Active boundary layer control in diffusers

Abstract

A combustor for a turbine engine is provided that includes an outer liner, an inner liner, and a dome together defining a combustion chamber, a diffuser positioned upstream of the combustion chamber, the diffuser configured to receive an airflow from a compressor section and provide a compressed airflow to the combustion chamber, and an outer shroud and an inner shroud positioned upstream of the combustion chamber, the outer shroud and the inner shroud configured to direct a portion of the airflow from the diffuser to the combustion chamber. The diffuser is configured to output the airflow having a greatest amount of air pressure at a center of the airflow, thereby optimizing a total air pressure fed to the combustion chamber through the dome.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to combustors in turbine engines, and in particular to a diffuser in a combustor of a turbine engine. BACKGROUND

[0002] Gas turbine engines generally include a core, and the core of a gas turbine engine generally includes, in serial flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. Compressed air is provided from the compressor section to the combustion section, where the compressed air is mixed with fuel and ignited to produce combustion gases. The combustion gases flow through the turbine section, driving the core.

[0003] Igniters are disposed within the combustion section or combustor, attached to a casing within the combustion section and extending to or through, for example, a combustion liner that at least partially defines a combustion chamber. Certain gas turbine engines use non-traditional high temperature materials, such as ceramic matrix composite (CMC) materials for the combustion liner. Such CMC materials are generally better able to withstand the extreme temperatures within the combustion chamber. The igniters can be movably attached to the combustion liner using a mounting assembly. The mounting assembly can allow the igniters to move relative to the combustion liner.

[0004] A diffuser is also disposed within the combustion section or combustor. The diffuser is configured to decelerate the air flow and convert the velocity of the air into an increase in static pressure. The effective conversion of velocity to pressure serves to reduce pressure losses throughout the system. In certain instances, more total air pressure can be required to supply flow to the combustor swirler to control emissions and durability. SUMMARY

[0005] One aspect of the present disclosure is to provide a combustor for a turbine engine. The combustor includes an outer liner, an inner liner, and a dome that together define a combustion chamber; a diffuser upstream of the combustion chamber, the diffuser configured to receive an air flow from a compressor section and provide the compressed air flow to the combustion chamber; and an outer shroud and an inner shroud upstream of the combustion chamber, the outer shroud and the inner shroud configured to direct a portion of the air flow from the diffuser to the combustion chamber. The diffuser is configured to output the air flow having a greatest amount of air pressure at a center of the air flow, thereby optimizing the total air pressure fed through the dome to the combustion chamber.

[0006] Another aspect of the present disclosure is to provide a turbine engine comprising: (A) a compressor section configured to produce compressed air; (B) a turbine section downstream of the compressor section; and (C) a combustion section disposed between the compressor section and the turbine section, the combustion section comprising a combustor. The combustor comprises: (a) an outer liner, an inner liner, and a dome that together define a combustion chamber; (b) a diffuser upstream of the combustion chamber, the diffuser configured to receive an air stream from the compressor section and provide a compressed air stream to the combustion chamber; and (c) an outer shroud and an inner shroud upstream of the combustion chamber, the outer shroud and the inner shroud configured to direct a portion of the air stream from the diffuser to the combustion chamber. The diffuser is configured to output the air stream having a maximum amount of air pressure at a center of the air stream, thereby optimizing a total air pressure fed through the dome to the combustion chamber.

[0007] A further aspect of the present disclosure is to provide a method of controlling an air stream in a combustor having a diffuser, a dome, and a combustion chamber. The method comprises: 1) injecting compressed air from a compressor section upstream of the diffuser into the diffuser of the combustor; 2) outputting an air stream from the diffuser; and 3) optimizing an air pressure amount to maximize an air stream pressure at a center of the air stream, thereby optimizing a total air pressure fed through the dome of the combustor to the combustion chamber of the combustor. Optimizing the air pressure amount comprises varying an amount of the air stream that escapes at an edge of the air stream.

[0008] Additional features, advantages, and embodiments of the present disclosure are set forth or apparent from consideration of the following detailed description, drawings, and claims. Moreover, it is to be understood that both the foregoing summary of the disclosure and the following detailed description are exemplary and intended to provide further explanation without limiting the scope of the disclosure as claimed. BRIEF DESCRIPTION OF DRAWINGS

[0009] The foregoing and other features and advantages will be apparent from consideration of the following detailed description taken in connection with the accompanying drawings, in which like reference characters commonly refer to like, functionally similar, and / or structurally similar elements.

[0010] Figure 1 is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure.

[0011] Figure 2 is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure Figure 1 is a schematic cross-sectional view of a combustion section of a turbine engine according to an embodiment of the present disclosure.

[0012] Figure 3 is a schematic view representing an outer shroud and an inner shroud defining an air stream through a swirler toward a combustion zone within a combustion chamber along with an outer housing and an inner housing according to an embodiment of the present disclosure.

[0013] Figure 4 is a schematic diagram showing the outer door between the outer diffuser wall and the outer shroud and the inner door (e.g., flap) between the inner diffuser wall and the inner shroud according to an embodiment of the present disclosure.

[0014] Figure 5A is a schematic diagram showing a configuration with the outer door and the inner door closed according to an embodiment of the present disclosure.

[0015] Figure 5B is a schematic diagram showing a configuration with the outer door and the inner door open according to an embodiment of the present disclosure.

[0016] Figure 6A is a schematic diagram showing a configuration using louvers according to an embodiment of the present disclosure, the louvers being in an open or substantially unobstructed air flow state around a center location of the air flow.

