Combustor

Abstract

A combustor includes a combustion chamber having an outer liner and an inner liner and defining a first combustion zone; an annular dome coupled to the outer liner and the inner liner; and a trapped vortex chamber extending from at least one of the outer liner or the inner liner and defining a second combustion zone. A plurality of first mixing assemblies are disposed through the annular dome and operable to inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are disposed at the trapped vortex chamber and operable to inject a second fuel-air mixture into a second combustion zone defined in the trapped vortex chamber to produce a combustion gas. The steam system includes a steam injector in fluid communication with the trapped vortex chamber. A steam injector is operable to inject steam into the trapped vortex chamber, and the steam is mixed with the combustion gas.

Description

Technical Field

[0001] The present disclosure generally relates to combustors, such as combustors for turbine engines. Background Art

[0002] A turbine engine generally comprises a fan and a core section arranged in flow communication with each other. A combustor is arranged in the core section to generate combustion gases for driving a turbine in the core section of the turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0003] The foregoing and other features and advantages will be apparent from the following more particular description of various exemplary embodiments, as illustrated in the drawings, in which like reference numerals generally indicate identical, functionally similar, or structurally similar elements.

[0004] Figure 1 is a schematic cross-sectional view of a turbine engine according to the present disclosure, taken along a longitudinal centerline axis of the turbine engine.

[0005] Figure 2 is taken along the longitudinal centerline axis of the turbine engine according to the present disclosure Figure 1 A schematic cross-sectional view of a combustor of a turbine engine.

[0006] Figure 3 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0007] Figure 4 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0008] Figure 5 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0009] Figure 6 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0010] Figure 7 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0011] Figure 8 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0012] Fig. 9is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0013] Fig.10 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0014] Fig.11 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment.

[0015] Fig.12 is a schematic cross-sectional view of a combustor of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. DETAILED DESCRIPTION

[0016] Features, advantages and embodiments of the present disclosure are set forth or apparent by considering the following detailed description, drawings and claims.In addition, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0017] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0018] As used herein, the terms “first,” “second,” “third,” and “fourth” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of the respective components.

[0019] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing.

[0020] The terms "front" and "rear" refer to relative positions within a turbine engine or vehicle, and refer to the normal operating attitude of the turbine engine or vehicle. For example, with respect to a turbine engine, front refers to a position closer to the engine inlet, while rear refers to a position closer to the engine nozzle or exhaust.

[0021] As used herein, the terms "low," "medium" (or "medium"), and "high," or their respective comparatives (e.g., "lower" and "higher," as applicable), when used with a compressor, combustor, turbine, shaft, fan, or turbine engine component, refer to relative pressures, relative speeds, relative temperatures, or relative power outputs within an engine, unless otherwise specified. For example, a "low power" setting defines an engine or combustor that is configured to operate at a power output lower than a "high power" setting for the engine or combustor, while a "medium power" setting defines an engine or combustor that is configured to operate at a power output higher than the "low power" setting and lower than the "high power" setting. The terms "low," "medium" (or "medium"), or "high" in such above-mentioned terms may additionally or alternatively be understood as relative to a minimum allowable speed, pressure, or temperature, or relative to a minimum or maximum allowable speed, pressure, or temperature for normal, desired, steady-state, etc., operation of the engine.

[0022] The various power levels of the turbine engines described in detail herein are defined as percentages of the maximum engine rated thrust at sea level static (SLS). Low power operation or conditions include, for example, less than thirty percent (30%) of the SLS maximum engine rated thrust of the turbine engine. Medium power operation or conditions include, for example, thirty percent (30%) to eighty-five percent (85%) of the SLS maximum engine rated thrust of the turbine engine. High power operation or conditions include, for example, greater than eighty-five percent (85%) of the SLS maximum engine rated thrust of the turbine engine. The value of the thrust of each of the low power operation, medium power operation, and high power operation of the turbine engine is exemplary only, and other values ​​of thrust can be used to define low power operation, medium power operation, and high power operation.

