, 6, and 7, according to some aspects of the disclosure. FIG. 8 includes the dilution port 502, the cold-side scoop 508, and the hot-side plunging 600 as variously shown in FIGs. 5, 6, and 7, according to some aspects of the disclosure. The leading edge 510 of the cold-side scoop 508 is depicted as being oriented perpendicular to the Z axis (perpendicular to the longitudinal axis of the combustor (not shown)). The exterior surface 504 of the liner 500 is depicted as being adjacent to the cold-side scoop 508. The interior surface 602 of the liner 500 is depicted as being adjacent to the hot-side plunging 600.Attorney Docket No. BEEHI-1028PCT

[0086] Using FIGs. 5 and 8 as one non-limiting illustrative example, where the cold-side scoop 508 is one example of one of first plurality of cold-side scoops, the figures illustrate that each of the first plurality of cold-side scoops 508 include a structure forming a wedge-shaped segment (802) taken from an exterior surface of a hemisphere (804) of a sphere (806), where: the hemisphere (804) is positioned on an equatorial plane (808) that aligns with an opening of the dilution port (502), and a leading edge of a respective one of the first plurality of cold-side scoops (508) is inclined at an inclined angle (0) relative to the equatorial plane (808), a base (812) of the inclined angle (0) lying on the equatorial plane (808). The angle 0 may be about 90 degrees. However, in some examples, the angle 0 may range from about 5 to about 100 degrees, or may range from about 30 to about 90 degrees, or may range from about 45 to about 75 degrees. Other values of the angle 0 are within the scope of the disclosure.

[0087] FIG. 9 is a bottom view of the section of the liner 500 depicted in FIGs. 5, 6, 7, and 8, according to some aspects of the disclosure. The dilution port 502 may be defined by the sidewall 506 encircling the dilution port 502. The interior surface 602 of the liner 500 is depicted as being adjacent to the hot-side plunging 600. A portion of the leading edge 510 of the cold-side scoop 508 and an interior portion of the cold-side scoop 508 are visible within the dilution port 502. The leading edge 510 is depicted as being oriented perpendicular to the Z axis (perpendicular to the longitudinal axis of the combustor (not shown)).

[0088] FIG. 10 is a side view of an outer surface of a liner 1001 of a foldback combustor 1000 of a gas turbine engine (not shown), according to some aspects of the disclosure. A combustion zone 1002, similar to the combustion zone 214 as shown and described in connection with FIGs. 2 and 3, is illustrated in dashed (phantom) line for reference.

[0089] The foldback combustor 1000 includes a depiction of a guide vane 1004 (similar to the centrifugal compressor guide vane 120 as shown and described in connection with FIG. 1) at a compressor outlet 1006 (similar to the centrifugal compressor outlet 122 as shown and described in connection with FIG. 1). The compressor (not shown) may be a centrifugal compressor (similar to the centrifugal compressor 114 as shown and described in connection with FIG. 1 ). A compressor exit flow 1010 with a swirl induced by the centrifugal compressor is illustrated with open ended arrows. The compressor exit flow 1010 with the swirl may be similar to the high-pressure compressed air 142Attorney Docket No. BEEHI-1028PCT(with the swirl) as shown and described in connection with FIG. 1 , and may be similar to the high-pressure compressed air 210 (with the swirl) as shown and described in connection with FIGs. 2, 3, and 4. The compressor exit flow 1010 with the swirl flows over the outer surface of the liner 1001 of the foldback combustor 1000. The foldback combustor 1000 may be part of an annular combustor according to some aspects. A combustor outlet 1011 is depicted along with a conduit 1015 between the combustor outlet 1011 and a turbine inlet 1016 are depicted.

[0090] Although examples of annular combustors are used throughout the disclosure, other types or styles of combustors are within the scope of the disclosure. An example given with respect to an annular combustor does not limit the example, or any part of the disclosure herein, to annular combustors.

[0091] A leading edge 1012 of a cold-side scoop 1008, associated with a combustion dilution port (referred to herein as a dilution port 1040), is depicted as being rotated to an angle that is perpendicular to a directional component of the compressor exit flow 1010 with the swirl, the directional component may be a tangential directional component. Configuring the angle of the leading edge 1012 of the cold-side scoop 1008 to be perpendicular to the directional component of the compressor exit flow 1010 with the swirl may maximize (e.g., relative to a scoop that has a leading edge that is configured to be other than perpendicular to the directional component of the compressor exit flow 1010 with the swirl) the capture of that compressor exit flow 1010, and recovery of dynamic pressure that may be lost in the absence of the cold-side scoop 1008.