[0017] Figure 6B is a schematic diagram showing a configuration using louvers (e.g., actuatable louvers) according to another embodiment of the present disclosure, the louvers being in a closed or obstructed air flow state.

[0018] Figure 7A is a schematic diagram showing a configuration using louvers according to another embodiment of the present disclosure, the louvers being in an open or substantially unobstructed air flow state toward an edge location of the air flow.

[0019] Figure 7B is a schematic diagram showing a configuration using louvers (e.g., actuatable louvers) according to another embodiment of the present disclosure, the louvers being in a closed or obstructed air flow state.

[0020] Figure 8 is a schematic diagram of a combustor according to an embodiment of the present disclosure showing a boundary layer of air flow when using a particular air pressure condition at a compressor upstream of the diffuser. DETAILED DESCRIPTION

[0021] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is merely for illustrative purposes. Those skilled in the relevant art will recognize that other components and configurations can be used without departing from the spirit and scope of the present disclosure.

[0022] Current diffuser configurations are limited in their ability to control and / or alter the air boundary layer reaching the combustion zone and / or the air pressure supplied to different parts of the combustion system. Therefore, it is desirable to control the diffuser boundary layer by injecting air or moving surfaces, which can force more total pressure air into the dome of the combustion chamber. Design features of various embodiments of the combustor include, but are not limited to: (1) moving the blocker plates in the diffuser wall to increase total pressure at the center, (2) continuous diffuser passages leading to the shroud with passive or driven scoops for supplying the liner and turbine, (3) three-pass diffusers with a center passage designed to maximize total pressure supply to the swirler under certain operating conditions, and (4) a rotary drive system.

[0023] One benefit of the configuration of the present combustor in accordance with embodiments of the present disclosure is to provide additional total pressure supply to the swirler, which can ultimately reduce pollutant emissions, such as NOx and smoke. This is especially desirable in engines designed for supersonic cruise, as these engines operate at high T3, low P3, and high fuel-air ratio optimum conditions to produce high NOx and smoke. There can be other benefits as well, such as improved durability of the overall dome due to increased total pressure supply to the cooling passages. However, care must be taken to ensure that the system still provides sufficient pressure drop for the liner and turbine cooling.

[0024] Reference will now be made in detail to the current embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to various features of the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the present disclosure. As used herein, the terms “first,” “second,” and “third” can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to relative locations along a flow path of fluid flow. For example, “upstream” refers to the direction against the fluid flow, and “downstream” refers to the direction with the fluid flow.

[0025] Reference will now be made in detail to the current embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to various features of the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the present disclosure. As used herein, the terms “first,” “second,” and “third” can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to relative locations along a flow path of fluid flow. For example, “upstream” refers to the direction against the fluid flow, and “downstream” refers to the direction with the fluid flow. Figure 1 is a schematic cross-sectional view of a gas turbine engine in accordance with embodiments of the present disclosure. More specifically, for embodiments of Figure 1 is a schematic cross-sectional view of a gas turbine engine in accordance with embodiments of the present disclosure. More specifically, for embodiments of Figure 1 As shown, the turbofan engine 10 defines an axial direction A (extending parallel to a longitudinal centerline 12 provided for reference) and a radial direction R, which is generally perpendicular to the axial direction A. The turbofan engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream from the fan section 14. The term “downstream” is used in reference to the sense of air or gas flow in the description.

[0026] The depicted core turbine engine 16 generally includes an outer casing 18 that is substantially tubular and defines an annular inlet 20. The outer casing 18 encloses, in serial flow relationship, a compressor section including a booster or low pressure (LP) compressor 22 and a high pressure (HP) compressor 24, a combustion section 26, a turbine section including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30, and an ejection exhaust nozzle section 32. A high pressure (HP) shaft or spool 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) shaft or spool 36 drivingly connects the LP turbine 30 to the LP compressor 22. The compressor section, the combustion section 26, the turbine section, and the ejection exhaust nozzle section 32 together define a core air flowpath 37.

[0027] For the depicted embodiment, the fan section 14 includes a fan 38 having variable pitch with a plurality of fan blades 40 coupled to a disk 42 in a spaced apart manner. As shown, the fan blades 40 generally extend outwardly from the disk 42 in a radial direction R. Since the fan blades 40 are operably coupled to a suitable actuation member 44 configured to uniformly collectively change the pitch of the fan blades 40, each fan blade 40 is rotatable about a pitch axis P relative to the disk 42. The fan blades 40, the disk 42, and the actuation member 44 can together be rotated about the longitudinal centerline 12 (longitudinal axis) by the LP shaft or spool 36 across a power gear box 46. The power gear box 46 includes a plurality of gears for adjusting or controlling the rotational speed of the fan 38 relative to the LP shaft or spool 36 to a more efficient rotational fan speed.

[0028] The disk 42 is covered by a rotatable front hub 48 having an aerodynamic profile to facilitate airflow over the plurality of fan blades 40. Further, the fan section 14 includes an annular fan casing or nacelle 50 that circumferentially surrounds the fan 38 and / or at least a portion of the core turbine engine 16. The nacelle 50 can be structured to be supported relative to the core turbine engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Further, a downstream section 54 of the nacelle 50 can extend over an outer portion of the core turbine engine 16 so as to define a bypass airflow passage 56 therebetween.