[0023] Unless otherwise indicated herein, the terms "coupled," "fixed," "attached," "connected," and the like refer to both direct coupling, fixing, attachment, or connection as well as indirect coupling, fixing, attachment, or connection through one or more intermediate components or features.

[0024] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0025] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of the turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc around the centerline of the turbine engine.

[0026] As used herein, the term "trapped vortex chamber" or "TVC" generally refers to one or more chambers of a combustor that are in fluid communication with a main combustion chamber of the combustor and that at least partially mix fuel in a swirling vortex of compressed air within the one or more chambers.

[0027] Here and throughout the specification and claims, range limitations are combined and interchanged. Unless the context or language indicates otherwise, such ranges are identified and include all subranges contained therein. For example, all ranges disclosed herein include the endpoints, and the endpoints can be combined independently of each other.

[0028] The combustor of a turbine engine (such as an aircraft turbine engine) ignites a fuel and air mixture to produce combustion gases, which in turn drive one or more turbines of the turbine engine, thereby rotating one or more loads (e.g., fans, propellers, etc.). Concerns about air pollution have led to stricter combustion emission standards. These standards regulate the nitrogen oxides (NO x ), non-volatile particulate matter (nvPM), and other types of exhaust emissions. nvPM includes, for example, soot, smoke, etc. Typically, NO is formed during the combustion process due to the high flame temperature in the burner. x . Turbine engine design trade-offs are necessary to meet requirements for noise, emissions, fuel burn, cost, weight, and performance. As temperatures increase in the combustor, NO x The generation increases due to higher temperatures. In turbine engine design, it is difficult to balance the reduction of NO x emissions, nvPM emissions, carbon monoxide (CO) and noise while achieving improved engine performance. For example, combustor design changes to achieve lower emissions must not impact the combustion system's ability to meet performance and certification requirements throughout the aircraft's operating cycle.

[0029] In addition to balancing lower emissions while achieving improved engine performance, another trade-off is reducing the specific fuel consumption (SFC) of a turbine engine. Specific fuel consumption is the amount of fuel consumed per unit of power output of a turbine engine. Therefore, a lower SFC means that less fuel is consumed to achieve a specific power output of the turbine engine. Some turbine engines utilize combustors in which steam is injected into the combustion chamber through a fuel nozzle. Injecting steam into the combustion chamber can reduce the SFC while also reducing NO xEmissions. For example, the more steam injected into the combustor, the more the SFC will be reduced. However, burning steam will increase CO emissions and may cause flameout because the steam will block the flame (e.g., reduce oxygen in the combustion chamber). In addition, such turbine engines that inject steam from the fuel nozzles can achieve up to about 5% water-to-air ratio (WAR) in the combustor before flameout occurs. Therefore, such turbine engines are limited in the amount of emissions and SFC reduction that can be achieved through steam injection before flameout.

[0030] Thus, embodiments of the present disclosure provide a system and method for balancing the need for low fuel combustion and low emissions (e.g., NO x The present invention provides a turbine engine having a burner, the burner having a trapped vortex cavity (TVC) connected to the main combustion zone fluid of the combustion chamber of the burner. A first flame is generated in the main combustion zone of the combustion chamber, and the first flame generates combustion gases in the combustion chamber. A second flame is generated in the TVC, and the second flame produces combustion gases in the TVC. The turbine engine includes a steam system that generates steam from the exhaust gas of the turbine engine. The steam system injects steam downstream or upstream of the second flame in the TVC. The steam is mixed with the combustion gases in the TVC, and then the TVC injects the steam and the combustion gases into the combustion chamber downstream of the main combustion zone. The first flame in the main combustion zone provides flame stability in the burner under different operating conditions (e.g., low power, medium power and high power).

[0031] The TVC enables a greater amount of steam to be injected into the burner without sacrificing the operability of the burner as compared to a burner without the benefit of the present disclosure. For example, steam is injected into the TVC away from the main combustion zone to avoid flameout of the first flame in the main combustion zone because the steam is kept away from the first flame. This configuration of injecting steam downstream of the flame and within the TVC enables a greater amount of steam to be injected into the burner to reduce emissions and reduce SFC while providing flame stability (e.g., avoiding flameout) as compared to a burner without the benefit of the present disclosure. The present disclosure provides up to 60% WAR, thereby enabling a large amount of steam to reduce emissions and reduce SFC while providing flame stability in the burner (e.g., avoiding flameout).