[0092] FIG. 11 is a side view cross-section of an outside surface of a liner 1101 of an axial combustor 1100 of a gas turbine engine (not shown), according to some aspects of the disclosure. The axial combustor 1100 may be similar to any combustor 144, 200, 300 as shown and described in connection with FIGs. 1, 2, 3, and 4. A combustion zone 1102, similar to the combustion zone 214 as shown and described in connection with FIGs. 2 and 3, is illustrated in dashed (phantom) line for reference. A compressor exit flow 1110 with the swirl is represented as flowing around (swirling) the outside surface of the liner 1101 for exemplary and non-limiting reasons.

[0093] FIG. 11 depicts a guide vane 1104 at a compressor outlet 1108. The compressor exit flow 1110 with the swirl flows over the surface of the axial combustor 1100. The leading edge 1012 of the cold-side scoop 1008, associated with the dilution port 1040,Attorney Docket No. BEEHI-1028PCTis depicted as being rotated to an angle that is perpendicular to the directional component of the compressor exit flow 1110 with the swirl. Configuring the angle of the leading edge 1112 of the cold-side scoop 1008 to be perpendicular to the directional component of the compressor exit flow 1110 with the swirl may maximize the capture of that compressor exit flow 1110, and recovery of dynamic pressure that may be lost in the absence of the cold-side scoop 1008. A turbine inlet 1116 is represented in schematic form.

[0094] FIG. 12 is a top view of the outside surface of the liner 1101 of the axial combustor 1100 of the gas turbine engine (not shown) of FIG. 11 , according to some aspects of the disclosure. The combustion zone 1102, similar to the combustion zone 214 as shown and described in connection with FIGs. 2 and 3, is illustrated in dashed (phantom) line for reference. The guide vane 1104, the compressor outlet 1108, and the turbine inlet 1116 appear at right angles to their presentation in FIG. 11. The compressor (not shown) may be a centrifugal compressor. The compressor exit flow 1010 with a swirl induced by the centrifugal compressor is illustrated with open ended arrows. The compressor exit flow 1010 with the swirl flows over the surface of the axial combustor 1100. The leading edge 1012 of the cold-side scoop 1008, associated with the dilution port 1040, is depicted as being rotated to an angle that is perpendicular to the directional component of the compressor exit flow 1010 with the swirl. Configuring the angle of the leading edge 1012 of the cold-side scoop 1008 to be perpendicular to the directional component of the compressor exit flow 1110 with the swirl may maximize the capture of that compressor exit flow 1110 with the swirl, and recovery of dynamic pressure that may be lost in the absence of the cold-side scoop 1008.

[0095] FIG. 13 is a side view cross-section of a portion of an annular combustor 1300 according to some aspects of the disclosure. The portion of the annular combustor 1300 may include one or more foldback combustors, such as the foldback combustor 1000 as shown and described in connection with FIG. 10. The liner 1301 of the annular combustor 1300 is shown in a cut-away view. The interior of the outer annulus 1302, the middle annulus 1303, and the inner annulus 1304 of the annular combustor 1300 are visible.

[0096] The relatively small holes that may number in the thousands in the annular combustor 1300 liner 1301 may be printed effusion cooling holes 1305. A plurality of cold-side scoops 1008 are depicted. Both the exterior and the interior of several onesAttorney Docket No. BEEHI-1028PCTof the plurality of the cold-side scoops 1008 are represented, along with a plurality of hot-side plungings 1042. A combustor outlet 1311, similar to the combustor outlet 111 as shown and described in connection FIG.1, is depicted along with a conduit 1315 between the combustor outlet 1311 and a turbine inlet 1316, similar to the turbine inlet 1016 and the turbine inlet 1116 as shown and described in FIG. 10.

[0097] A compressor diffuser 1324 is visible. The compressor diffuser 1324 may be similar to the diffuser 124 as shown and described in connection with FIG. 1. A purpose of the compressor diffuser 1324 is to linearize the flow of high-pressure compressed air 1342 exiting the compressor (not shown) and traveling toward the annular combustor 1300. The compressor may be a centrifugal compressor. In smaller size engines there may not be enough room to provide a diffuser that can supply air that is completely axial (linear). Accordingly, the compressor exit flow 1310 (exiting the compressor diffuser 1324) may be mixed with swirling high-pressure compressed air.

[0098] The compressor exit flow 1310 with the swirl may be similar to the high- velocity, high-pressure engine exhaust gas 110 (with the swirl) and the high-pressure compressed air 210 (with the swirl) as shown and described in connection with FIGs.1, 2, 3, and 4. The compressor exit flow 1310 with the swirl flows over the exterior surface of the liner 1301 of the annular combustor 1300.