[0029] During operation of the turbofan engine 10, a volume of air flow 58 enters the turbofan engine 10 through the associated inlet 60 of the nacelle 50 and / or fan section 14 in the airflow direction 58. As the volume of air passes through the fan blades 40, a first portion of air as indicated by arrow 62 is channeled or directed into the bypass airflow passage 56, while a second portion of air as indicated by arrow 64 is channeled or directed into the core airflow path 37, or more specifically, into the LP compressor 22. The ratio between the first portion of air indicated by arrow 62 and the second portion of air indicated by arrow 64 is commonly referred to as the bypass ratio. The pressure of the second portion of air indicated by arrow 64 is then increased as it is directed through the high pressure (HP) compressor 24 and into the combustion section 26 where it is mixed with fuel and burned to provide combustion gases 66.

[0030] The combustion gases 66 are directed through the HP turbine 28 where a portion of thermal and / or kinetic energy from the combustion gases 66 is extracted through sequential stages of HP turbine stator vanes 68 coupled to the outer casing 18 and HP turbine rotor blades 70 coupled to the HP shaft or spool 34, thus causing the HP shaft or spool 34 to rotate, thereby supporting the operation of the HP compressor 24. The combustion gases 66 then directed through the LP turbine 30 where a second portion of thermal and kinetic energy is extracted from the combustion gases 66 through sequential stages of LP turbine stator vanes 72 coupled to the outer casing 18 and LP turbine rotor blades 74 coupled to the LP shaft or spool 36, thus causing the LP shaft or spool 36 to rotate, thereby supporting the operation of the LP compressor 22 and / or the rotation of the fan 38.

[0031] The combustion gases 66 are then directed through the jet exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. At the same time, the pressure of the first portion of air 62 is significantly increased as it is directed through the bypass airflow passage 56 prior to being exhausted from the fan nozzle exhaust section 76 of the turbofan engine 10, also providing propulsive thrust. The HP turbine 28, the LP turbine 30, and the jet exhaust nozzle section 32 at least partially define a hot gas path 78 for channeling the combustion gases 66 through the core turbine engine 16.

[0032] It should be understood, however, that Figure 1 The turbofan engine 10 depicted is by way of example only and in other example embodiments the turbofan engine 10 can have any other suitable configuration. It should also be understood that aspects of the present disclosure can be incorporated into any other suitable gas turbine engine in other example embodiments. For example, aspects of the present disclosure can be incorporated into, for example, a turboshaft engine, a turboprop engine, a turboshaft core engine, a turbojet engine, etc. in other example embodiments.

[0033] Figure 2 is in accordance with embodiments of the present disclosure Figure 1 A schematic cross-sectional view of a combustion section 26 of a turbofan engine 10 in accordance with embodiments of the present disclosure. The combustion section 26 generally includes a combustor 80 that generates combustion gases that are discharged into a turbine section, or more specifically, into an HP turbine 28. The combustor 80 includes an outer liner 82, an inner liner 84, and a dome 86. Together, the outer liner 82, the inner liner 84, and the dome 86 define a combustion chamber 88. In addition, a diffuser 90 is positioned upstream of the combustion chamber 88. The diffuser 90 has an outer diffuser wall 90A and an inner diffuser wall 90B. The inner diffuser wall 90B is closer to the longitudinal centerline 12. The diffuser 90 receives a flow of air from the compressor section and provides the flow of compressed air to the combustor 80. In one embodiment, the diffuser 90 provides the flow of compressed air to a single circumferential row of fuel / air mixers 92. In one embodiment, the dome 86 of the combustor 80 is configured as a single annular dome, and the circumferential row of fuel / air mixers 92 are disposed within openings formed in the dome (air supply dome or combustor dome) 86. However, in other embodiments, multiple annular domes can also be used.

[0034] In one embodiment, the diffuser 90 can be used to slow down the high velocity, highly compressed air from the compressor (not shown) to an optimal velocity for the combustor. In addition, the diffuser 90 can also be configured to limit flow distortion as much as possible by avoiding flow effects like boundary layer separation. Like most other gas turbine engine components, the diffuser 90 is generally designed to be as light as possible to reduce the weight of the overall engine.

[0035] Fuel nozzles (not shown) provide fuel to the fuel / air mixers 92 according to the desired performance of the combustor 80 in various engine operating states. In one embodiment, the fuel nozzles are configured to provide fuel to the fuel / air mixers 92 in a circumferential row. In other embodiments, the fuel nozzles can be configured to provide fuel to the fuel / air mixers 92 in a circumferential row and in a radial row. Figure 2 In the illustrated embodiment, an outer shroud (e.g., an annular shroud) 94 and an inner shroud (e.g., an annular shroud) 96 are positioned upstream of the combustion chamber 88 in order to direct the flow of air into the fuel / air mixers 92. The outer shroud 94 and the inner shroud 96 can also direct a portion of the flow of air from the diffuser 90 to an outer passage 98 defined between the outer liner 82 and an outer casing 100 and to an inner passage 102 defined between the inner liner 84 and an inner casing 104. In addition, an inner support cone 106 is further shown as being connected to a nozzle support 108 using a plurality of bolts 110 and nuts 112. However, other combustion sections can include any other suitable structural configuration.

[0036] In some embodiments, the outer liner 82 and the inner liner 84 can be formed of a ceramic matrix composite (CMC), which is a non-metallic material with high temperature capability. Exemplary composite materials for such liners include silicon carbide, silicon, silica, or alumina-based materials, and combinations thereof. Generally, ceramic fibers are embedded in a matrix, such as an oxidation-stable reinforcing fiber, including monofilaments, such as sapphire and silicon carbide, as well as rovings and yarns, including silicon carbide, aluminum silicate, and short-cut whiskers and fibers, and optionally ceramic particles (e.g., oxides of Si, Al, Zr, Y, and combinations thereof) and inorganic fillers (e.g., pyrophyllite, wollastonite, mica, talc, kyanite, and montmorillonite). CMC materials can have a coefficient of thermal expansion in the range of about 1.3 x 10 -6 in / in / °F to about 3.5 x 10 -6 in / in / °F.