[0032] Now referring to the accompanying drawings, Figure 1 is a schematic cross-sectional view of a turbine engine 10 taken along a longitudinal centerline axis 12 of the turbine engine 10 according to an embodiment of the present disclosure. Figure 1As shown, the turbine engine 10 defines an axial direction A (extending parallel to a longitudinal centerline axis 12 for reference) and a radial direction R perpendicular to the axial direction A. Generally, the turbine engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream of the fan section 14 .

[0033] The depicted core turbine engine 16 generally includes a casing 18 that is substantially tubular and defines an annular inlet 20. Figure 1 As shown schematically, the casing 18 encloses, in serial flow relationship: a compressor section 21, which includes a supercharger or low pressure (LP) compressor 22, followed downstream by a high pressure (HP) compressor 24; a combustion section 26; a turbine section 27, which includes a high pressure (HP) turbine 28, followed downstream by a low pressure (LP) turbine 30; and an injection exhaust nozzle section 32. A high pressure (HP) shaft 34 or spool drivingly connects the HP turbine 28 to the HP compressor 24 so that the HP turbine 28 and the HP compressor 24 rotate in unison. A low pressure (LP) shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22 so that the LP turbine 30 and the LP compressor 22 rotate in unison. The compressor section 21, the combustion section 26, the turbine section 27, and the injection exhaust nozzle section 32 together define a core air flow path.

[0034] for Figure 1 In the embodiment depicted in FIG. 1 , fan section 14 includes a fan 38 (eg, a variable pitch fan) having a plurality of fan blades 40 coupled to a disk 42 in a spaced-apart manner. Figure 1 As shown, fan blades 40 extend outwardly from disk 42 generally in radial direction R. Each fan blade 40 can rotate relative to disk 42 about pitch axis P by virtue of fan blades 40 being operably coupled to actuating members 44, which are configured to collectively and uniformly change the pitch of fan blades 40. Fan blades 40, disk 42, and actuating members 44 can rotate together about longitudinal centerline axis 12 via fan shaft 45, which is powered by LP shaft 36 across a power gearbox (also referred to as gearbox assembly 46). Gearbox assembly 46 is Figure 1 The gearbox assembly 46 includes a plurality of gears for adjusting the rotational speed of the fan shaft 45 and, therefore, the rotational speed of the fan 38 relative to the LP shaft 36 .

[0035] Still reference Figure 1In an exemplary embodiment of the present invention, disk 42 is covered by a rotatable fan hub 48 that is aerodynamically shaped to facilitate airflow through a plurality of fan blades 40. In addition, fan section 14 includes an annular fan case or nacelle 50 that circumferentially surrounds fan 38 and at least a portion of core turbine engine 16. Nacelle 50 is supported relative to core turbine engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. In addition, a downstream section 54 of nacelle 50 extends over an outer portion of core turbine engine 16 to define a bypass airflow passage 56 therebetween.

[0036] During operation of the turbine engine 10, a quantity of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the fan section 14. As the quantity of air 58 passes through the fan blades 40, a first portion of air 62 is directed or directed into the bypass airflow passage 56, while a second portion of air 64 is directed or directed into the upstream section of the core air flow path, or more specifically, into the annular inlet 20 of the LP compressor 22. The ratio between the first portion of air 62 and the second portion of air 64 is generally referred to as the bypass ratio. The pressure of the second portion of air 64 is then increased to form compressed air 65, and the compressed air 65 is directed through the HP compressor 24 and into the combustion section 26, where the compressed air 65 is mixed with fuel and combusted to provide combustion gases 66.