[0099] A leading edge 1012 of a cold-side scoop 1008, associated with a combustion dilution port 1040, is depicted as being rotated to an angle that would be perpendicular to the direction of the com pressor exit flow 1310 (e.g., the mass-flow). Configuring the angle of the leading edge 1012 of the cold-side scoop 1008 to be perpendicular to the directional component of the compressor exit flow 1310 with the swirl may maximize (e.g., relative to a scoop that has a leading edge that is configured to be other than perpendicular to the flow with the swirl) the capture of that compressor exit flow 1310, and recovery of dynamic pressure that may be lost in the absence of the cold-side scoop 1008.

[0100] The foldback combustor 1000 of FIG. 10, the axial combustor 1100 of FIGs. 11 and 12, and the annular combustor 1300 of FIG. 13 each include a plurality of dilution ports, represented by the dilution port 1040 to avoid cluttering the drawings. The dilution port 1040 may be similar to the dilution port 302 of FIG. 3. Any dilution port 1040 may include a cold-side scoop 1008, a hot-side plunging 1042, both the coldside scoop 1008 and the hot-side plunging 1042, or neither the cold-side scoop 1008Attorney Docket No. BEEHI-1028PCTnor the hot-side plunging 1042. Any combination of one, both, or neither is within the scope of the disclosure. The dilution port 1040, the cold-side scoop 1008 and the hot- side plunging 1042 may be similar to the dilution port 302, the cold-side scoop 308, and the hot-side plunging 306, respectively, as shown and described in connection with FIG. 3. In cases where the foldback combustor 1000, the axial combustor 1100, the annular combustor 1300, and / or any of their liners 1001, 1101, 1301, as shown and described in connection with FIGs. 10, 11 & 12, and 13, are 3D printed, the coldside scoop 1008 and the hot-side plunging 1042 (if present) associated with a given dilution port 1040 may be fabricated as integral features of the liner 1001 , 1101, 1301 of the foldback combustor 1000, the axial combustor 1100, the annular combustor 1300, respectively.

[0101] In some examples, all, or a given percentage of all, dilution ports 1040 of a combustor, such as the combustor foldback combustor 1000, the axial combustor 1100, the annular combustor 1300 of FIGs. 10, 11 and 12, and 13, respectively may include a cold-side scoop 1008, a hot-side plunging 1042, or both the cold-side scoop 1008 and the hot-side plunging 1042 according to some aspects of the disclosure.

[0102] Both the cold-side scoop 1008 and the hot-side plunging 1042 redirect a directional component of velocity towards a radial direction. Redirecting the directional component of velocity towards the radial direction may improve a gas turbine engine’s ability to mix cold air (not shown) with the hot combustion gas in the combustion zone 1002, 1102, 1202 as shown and described in connection with FIGs. 10, 11, and 12, respectively.

[0103] In a gas turbine engine, specific fuel consumption (SFC) may be improved by allowing a swirling flow 1214 (FIG. 12) in the compressor-exit velocity field 1215 following the guide vane 1104 to remain in the compressor exit flow 1110 of a compressor outlet 1108 rather than forcing the compressor exit flow 1110 to be axial; however, that swirling flow 1214 (FIG. 12) then enters the space 234 (FIG. 2) and 1334 (FIG. 13) between the interior of the combustor case 148 (FIG. 1 ), 1348 (FIG. 13) (not shown in FIGs. 10, 11, and 12) and the outside surface (e.g., the exterior) of the liner 1001 (FIG. 10), 1101 (FIG. 11), 1201 (FIG. 12), where it must penetrate radially (e.g. in the negative Y axis direction via the dilution port 1040) to achieve good mixing with the hot combustion gas in the combustion zone 1002 (FIG. 10, 1102 (FIG. 11), 1202 (FIG. 12) within the liner 1001 (FIG. 10), 1101 (FIGs. 11 and 12), 1301 (FIG. 13) of theAttorney Docket No. BEEHI-1028PCTfoldback combustor 1000 (FIG. 10), axial combustor 1100 (FIGs. 11 and 12), and annular combustor 1300 (FIG. 13). If the dilution port 1040 (which is representative of a plurality of dilution ports surrounding the circumference of the liner 1001 , 1101, 1301 ) were simply holes, without an external structure of a cold-side scoop, for example, the directional component of velocity associated with the swirling flow 1214 (FIG. 12) would reduce mixing efficiency.

[0104] Accordingly, the plurality of dilution ports, represented by the dilution port 1040, may be fabricated with cold-side scoops 1008 and hot-side plungings 1042 (or their equivalents) to convert tangential velocity into radial velocity to achieve good mixing of cold air (not shown) with hot combustion gas in the combustion zone 1002 (FIG.10), 1102 (FIG. 11), 1202 (FIG. 12). Without good mixing of the cold air (not shown) with the hot combustion gas in the combustion zone, a given combustor may run with poor efficiency, visible smoke, and hot streaks at the turbine inlet 1016.