[0037] In contrast, other components of the combustor 80 or combustion section 26, such as the outer shell 100, the inner shell 104, and other support members of the combustion section 26, can be formed of a metal, such as a nickel-based superalloy (which can have a coefficient of thermal expansion in the range of about 8.3 to 8.6 x 10 -6 in / in / °F at temperatures in the range of about 1000°F to 1200°F) or a cobalt-based superalloy (which can have a coefficient of thermal expansion in the range of about 9.2 to 9.4 x 10 -6 in / in / °F). The outer liner 82 and the inner liner 84 can support the extreme temperature environment present in the combustion chamber 88.

[0038] The combustor 80 is also provided with an igniter 114. The igniter 114 is provided to ignite a fuel / air mixture supplied to the combustion chamber 88 of the combustor 80. The igniter 114 is attached to the outer shell 100 of the combustor 80 in a substantially fixed manner. Further, the igniter 114 extends generally in the axial direction A2, defining a distal end 116 that is positioned proximate an opening in the combustor members of the combustion chamber 88. The distal end 116 is positioned proximate an opening 118 in the outer liner 82 of the combustor 80 to the combustion chamber 88.

[0039] The outer liner 82 and the inner liner 84 have a plurality of holes (not shown) disposed therein. The holes are distributed along the surfaces of the outer liner 82 and the inner liner 84 to allow air to enter the combustion chamber 88. Alternatively, the outer liner 82 and the inner liner 84 can be made of a porous material. The outer liner 82 and the inner liner 84 contain the combustion process and introduce various air streams (intermediate, dilution, and cooling) into the combustion chamber 88.

[0040] In one embodiment, the dome 86 of the combustor 80, together with the outer liner 82 and the inner liner 84, define a swirler 130. As air enters the combustion chamber 88, the air flows through the swirler 130. The dome 86 and the swirler 130 function to create turbulence in the air stream to rapidly mix the air with the fuel. The swirler creates a localized low pressure area that forces some of the combustion products to recirculate, as shown in Figure 2 The dome 86 and the swirler 130 are designed to not create more turbulence than is required to sufficiently mix the fuel and air.

[0041] Figure 3 is a schematic view of the outer shroud 94 and the inner shroud 96 together with the outer housing 100 and the inner housing 104 defining, in conjunction, the air stream through the swirler 130 toward the combustion zone 155 within the combustion chamber 88, in accordance with an embodiment of the present disclosure. In this embodiment, the air stream 150 from the diffuser 90 Figure 3 is split into three air stream portions 152, 154, and 156 by the geometry of the outer shroud 94, the inner shroud 96, the outer housing 100, and the inner housing 104. The air stream portion 152 passes between the outer housing 100 and the outer shroud 94. The air stream portion 154 passes between the inner housing 104 and the inner shroud 96. The air stream portion 156 passes between the outer shroud 94 and the inner shroud 96 into the dome 86 and through the swirler 130 into the combustion zone 155 within the combustion chamber 88. The air stream portions 152 and 154 are lateral air streams, while the air stream portion 156 is a central air stream. This configuration is referred to as a “three-pass diffuser” because two lateral air streams 152 and 154 and a central air stream 156 are created after the air is output by the diffuser 90. The amount of air in the central air stream 156 and the amount of air in the lateral air streams 152 and 154 can be controlled and adjusted as needed depending on the desired energy output by the combustor 80 and ultimately the operating conditions of the turbine engine 10 Figure 1 . For example, the amount of air in the central air stream 156 can be controlled to optimize the total air pressure fed through the dome 86 of the combustor 80 to the swirler 130. In this embodiment, the air distribution is optimized by providing an air stream fed through the connected diffuser 90 and shrouds 94, 96 by capturing the total pressure feed, rather than the static pressure feed. This geometry eliminates the pressure losses associated with the rapid expansion of the air stream downstream of the diffuser outlet.

[0042] Figure 4is a schematic view of outer doors 190A between outer diffuser wall 90A and outer shroud 94 and inner doors 190B (e.g., flaps) between inner diffuser wall 90B and inner shroud 96 in accordance with an embodiment of the present disclosure. In one embodiment, outer doors 190A are disposed on outer diffuser wall 90A and inner doors 190B are disposed on inner diffuser wall 90B. In one embodiment, outer doors 190A are disposed between outer diffuser wall 90A and outer shroud 94 of diffuser 90. Also, inner doors 190B are disposed between inner diffuser wall 90B and inner shroud 96 of diffuser 90. In one embodiment, outer doors 190A are hingedly mounted to outer diffuser wall 90A of diffuser 90. Thus, outer doors 190A pivot or rotate to open / close an opening 192A between outer diffuser wall 90A and outer shroud 94. In one embodiment, inner doors 190B are hingedly mounted to inner diffuser wall 90B of diffuser 90. Thus, inner doors 190B also pivot or rotate to open / close an opening 192B between inner diffuser wall 90B and inner shroud 96. Air flow 160 to swirler 130 can be controlled (e.g., controlled opening or closing) by actuation of outer doors 190A, or inner doors 190B, or both. Although, in Figure 4 the present disclosure, outer doors 190A and inner doors 190B are shown as being rotatable, other types of doors can be used, such as slidable doors, etc. For example, when outer doors 190A and inner doors 190B are opened as shown in Figure 4 portion 161 of air flow 160 will escape through openings 192A and 192B, thus, only a remaining air flow portion 162 of air flow 160 continues to flow to swirler 130 or combustion chamber 88. In one embodiment, outer doors 190A or inner doors 190B or both are controlled to control the level of opening or closing of opening 192B between inner diffuser wall 90B and inner shroud 96 or opening 192A between outer diffuser wall 90A and outer shroud 94, thereby controlling the amount of air flow to dome 86 and swirler 130 and thus to combustion chamber 88. By controlling the level of opening / closing of outer doors 190A and / or inner doors 190B, the amount of air flow portion 161 that escapes through openings 192A and 192B can be controlled and thus the amount of air flow 162 that reaches swirler 130 and ultimately combustion chamber 88 can be controlled. It can be appreciated that outer doors 190A and inner doors 190B can be actuated independently of each other. For example, outer doors 190A can be opened to a certain level while inner doors 190B can remain closed or opened to another level or vice versa. For example, when outer doors 190A, inner doors 190B or both are partially opened, a first air flow portion 161 of air flow 160 escapes through opening 192B between inner diffuser wall 90B and inner shroud 96 and / or through opening 192A between outer diffuser wall 90A and outer shroud 94 and a second air flow portion 162 (e.g., a main air flow portion) of air flow 160 continues towards combustion chamber 88.