[0037] The combustion gases 66 are directed into and expanded through the HP turbine 28, wherein a portion of the heat and kinetic energy from the combustion gases 66 is extracted via successive stages of HP turbine stator blades 68 coupled to the casing 18 and HP turbine rotor blades 70 coupled to the HP shaft 34, thereby rotating the HP shaft 34, thereby supporting operation of the HP compressor 24. The combustion gases 66 are then directed into and expanded through the LP turbine 30. Here, a second portion of the heat and kinetic energy is extracted from the combustion gases 66 via successive stages of LP turbine stator blades 72 coupled to the casing 18 and LP turbine rotor blades 74 coupled to the LP shaft 36, thereby rotating the LP shaft 36, thereby supporting operation of the LP compressor 22 and rotation of the fan 38 via the gearbox assembly 46.

[0038] 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, also providing propulsive thrust, as it is directed through the bypass airflow passage 56 before being discharged from the fan nozzle exhaust section 76 of the turbine engine 10. 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 directing the combustion gases 66 through the core turbine engine 16.

[0039] As described in detail above, the second portion of air 64 is mixed with fuel 67 in the combustion section 26 to produce combustion gases 66. The turbine engine 10 also includes a fuel system 80 for providing fuel 67 to the combustion section 26. The fuel system 80 includes a fuel tank (not shown) for storing fuel therein and one or more fuel injector lines 82 for providing fuel 67 to the combustion section 26, as described in further detail below. The fuel system 80 may include one or more valves for controlling the amount of fuel 67 provided to the combustion section 26. The fuel 67 may be any type of fuel for a turbine engine, including a liquid fuel or a gaseous fuel. For example, the fuel 67 may be JetA, sustainable aviation fuel (SAF) including biofuels, hydrogen-based fuel (H2), etc.

[0040] Turbine engine 10 includes a steam system 90 in fluid communication with exhaust nozzle section 32. Steam system 90 extracts steam 69 from exhaust gas in exhaust nozzle section 32. Steam system 90 includes one or more steam lines 92 to provide steam 69 to combustion section 26, as described in further detail below.

[0041] Figure 1 The turbine engine 10 depicted in the drawings is provided as an example only. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 38 may be configured in any other suitable manner (e.g., as a fixed pitch fan) and may also be supported using any other suitable fan frame configuration. In addition, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In still other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, a propfan engine, a turbojet engine, a turboprop engine, and / or a turboshaft engine.

[0042] Figure 2 is along the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1 ) intercepted turbine engine 10 ( Figure 1 ) is a schematic cross-sectional view of a combustor 200. In an exemplary embodiment, the combustion section 26 ( Figure 1 ) includes a combustor 200 having a combustion chamber 202 defined by an outer liner 204 and an inner liner 206. The combustor 200 is an annular combustor. However, the combustor 200 may include any type of combustor, for example, an annular combustor, a double annular combustor, a can annular combustor, etc.

[0043] The outer liner 204 and the inner liner 206 surround the turbine engine 10 ( Figure 1) is annular about the longitudinal centerline axis 12 of the combustor 200. The outer liner 204 defines the radial outer boundary of the combustion chamber 202, and the inner liner 206 defines the radial inner boundary of the combustion chamber 202. The outer liner 204 and the inner liner 206 are radially inwardly spaced from an outer combustor casing 208 and an inner combustor casing 209 extending circumferentially around the outer liner 204 and the inner liner 206, respectively. At least one of the outer liner 204 or the inner liner 206 includes one or more liner air holes 205, which are operable to guide the compressed air 65 through at least one of the outer liner 204 or the inner liner 206 and into the combustion chamber 202 to cool at least one of the outer liner 204 or the inner liner 206 (for example, by film cooling). The combustor 200 also includes an annular dome 210 upstream of the outer liner 204 and the inner liner 206 and coupled to the outer liner 204 and the inner liner 206. The annular dome 210 defines the upstream end of the combustion chamber 202. The combustion chamber 202 extends from the annular dome 210 to a combustion chamber outlet 211 .