[0105] In some examples, the swirling flow 1214 in the compressor-exit velocity field 1215 (FIG. 12) was passed through the guide vane 1004, 1104 (FIGs. 10, 11, 12), at the compressor outlet 1006, 1106 (FIGs. 10, 11, 12), that removed most of the swirl from the compressor exit flow 1010, 1110, 1310 (FIGs. 10, 11, 12, 13) so that the flow around the foldback combustor 1000, the axial combustor 1100, and the annular combustor 1300 was largely axial in its orientation. The act of removing the swirl of the compressor exit flow 1010, 1110, 1310 however, imposes a pressure loss, thereby increasing the fuel consumption of the engine relative to one with its compressor exit flow 1010 left with the swirl in the compressor exit flow 1010.

[0106] In examples where a combustor (e.g., similar to the combustor 144 of FIG. 1, 200 of FIG. 2, 300 of FIG. 3 and FIG. 4, foldback combustor 1000 of FIG. 10, axial combustor 1100 of FIGs. 11 and 12, and annular combustor 1300 of FIG. 13) is 3D printed, pluralities of cold-side scoops (e.g., similar to the cold-side scoop 308 of FIG.3 and FIG. 4, the cold-side scoop 508 of FIGS. 5, 6, 7, 8, and 9, and the cold-side scoop 1008 of FIGs. 10, 11, and 12) and hot-side plungings (e.g., similar to the hot- side plunging 246 of FIG. 2, 306 of FIG. 3, 600 of FIGs. 6, 8, and 9, and 1042 of FIGs.10, 11, and 13), each associated with a respective dilution port (e.g., dilution port 244 of FIG. 2, 302 of FIGs. 3 and 4, 502 of FIGs. 5, 6, 7, 8, and 9, and 1040 of FIGs. 10, 11, 12, and 13) of a plurality of dilution ports, may be printed as integral features of the combustor. The cold-side scoops (e.g., similar to the cold-side scoop 308 of FIG.Attorney Docket No. BEEHI-1028PCT3 and FIG. 4, the cold-side scoop 508 of FIGS. 5, 6, 7, 8, and 9, and the cold-side scoop 1008 of FIGs. 10, 11, 12, and 13) and hot-side plungings (e.g., similar to the hot-side plunging 246 of FIG. 2, 306 of FIG. 3, 600 of FIGs. 6, 8, and 9, and 1042 of FIGs. 10, 11, and 13) may provide improved combustion mixing (e.g., improved combustion mixing quality) and engine efficiency.

[0107] FIG. 14 is the side view cross-section of the portion of the annular combustor 1300 of FIG. 13 identifying a first row of dilution ports 1402, a second row of dilution ports 1404, and a row of primary ports 1406, according to some aspects of the disclosure. The various ports are offset around the circumferences of the rows of ports so that they do not block the next row of ports from an airflow direction point of view. In the example of FIGs. 13 and 14, there are relatively few number of primary ports 1406 in the primary zone. Reducing the number of primary ports reduces the air admitted into the primary zone and brings the primary zone closer to stoichiometric.

[0108] In some examples, the (quantity of the) first plurality of dilution ports 502, 1502, 1504 may be equal to the (quantity of the) second plurality of cold-side scoops 508, 1508, 1510. The annular combustor 1300 may further include a third plurality of primary ports 1406, and a fourth plurality of cold-side scoops 1408. Each of the fourth plurality of cold-side scoops 1408 may be respectively integrated with a corresponding primary port of the third plurality of primary ports 1406. In some examples, the (quantity of the) third plurality of primary ports 1406 may be equal to the (quantity of the) fourth plurality of cold-side scoops 1408.

[0109] In some examples, the annular combustor 1300, including the second plurality of cold-side scoops 508, 1508, 1510, may be printed on a three dimensional (3D) printer as a unitary object. The 3D printer may fabricate the unitary object using a metal powder. Various additive manufacturing methods may be used to fabricate the gas turbines or any component part of the gas turbines described herein. For example and without limitation, various additive manufacturing metal powder processes include, but are not limited to, selective laser melting (SLM), selective laser sintering (SLS), electron beam melting (EBM), laser engineering net shaping (LENS) I directed energy deposition (DED), electron beam fabrication (EBF), and industrial metal additive manufacturing for superalloys.

[0110] Fuel injection occurs in the top right of the annular combustor 1300 as illustrated in the configurations of FIGs. 13 and 14. The air inside the annular combustor 1300Attorney Docket No. BEEHI-1028PCTtravels to the left of the fuel injection before reversing and flowing to the right into the turbine inlet 1316 (e.g., into a nozzle guide vane (NGV), turbine inlet guide vane, turbine inlet nozzle, or nozzle diaphragm). Combustion occurs in the primary, intermediate, and dilution zones of the annular combustor 1300. According to one aspect, all combustion may be completed by the time the combustion exhaust reaches the turbine inlet 1316 (e.g., reaches the NGV).