[0043] Figure 5A This is a schematic diagram illustrating the closed configuration of the outer door 190A and the inner door 190B according to an embodiment of the present disclosure. Figure 5B This is a schematic diagram illustrating the configuration of the outer door 190A and inner door 190B when opened according to an embodiment of the present disclosure. Figure 5A and 5B The airflow from diffuser 90 to outer cover 94 and inner cover 96 is also schematically depicted. Figure 5A and 5B The end 170 of the air compressor leading to the diffuser 90 is also shown. By changing the opening of the outer door 190A and / or the inner door 190B, the airflow reaching the swirler 130 and the combustion zone 155 between the outer liner 82 and the inner liner 84 can be controlled and / or altered to achieve optimal operation and performance of the burner 80. In one embodiment, the outer door 190A and the inner door 190B can resemble variable block blade (VBV) doors. The airflow from the diffuser 90 can be diverted so that the airflow is directed through the doors into the passageway, rather than primarily towards the swirler 130 entering the dome.

[0044] Using advanced cycles, combustor optimization (e.g., flow splitting) can be sandwiched between critical design points. For example, high total pressure ratio (OPR), high exhaust gas temperature (EGT) cycles can also have very efficient (i.e., low fuel-air ratio (FAR)) cruise cycle conditions. The airflow splitting can be a high dome splitting at takeoff (T / O) but lower during cruise to manage landing / takeoff (LTO) nitrous oxide (NOx) versus cruise combustion efficiency.

[0045] Figure 6A This is a schematic diagram illustrating the construction of a louver 200 according to an embodiment of the present disclosure, wherein the louver 200 is in an open or substantially unobstructed state around the central position of the airflow 204. Figure 6B This is a schematic diagram illustrating a construction using a veneer 200 (e.g., an actuable veneer) according to another embodiment of the present disclosure, the veneer 200 being in a closed or airflow-obstructing state. In one embodiment, such as Figure 6A and 6B As shown, the venetian blind 200 can be rotatably mounted to the housing 100. Figure 6A In the configuration shown, the louver 200 is rotated such that the opening 202 in the louver 200, located at the center position relative to the airflow 204, faces the airflow 204 output by the diffuser 90. As a result, most of the airflow 204 is directed towards the vortex 130 (e.g., at its center position) at the airflow 204. Figure 2 , 3 (As shown in Figure 4) it passes through opening 202 essentially without obstruction. InFigure 6A In the illustrated configuration, the openings 202 of the louvers 200 are substantially located at a central position with respect to the direction of the air flow 204, such that a majority of the air flow 204 passes through the openings 202 unimpeded at the central position of the air flow 204 and slightly impeded at the edges of the openings 202 at the edges of the air flow 204. In Figure 6B In the illustrated configuration, the louvers 200 are rotated such that the openings 202 in the louvers 200 face away from the air flow 204 output by the diffuser 90. As a result, a minor or minimal portion of the air flow 204 passes through the openings 202 of the louvers 200. For example, the louvers 200 can be rotated using a rotating arm 206. However, it is to be appreciated that other means for rotating the louvers 200 can also be used.

[0046] Figure 7A is a schematic diagram illustrating a configuration using louvers 210 in an open or substantially unimpeded air flow state toward the edge position of the air flow 214, in accordance with another embodiment of the present disclosure. Figure 7B is a schematic diagram illustrating a configuration using louvers 210 (e.g., actuatable louvers) in a closed or impeded air flow state, in accordance with another embodiment of the present disclosure. In one embodiment, as Figure 7A and 7B As illustrated, the louvers 210 can be rotatably mounted to the outer housing 100. In Figure 7A In the illustrated configuration, the louvers 210 are rotated such that the openings 212 in the louvers 210 face toward the edge of the air flow 214 output by the diffuser 90. As a result, a majority of the air flow 214 passes through the openings 212 substantially unimpeded at the edge position of the air flow 214 but impeded at the central position of the air flow 214 away from the cyclone 130. In Figure 7A In the illustrated configuration, the openings 212 of the louvers 210 are substantially located at an edge position with respect to the flow direction of the air flow 214, such that a majority of the air flow 214 passes through the openings 212 unimpeded at the edges of the air flow 214 but impeded at the central position of the air flow 214. In Figure 7B In the illustrated configuration, the louvers 210 are rotated such that the openings 212 in the louvers 210 face away from the air flow 214 output by the diffuser 90. As a result, a minor or minimal portion of the air flow 214 passes through the openings 212 of the louvers 210. For example, the louvers 210 can be rotated using a rotating arm 216. However, it is to be appreciated that other means for rotating the louvers 210 can also be used.

[0047] As can be appreciated, the configuration of the louvers 200 illustrated in Figure 6A and 6B may be used with the configuration of the louvers 210 illustrated in Figure 7A and7B The louver construction shown is combined in various ways. For example, louver 200 can be used to control the amount of airflow passing through the center of the airflow, while louver 200 can be used to control the amount of airflow passing through the edges of the airflow. This allows for increased or improved control over the airflow, and thus increases the adjustability of the burner's energy output.

[0048] Figure 8 This is a schematic diagram of a burner 80 according to an embodiment of the present disclosure, showing the boundary layer of the airflow when specific air pressure conditions are used at the compressor upstream of the diffuser. Figure 8 In the illustrated embodiment, air pressure from a compressor (not shown) upstream of diffuser 90 is controlled to control the boundary layer of airflow 300, causing airflow 300 to concentrate towards central location 302 to maintain a strong core, thereby generating an airflow with a concentrated central air distribution. This captures the total pressure supplied to dome 86 through outer shroud 94 and inner shroud 96 to increase fuel-air mixing in combustion chamber 88. In one embodiment, a laminar boundary layer airflow is generated to produce less skin friction, thereby maintaining a strong central pressure distribution, allowing a larger volume of airflow 300 to reach swirler 130 and ultimately combustion chamber 88.

[0049] One advantage of the construction of this combustor according to embodiments of this disclosure is that it provides an additional total pressure supply to the swirler 130, which can ultimately reduce pollutant emissions such as NOx and soot. This is particularly desirable in engines designed for supersonic cruise, as these engines operate under optimal conditions of high T3, low P3, and high fuel-air ratio to produce high NOx and soot. Other benefits may also exist, such as improved overall dome durability due to the increased total pressure supply to the cooling passages. However, care must be taken to ensure that the system still provides sufficient pressure drop for bushing and turbine cooling.

[0050] A combustor for a turbine engine includes: an outer liner, an inner liner, and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser configured to receive an airflow from a compressor section and supply a compressed airflow to the combustion chamber; and an outer shroud and an inner shroud located upstream of the combustion chamber, the outer shroud and the inner shroud configured to guide a portion of the airflow from the diffuser to the combustion chamber, wherein the diffuser is configured to output an airflow having a maximum air pressure at the center of the airflow, thereby optimizing the total air pressure supplied to the combustion chamber through the dome.

[0051] The burner of any of the preceding claims, wherein the diffuser includes an outer diffuser wall and an inner diffuser wall, an outer door is disposed on the outer diffuser wall and an inner door is disposed on the inner diffuser wall, wherein the outer door is configured to open or close an opening between the outer diffuser wall of the diffuser and the outer shroud, and wherein the inner door is configured to open or close another opening between the inner diffuser wall of the diffuser and the inner shroud.

[0052] The burner of any of the preceding claims, wherein the outer door is hingedly mounted to the outer diffuser wall and is configured to rotate to open or close an opening between the outer diffuser wall and the outer shroud, and wherein the inner door is hingedly mounted to the inner diffuser wall and is configured to rotate to open or close an opening between the inner diffuser wall and the inner shroud.

[0053] The burner of any of the preceding claims, wherein at least one of the outer door and the inner door is controllable to control a level of opening or closing of the opening between the inner diffuser wall and the inner shroud or the opening between the outer diffuser wall and the outer shroud, thereby controlling an amount of air flow supplied to the dome and swirler.

[0054] The burner of any of the preceding claims, wherein when at least one of the outer door and the inner door is partially open, a first portion of the air flow escapes through the opening between the inner diffuser wall and the inner shroud or through the opening between the outer diffuser wall and the outer shroud, a major second portion of the air flow continues toward the combustion chamber.

[0055] The burner of any of the preceding claims, further comprising a louver disposed downstream of the diffuser, wherein the louver is configured and arranged to control an amount of air flow reaching the combustion chamber.

[0056] The burner of any of the preceding claims, wherein the louver includes openings located at a central position relative to the air flow, such that when faced with the air flow output by the diffuser, a majority of the air flow passes through the openings substantially unimpeded at the central position of the air flow toward the combustion chamber and impeded at the edges of the air flow.

[0057] The burner of any of the preceding claims, wherein the louver includes openings located at an edge position relative to the air flow, such that when faced with the air flow output by the diffuser, a majority of the air flow passes through the openings substantially unimpeded at the edge position away from the combustion chamber and impeded at the central position of the air flow.

[0058] The combustor of any of the preceding claims, wherein the air stream output by the diffuser is generated by an air compressor in the compressor section upstream of the diffuser, wherein air pressure from the compressor section is controlled to control a boundary layer of the air stream output by the diffuser to produce the air stream with a concentrated center air distribution to increase fuel-air mixing in the combustion chamber.

[0059] A turbine engine comprising: (A) a compressor section configured to produce compressed air; (B) a turbine section downstream of the compressor section; and (C) a combustion section disposed between the compressor section and the turbine section, the combustion section comprising a combustor comprising: (a) an outer liner, an inner liner, and a dome together defining a combustion chamber; (b) a diffuser upstream of the combustion chamber, the diffuser configured to receive an air stream from the compressor section and provide a compressed air stream to the combustion chamber; and (c) an outer shroud and an inner shroud upstream of the combustion chamber, the outer shroud and the inner shroud configured to direct a portion of the air stream from the diffuser to the combustion chamber, wherein the diffuser is configured to output an air stream having a maximum amount of air pressure at a center of the air stream to optimize total air pressure fed through the dome to the combustion chamber.