[0111] FIG. 15 is an enlarged view of a portion of the side view cross-section of a portion of the annular combustor 1300 of FIG. 13, according to some aspects of the disclosure. FIG. 15 depicts a plurality of dilution ports, including a first dilution port 1502 and a second dilution port 1504, according to some aspects of the disclosure. The first dilution port 1502 includes a first cold-side scoop 1508 and a first hot-side plunging 1506. The second dilution port 1504 includes a second cold-side scoop 1510 and a second hot-side plunging 1512. The second dilution port 1504 is shown in crosssection. As can be observed from the cross-sectional view, the second dilution port 1504 may be defined by an internal sidewall 1514 of the annular combustor 1300, which encircles the second dilution port 1504.

[0112] A first leading edge 1516 of the first cold-side scoop 1508 of the first dilution port 1502 is depicted. A second leading edge 1518 of the second cold-side scoop 1510 of the second dilution port 1504 is also depicted. A compressor exit flow with the swirl (not shown) induced by the centrifugal compressor (not shown) is configured to flow over an exterior surface 1520 (e.g., the cold-side surface) of the liner 1301 of the annular combustor 1300. The first leading edge 1516 of the first cold-side scoop 1508 associated with the first dilution port 1502, is depicted as being rotated to a first angle that is perpendicular to a directional component of the compressor exit flow with the swirl (not shown). The second leading edge 1518 of the second cold-side scoop 1510 associated with the second dilution port 1504, is depicted as being rotated to a second angle that is perpendicular to a directional component of the compressor exit flow with the swirl (not shown). The first angle and the second angle may be the same angle in some examples, while in other examples, the first angle and the second angle may be different angles. Configuring the first and second angles of the first leading edge 1518 and the second leading edge 1518 of the first cold-side scoop 1508 and the second cold-side scoop 1510, respectively to be perpendicular to the directional component of the compressor exit flow (at the given cold-side scoop) with the swirl may maximizeAttorney Docket No. BEEHI-1028PCTthe capture of that compressor exit flow, and the recovery of dynamic pressure that may be lost in the absence of the first cold-side scoop 1508 and the second cold-side scoop 1510.

[0113] Using FIGs. 5, 13, 15, and 16 for purposes of an illustrative and non-limiting example, an annular combustor 1300 may include a liner 1301, a case 1348 outside the liner 1301 , and a first plurality of dilution ports, 502 (FIG. 5), 1502, 1504 (FIG. 15). Each of the first plurality of dilution ports 502, 1502, 1504 may be defined by one or more internal sidewalls 506, 1514 of the liner 500, 1301. The annular combustor 1300 may also include a second plurality of cold-side scoops 508, 1508, 1510, each of the second plurality of cold-side scoops respectively integrated with a corresponding dilution port of the first plurality of dilution ports 502, 1502, 1504. According to some aspects, each of the second plurality of cold-side scoops 508, 1508, 1510 may have a leading edge 510, 1516, 1518 that is configured to be oriented perpendicular to a predetermined directional component of a compressor exit flow 1610. The annular combustor 1300 may be configured to receive the compressor exit flow 1610 from a centrifugal compressor 114 (FIG. 1).

[0114] In other words, each of the first plurality of dilution ports 502, 1502, 1504 may be defined by one or more internal sidewalls 506 of the liner 500 and each of the second plurality of cold-side scoops 508, 1508, 1510 may extend from an exterior surface 1530 of a liner 1301 into a space 1334 defined between an interior surface 1522 of a case 1348 and the exterior surface 1530 of the liner 1301.

[0115] According to some aspects, a plurality of hot-side plungings 306, 1506, 1512, may be formed in association with one or more of the first plurality of dilution ports 302, 1502, 1504. In some examples, at least one of the first plurality of dilution ports 302, 1502, 1504 may be associated with, formed with, both the cold-side scoop (308, 1508, 1510 and a hot-side plunging 306, 1506, 1512.

[0116] FIG. 16 is a cut-away view of the annular combustor 1300 of FIG. 13, according to some aspects of the disclosure. The exterior surface 1520 of the liner 1301 is visible. The first row of dilution ports 1402, the second row of dilution ports 1404, and the row of primary ports 1406, as shown and described in connection with FIG.13 and 14 are depicted. Each of the dilution ports and each of the primary ports are configured with a cold-side scoop. A compressor exit flow 1610 with a swirl 1602 induced by aAttorney Docket No. BEEHI-1028PCTcentrifugal compressor (not shown) exits the compressor diffuser 1324 and flows over the exterior surface 1520 of the liner 1301 of the annular combustor 1300.

[0117] Using a second dilution port 1640 of the first row of dilution ports 1402 as a representative example, the leading edge 1612 of the cold-side scoop 1608 is depicted as being rotated to an angle that is perpendicular to the directional component of the compressor exit flow 1610 with the swirl 1602. Configuring the angle of the leading edge 1612 of the cold-side scoop 1608 to be perpendicular to the directional component of the compressor exit flow 1610 with the swirl 1602 may maximize the capture of that compressor exit flow, and the recovery of dynamic pressure that may be lost in the absence of the cold-side scoop 1608.

[0118] In some examples, the compressor exit flow 1610 may be configured to include the swirl 1602 induced by the centrifugal compressor 114 (FIG. 1). The capture of the compressor exit flow 1610 with the swirl 1602 may be maximized by configuring an angle of a respective leading edge 1612 of each of the second plurality of cold-side scoops 1608 to be perpendicular to a directional component of the compressor exit flow 1610 with the swirl 1602.

[0119] Furthermore, a recovery of dynamic pressure that would be lost in an absence of a given one of the second plurality of cold-side scoops 1608 may be maximized by configuring the angle of the respective leading edge 1612 of each of the second plurality of cold-side scoops 1608 to be perpendicular to a directional component of the compressor exit flow 1610 with the swirl 1602.

[0120] According to aspects herein, the compressor exit flow 1610 with the swirl 1602 may be configured to flow over an exterior surface 1520 of the liner 1301 of the annular combustor 1300. In some examples, the second plurality of cold-side scoops 1508, 1510 may extend from the exterior surface 1520 of the liner 1301 into the compressor exit flow 1610 with the swirl 1602.

[0121] As illustrated in the examples of FIGs. 10-16, the exemplary cold-side scoops 1008, first cold-side scoop 1508, second cold-side scoop 1510, second cold-side scoop 1608 may be less than quarters of a sphere. The leading edges of the cold-side scoops such as the leading edge 1012 (FIGs. 10-13), first leading edge 1516, and the second leading edge 1518 of the first cold-side scoop 1508 and the second cold-side scoop 1510 (FIG. 15) and the leading edge 1612 of the second cold-side scoop 1608 (FIG. 16), may slope backward (e.g., away from the direction of the advancingAttorney Docket No. BEEHI-1028PCTcompressor exit flow 1610 with the swirl 1602 (FIG. 16)). The tops of the exemplary cold-side scoops 1008, first cold-side scoop 1508, second cold-side scoop 1510, coldside scoops 1608 opening extend into the space above the surface of the liner 1301 of the annular combustor 1300 and below the inner surface of the outer casing of the annular combustor 1300. The air that flows over and around the cold-side scoops 1008, first cold-side scoop 1508, second cold-side scoop 1510, cold-side scoops 1608 moves along the annulus between the outer casing and the liner to feed dilution, primary, and other ports (openings, holes).

[0122] The compressor exit flow 1610 with the swirl 1602 (FIG. 16) is present in the entire height of the annulus, however only a portion of the air is collected by the cold-side scoops 1008, first cold-side scoop 1508, second cold-side scoop 1510, cold-side scoops 1608 at each port (e.g., dilution port, primary port, etc.).

[0123] Several aspects of gas turbine engine combustors have been presented with reference to exemplary implementations. As those persons having ordinary skill in the art will readily appreciate, various aspects described throughout this disclosure may be extended to other combustors in other engines.

[0124] The following provides an overview of aspects of the present disclosure.

[0125] Aspect 1: An annular combustor, comprising: a liner; a case outside the liner;a first plurality of dilution ports, each of the first plurality of dilution ports defined by one or more internal sidewalls of the liner; and a second plurality of cold-side scoops, each of the second plurality of cold-side scoops respectively integrated with a corresponding dilution port of the first plurality of dilution ports, wherein each of the second plurality of cold-side scoops has a leading edge that is configured to be oriented perpendicular to a predetermined directional component of a compressor exit flow, and the annular combustor is configured to receive the compressor exit flow from a centrifugal compressor.

[0126] Aspect 2: The annular combustor of aspect 1, wherein each of the second plurality of cold-side scoops comprises a structure formed as a wedge-shaped segment taken from an exterior surface of a hemisphere of a sphere, wherein: the hemisphere is positioned on an equatorial plane that aligns with an opening of the corresponding dilution port of the first plurality of dilution ports, and the leading edge of a respective one of the second plurality of cold-side scoops is inclined at an inclinedAttorney Docket No. BEEHI-1028PCTangle (0) relative to the equatorial plane, a base of the inclined angle (0) lying on the equatorial plane.