[0060] The turbine engine of the preceding claim, further comprising an igniter extending into the combustor through an opening in the combustor, wherein the igniter is configured to ignite a fuel and air mixture supplied to the combustion chamber of the combustor.

[0061] The turbine engine of any of the preceding claims, wherein the diffuser comprises an outer diffuser wall and an inner diffuser wall, an outer door disposed on the outer diffuser wall and an inner door disposed on the inner diffuser wall, wherein the outer door is configured to open or close an opening between the outer diffuser wall of the diffuser and the outer shroud, and wherein the inner door is configured to open or close another opening between the inner diffuser wall of the diffuser and the inner shroud.

[0062] The turbine engine of any of the preceding claims, wherein the outer door is hingedly mounted to the outer diffuser wall and the outer door is configured to rotate to open or close the opening between the outer diffuser wall and the outer shroud, and wherein the inner door is hingedly mounted to the inner diffuser wall and the inner door is configured to rotate to open or close the opening between the inner diffuser wall and the inner shroud.

[0063] The turbine engine according to any of the preceding claims, wherein at least one of the outer door and the inner door is controllable to control a level of opening or closing of the opening between the inner diffuser wall and the inner shroud or the opening between the outer diffuser wall and the outer shroud, thereby controlling an amount of air flow to the dome and swirler.

[0064] The turbine engine according to any of the preceding claims, wherein when at least one of the outer door and the inner door is partially open, a first portion of the air flow escapes through the opening between the inner diffuser wall and the inner shroud or through the opening between the outer diffuser wall and the outer shroud, and a major second portion of the air flow continues towards the combustion chamber.

[0065] The turbine engine according to claim 10, further comprising a louver disposed downstream of the diffuser, wherein the louver is constructed and arranged to control an amount of air flow to the combustion chamber.

[0066] The turbine engine according to any of the preceding claims, wherein the louver comprises openings located at a central position relative to the air flow, such that when faced with the air flow output by the diffuser, a majority of the air flow passes through the openings substantially unimpeded at a central position of the air flow towards the combustion chamber and impeded at an edge of the air flow.

[0067] The turbine engine according to any of the preceding claims, wherein the louver comprises openings located at an edge position relative to the air flow, such that when faced with the air flow output by the diffuser, a majority of the air flow passes through the openings substantially unimpeded at an edge position away from the combustion chamber and impeded at a central position of the air flow.

[0068] The turbine engine according to any of the preceding claims, wherein the compressor section comprises an air compressor, wherein the air flow output by the diffuser is generated by the air compressor in the compressor section upstream of the diffuser, wherein an air pressure from the compressor section is controlled to control a boundary layer of the air flow output by the diffuser, thereby generating the air flow with a concentrated central air distribution in order to increase a fuel-air mixture in the combustion chamber.

[0069] A method of controlling an air flow in a combustor according to any of the preceding requirements, the combustor having a diffuser, a dome, and a combustion chamber, the method comprising: injecting compressed air from a compressor section upstream of the diffuser to the diffuser of the combustor; outputting an air flow from the diffuser; and optimizing an air pressure amount to maximize a pressure of the air flow at a center of the air flow to optimize a total air pressure fed through the dome of the combustor to the combustion chamber of the combustor, wherein optimizing an air pressure amount comprises changing an amount of air flow that escapes at an edge of the air flow.

[0070] While the foregoing description has been directed to the preferred embodiments of the present disclosure, it will be apparent to those skilled in the art that other variations and modifications can be made within the spirit or scope of the disclosure. Furthermore, features described in conjunction with one embodiment can be used in conjunction with other embodiments, even if such features are not explicitly stated above.

Claims

1. A combustor for a turbine engine, characterized in that, The burner includes: Together they define the outer lining, inner lining, and dome of the combustion chamber; A diffuser, positioned upstream of the combustion chamber, configured to receive airflow from the compressor section and supply compressed airflow to the combustion chamber; and An outer cover and an inner cover, located upstream of the combustion chamber, are configured to guide a portion of the airflow from the diffuser into the combustion chamber. The diffuser is configured to output an airflow with the maximum air pressure at the center of the airflow, thereby optimizing the total air pressure supplied to the combustion chamber through the dome. The diffuser includes an outer diffuser wall and an inner diffuser wall, with an outer door disposed on the outer diffuser wall and an inner door disposed on the inner diffuser wall. The outer door is configured to open or close the opening between the outer diffuser wall and the outer casing of the diffuser, and The inner door is configured to open or close another opening between the inner diffuser wall and the inner cover of the diffuser.

2. The burner according to claim 1, characterized in that, in, The outer door hinge is mounted to the outer diffuser wall, and the outer door is configured to rotate to open or close the opening between the outer diffuser wall and the outer casing. The inner door hinge is mounted to the inner diffuser wall, and the inner door is configured to rotate to open or close the opening between the inner diffuser wall and the inner cover.

3. The burner according to claim 1, characterized in that, in, At least one of the outer door and the inner door is controllable to control the level of opening or closing of the opening between the inner diffuser wall and the inner shroud or the opening between the outer diffuser wall and the outer shroud, thereby controlling the amount of airflow supplied to the dome and the vortex.

4. The burner according to claim 3, characterized in that, in, When at least one of the outer door and the inner door is partially opened, a first portion of the airflow escapes through the opening between the inner diffuser wall and the inner shroud or through the opening between the outer diffuser wall and the outer shroud, and a main second portion of the airflow continues toward the combustion chamber.