[0127] Aspect 3: The annular combustor of aspect 1 or aspect 2, wherein each of the first plurality of dilution ports is defined by the one or more internal sidewalls of the liner and each of the second plurality of cold-side scoops extends from an exterior surface of the liner into a space defined between an interior surface of the case and the exterior surface of the liner.

[0128] Aspect 4: The annular combustor of any of aspects 1 through 3, wherein the compressor exit flow is configured to include a swirl induced by the centrifugal compressor.

[0129] Aspect 5: The annular combustor of aspect 4, wherein a capture of the compressor exit flow with the swirl is maximized by configuring an angle of the leading edge of each of the second plurality of cold-side scoops to be perpendicular to a directional component of the compressor exit flow with the swirl.

[0130] Aspect 6: The annular combustor of any of aspects 1 through 5, wherein a recovery of dynamic pressure that would be lost in an absence of a given one of the second plurality of cold-side scoops is maximized by configuring an angle of the leading edge of each of the second plurality of cold-side scoops to be perpendicular to a directional component of the compressor exit flow with the swirl.

[0131] Aspect 7: The annular combustor of any of aspects 1 through 6, wherein the compressor exit flow with the swirl is configured to flow over an exterior surface of the liner of the annular combustor.

[0132] Aspect 8: The annular combustor of aspect 7, wherein the second plurality of cold-side scoops extends from the exterior surface of the liner of the annular combustor into the compressor exit flow with the swirl.

[0133] Aspect 9: The annular combustor of any of aspects 1 through 8, wherein the first plurality of dilution ports is equal to the second plurality of cold-side scoops.

[0134] Aspect 10: The annular combustor of any of aspects 1 through 9, further comprising: a third plurality of primary ports, and a fourth plurality of cold-side scoops, each of the fourth plurality of cold-side scoops respectively integrated with a corresponding primary port of the third plurality of primary ports.

[0135] Aspect 11: The annular combustor of aspect 10, wherein the third plurality of primary ports is equal to the fourth plurality of cold-side scoops.Attorney Docket No. BEEHI-1028PCT

[0136] Aspect 12: The annular combustor of any of aspects 1 through 11 , wherein the annular combustor, including the second plurality of cold-side scoops, is printed on a three dimensional (3D) printer as a unitary object.

[0137] Aspect 13: The annular combustor of aspect 12, wherein the 3D printer fabricates the unitary object using a metal powder.

[0138] Aspect 14: The annular combustor of any of aspects 1 through 13, further comprising a plurality of hot-side plungings formed in association with one or more of the first plurality of dilution ports.

[0139] Aspect 15: The annular combustor of any of aspects 1 through 14, where at least one of the first plurality of dilution ports comprises both a cold-side scoop and a hot- side plunging.

[0140] Aspect 16: An annular combustor configured to be fed with compressed air exiting a centrifugal compressor, the annular combustor comprising: a plurality of dilution ports, one or more cold-side scoops, each formed with a dilution port of the plurality of dilution ports, wherein a leading edge of each of the one or more cold-side scoops is configured to be perpendicular to a compressor exit flow with a swirl induced by the centrifugal compressor, wherein the compressor exit flow with a swirl flows over a surface of the annular combustor, and wherein the leading edge of each of the one or more cold-side scoop associated with a respective dilution port is configured to be perpendicular to a directional component of the compressor exit flow with the swirl.

[0141] Aspect 17: The annular combustor of aspect 16, wherein configuring the angle of the leading edge of the cold-side scoop to be perpendicular to the directional component of the compressor exit flow with the swirl maximizes the capture of that compressor exit flow and the recovery of dynamic pressure that may be lost in the absence of the cold-side scoop.

[0142] Aspect 18: The annular combustor of aspect 16 or aspect 17, wherein the combustor, including the dilution ports each configured with a cold-side scoop, is printed on a three dimensional (3D) printer as a unitary object.

[0143] Aspect 19: The annular combustor of aspect 18, wherein the 3D printer fabricates the unitary object using metal powder.

[0144] Aspect 20. The annular combustor of any of aspects 16 through 19, further comprising a plurality of hot-side plungings formed in association with each of the plurality of dilution ports.Attorney Docket No. BEEHI-1028PCT

[0145] Aspect 21: The annular combustor of any of aspects 16 through 20, further comprising: a plurality of primary ports each configured with a cold-side scoop, and a primary port cold-side scoop leading edge of each primary port cold-side scoop is configured to be perpendicular to the compressor exit flow with the swirl induced by the centrifugal compressor wherein the compressor exit flow with the swirl flows over the surface of the annular combustor, and wherein the leading edge of each primary port cold-side scoop associated with a respective primary port is configured to be perpendicular to a directional component of the compressor exit flow with the swirl.

[0146] Aspect 22: The annular combustor of any of aspects 16 through 21, where at least one of the plurality of dilution ports comprises both the cold-side scoop and a hot-side plunging.

Claims

Attorney Docket No. BEEHI-1028PCTCLAIMSWhat is claimed is:

1. An annular combustor (1300), comprising:a liner (1301);a case (1348) outside the liner (1301 );a first plurality of dilution ports (302, 502, 1502, 1504), each of the first plurality of dilution ports defined by one or more internal sidewalls (506, 1514) of the liner (500, 1301 ); anda second plurality of cold-side scoops (508, 1508, 1510), each of the second plurality of cold-side scoops respectively integrated with a corresponding dilution port of the first plurality of dilution ports (502, 1502, 1504),wherein each of the second plurality of cold-side scoops (508, 1508, 1510) has a leading edge (510, 1516, 1518, 1612) that is configured to be oriented perpendicular to a predetermined directional component of a compressor exit flow (1610), and the annular combustor is configured to receive the compressor exit flow (1610) from a centrifugal compressor (114).

2. The annular combustor of claim 1, wherein each of the second plurality of coldside scoops (508, 1508, 1510) comprises a structure formed as a wedge-shaped segment (802) taken from an exterior surface of a hemisphere (804) of a sphere (806), wherein:the hemisphere (804) is positioned on an equatorial plane (808) that aligns with an opening of the corresponding dilution port of the first plurality of dilution ports (502, 1502, 1504), andthe leading edge (510, 1516, 1518, 1612) of a respective one of the second plurality of cold-side scoops (508, 1508, 1510) is inclined at an inclined angle (0) relative to the equatorial plane (808), a base (812) of the inclined angle (0) lying on the equatorial plane (808).

3. The annular combustor of claim 1 , wherein each of the first plurality of dilution ports (502, 1502, 1504) is defined by the one or more internal sidewalls (506) of the liner (500) and each of the second plurality of cold-side scoops (508, 1508, 1510) extends from anAttorney Docket No. BEEHI-1028PCTexterior surface (1530) of the liner (1301) into a space (1334) defined between an interior surface (1522) of the case (1348) and the exterior surface (1530) of the liner (1301).

4. The annular combustor of claim 1, wherein the compressor exit flow (1610) is configured to include a swirl (1602) induced by the centrifugal compressor (114).

5. The annular combustor of claim 4, wherein a capture of the compressor exit flow (1610) with the swirl (1602) is maximized by configuring an angle of the leading edge (1612) of each of the second plurality of cold-side scoops (1608) to be perpendicular to a directional component of the compressor exit flow (1610) with the swirl (1602).

6. The annular combustor of claim 4, wherein a recovery of dynamic pressure that would be lost in an absence of a given one of the second plurality of cold-side scoops (1608) is maximized by configuring an angle of the leading edge (1612) of each of the second plurality of cold-side scoops (1608) to be perpendicular to a directional component of the compressor exit flow (1610) with the swirl (1602).

7. The annular combustor of claim 4, wherein the compressor exit flow (1610) with the swirl (1602) is configured to flow over an exterior surface (1520) of the liner (1301 ) of the annular combustor (1300).

8. The annular combustor of claim 7, wherein the second plurality of cold-side scoops (1508, 1510) extends from the exterior surface (1520) of the liner (1301) of the annular combustor (1300) into the compressor exit flow (1610) with the swirl (1602).

9. The annular combustor of claim 1 , wherein the first plurality of dilution ports (502, 1502, 1504) is equal to the second plurality of cold-side scoops (508, 1508, 1510).

10. The annular combustor of claim 1 , further comprising:a third plurality of primary ports (1406), anda fourth plurality of cold-side scoops (1408), each of the fourth plurality of cold-side scoops (1408) respectively integrated with a corresponding primary port of the third plurality of primary ports (1406).Attorney Docket No. BEEHI-1028PCT11. The annular combustor of claim 10, wherein the third plurality of primary ports (1406) is equal to the fourth plurality of cold-side scoops (1408).

12. The annular combustor of claim 1, wherein the annular combustor, including the second plurality of cold-side scoops (508, 1508, 1510), is printed on a three dimensional (3D) printer as a unitary object.

13. The annular combustor of claim 12, wherein the 3D printer fabricates the unitary object using a metal powder.

14. The annular combustor of claim 1, further comprising a plurality of hot-side plungings (306) formed in association with one or more of the first plurality of dilution ports (302, 502, 1502, 1504).

15. The annular combustor of claim 1 , where at least one of the first plurality of dilution ports (302, 502, 1502, 1504) comprises both a cold-side scoop (308, 1508, 1510) and a hot-side plunging (306, 600, 1506, 1512).

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