5. The burner according to claim 1, characterized in that, in, The airflow output from the diffuser is generated by an air compressor in the compressor section located upstream of the diffuser, wherein the air pressure from the compressor section is controlled to control the boundary layer of the airflow output from the diffuser, thereby generating the airflow with a concentrated central air distribution to increase fuel-air mixing in the combustion chamber.

6. A combustor for a turbine engine, characterized in that, The burner includes: Together they define the outer lining, inner lining, and dome of the combustion chamber; A diffuser, located upstream of the combustion chamber, is configured to receive airflow from the compressor section and supply compressed airflow to the combustion chamber; An outer cover and an inner cover, located upstream of the combustion chamber, the outer cover and the inner cover being configured to guide a portion of the airflow from the diffuser into the combustion chamber; and A louver disposed downstream of the diffuser, the louver being constructed and arranged to control the amount of airflow reaching the combustion chamber, the louver including an opening. The diffuser is configured to output an airflow with maximum air pressure at its center, thereby optimizing the total air pressure supplied to the combustion chamber through the dome. The opening is located at the center of the airflow, such that when the opening faces the airflow output from the diffuser, most of the airflow passes substantially unimpeded through the opening toward the combustion chamber at the center of the airflow, while being obstructed at the edges of the airflow. The opening is located at an edge position relative to the airflow, such that when the opening faces the airflow output by the diffuser, most of the airflow passes through the opening substantially unimpeded away from the combustion chamber at the edge position, while being obstructed at the center position of the airflow.

7. A turbine engine, characterized in that, include: (A) A compressor section configured to generate compressed air; (B) Turbine section, which is located downstream of the compressor section; and (C) A combustion section, disposed between the compressor section and the turbine section, the combustion section including a burner, the burner comprising: (a) Together they define the outer liner, inner liner, and dome of the combustion chamber; (b) A diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive airflow from the compressor section and provide compressed airflow to the combustion chamber; and (c) An outer cover and an inner cover, the outer cover and the inner cover being located upstream of the combustion chamber, the outer cover and the inner cover being configured to guide a portion of the airflow from the diffuser into the combustion chamber. The diffuser is configured to output an airflow with the maximum air pressure at the center of the airflow, thereby optimizing the total air pressure supplied to the combustion chamber through the dome. The diffuser includes an outer diffuser wall and an inner diffuser wall, with an outer door disposed on the outer diffuser wall and an inner door disposed on the inner diffuser wall. The outer door is configured to open or close the opening between the outer diffuser wall and the outer casing of the diffuser, and The inner door is configured to open or close another opening between the inner diffuser wall and the inner cover of the diffuser.

8. The turbine engine according to claim 7, characterized in that, It further includes an igniter extending into the burner through an opening in the burner. The igniter is configured to ignite the fuel and air mixture supplied to the combustion chamber of the burner.

9. The turbine engine according to claim 7, characterized in that, in, The outer door hinge is mounted to the outer diffuser wall, and the outer door is configured to rotate to open or close the opening between the outer diffuser wall and the outer casing. The inner door hinge is mounted to the inner diffuser wall, and the inner door is configured to rotate to open or close the opening between the inner diffuser wall and the inner cover.

10. The turbine engine according to claim 7, characterized in that, in, At least one of the outer door and the inner door is controllable to control the level of opening or closing of the opening between the inner diffuser wall and the inner shroud or the opening between the outer diffuser wall and the outer shroud, thereby controlling the amount of airflow supplied to the dome and the vortex.

11. The turbine engine according to claim 10, characterized in that, in, When at least one of the outer door and the inner door is partially opened, a first portion of the airflow escapes through the opening between the inner diffuser wall and the inner shroud or through the opening between the outer diffuser wall and the outer shroud, and a main second portion of the airflow continues toward the combustion chamber.

12. The turbine engine according to claim 7, characterized in that, It further includes louvers disposed downstream of the diffuser, wherein the louvers are configured and arranged to control the amount of airflow reaching the combustion chamber.

13. The turbine engine according to claim 12, characterized in that, in, The louver includes an opening located at the center of the airflow, such that when the opening faces the airflow output by the diffuser, most of the airflow passes substantially unimpeded through the opening toward the combustion chamber at the center of the airflow, while being obstructed at the edges of the airflow.

14. The turbine engine according to claim 12, characterized in that, in, The louver includes an opening located at an edge relative to the airflow, such that when the opening faces the airflow output by the diffuser, most of the airflow passes substantially unimpeded through the opening away from the combustion chamber at the edge position, while being obstructed at the center position of the airflow.

15. The turbine engine according to claim 7, characterized in that, in, The compressor section includes an air compressor, wherein the airflow output from the diffuser is generated by the air compressor in the compressor section upstream of the diffuser, wherein the air pressure from the compressor section is controlled to control the boundary layer of the airflow output from the diffuser, thereby generating the airflow with a concentrated central air distribution to increase fuel-air mixing in the combustion chamber.

16. A method for controlling airflow in a burner according to any one of claims 1-6, the burner having a diffuser, a dome, and a combustion chamber, characterized in that, The method includes: Compressed air is injected from the compressor section upstream of the diffuser into the diffuser of the burner; An airflow is output from the diffuser; and Optimize the air pressure to maximize the pressure of the airflow at its center, thereby optimizing the total air pressure supplied to the combustion chamber of the burner through the burner's dome. Optimizing the air pressure includes changing the amount of airflow escaping at the edge of the airflow.

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