[0044] A plurality of first mixing components 212 ( Figure 2 The plurality of first mixing assemblies 212 (only one of which is shown) are circumferentially spaced around the annular dome 210 to deliver a first mixture of fuel and air to the combustion chamber 202. For example, the plurality of first mixing assemblies 212 deliver the first mixture of fuel and air to the first combustion zone 202a of the combustion chamber 202, as described in further detail below. The first combustion zone 202a is also referred to as the main combustion zone. Figure 2 In FIG. 1 , the first mixing assembly 212 is shown to include a first mixer 214 and a first mixing assembly swirler 216. The combustor 200 includes a plurality of first fuel injectors 218 ( Figure 2 2 (only one is shown), wherein each of the plurality of first fuel injectors 218 is coupled in flow communication with each respective first mixing assembly 212. The plurality of first fuel injectors 218 are circumferentially spaced about the annular dome 210 and extend radially from the outer combustor casing 208 to the plurality of first mixing assemblies 212. In some embodiments, the plurality of first fuel injectors 218 extend from the inner combustor casing 209, or may extend from both the outer combustor casing 208 and the inner combustor casing 209.

[0045] A plurality of second mixing components 220 ( Figure 2 The plurality of second mixing assemblies 220 are circumferentially spaced about the outer liner 204 to deliver a second mixture of fuel and air to the second combustion zone 202b, as described in further detail below. The second combustion zone 202b is also referred to as a secondary combustion zone. The second combustion zone 202b is configured to inject combustion gases 66 from the second combustion zone 202b axially rearward of the first combustion zone 202a, as described in further detail below. Each of the plurality of second mixing assemblies 220 includes a second mixer 222. The plurality of second fuel injectors 224 ( Figure 2A plurality of second fuel injectors 224 are circumferentially spaced apart around the outer liner 204 and extend radially from the outer combustor casing 208 to the plurality of second mixing assemblies 220.

[0046] The combustor 200 includes a TVC 230 extending from the outer liner 204 and defining a second combustion zone 202b. Figure 2 Although one TVC 230 is shown and described in the drawings, the combustor 200 may include one or more TVCs 230. The TVC 230 is a cavity and is used to generate a trapped vortex of the fuel-air mixture, as further described below. For example, the plurality of second mixing assemblies 220 are positioned to radially inject the fuel 67 into the TVC 230, as further described below. Although Figure 2 The TVC 230 is shown extending from the outer liner 204, but the TVC 230 may extend from the inner liner 206. In some embodiments, both the outer liner 204 and the inner liner 206 include a TVC 230 extending therefrom. The TVC 230 includes an outlet axially rearward of the annular dome 210. In this manner, the TVC 230 is operable to inject the combustion gases 66 downstream of the annular dome 210.

[0047] The TVC 230 is defined by one or more walls (collectively referred to as "walls" of the TVC 230). For example, the TVC 230 is defined by a first wall 232, a second wall 234, a third wall 236, and a fourth wall 238. The first wall 232 and the second wall 234 extend generally radially, and the third wall 236 and the fourth wall 238 extend generally axially. The first wall 232 defines a front wall of the TVC 230, the second wall 234 defines a rear wall of the TVC 230, the third wall 236 defines a first axial wall of the TVC 230, and the fourth wall 238 defines a second axial wall of the TVC 230. The second wall 234 is axially spaced behind the first wall 232. The first wall 232 extends generally radially from a front end of the third wall 236 to a front end of the fourth wall 238. The second wall 234 extends generally radially to a rear end of the third wall 236. The third wall 236 is radially spaced outward from the fourth wall 238. The third wall 236 extends axially from the radially outer end of the first wall 232 to the radially outer end of the second wall 234. The fourth wall 238 extends axially from the radially inner end of the first wall 232 to the TVC opening 240 defined between the rear end of the fourth wall 238 and the axial forward surface of the second wall 234.

[0048] The TVC 230 is defined between the first wall 232, the second wall 234, the third wall 236, and the fourth wall 238. In this manner, the TVC 230 is positioned generally radially outward from the combustion chamber 202. The TVC opening 240 is an opening in the outer liner 204 to provide flow communication from the TVC 230 to the combustion chamber 202. In particular, the TVC opening 240 is positioned downstream of the first combustion zone 202a. Although Figure 2 The TVC 230 shown in FIG. 2 includes a substantially rectangular cross-section, but the TVC 230 may include any shape.

[0049] The TVC 230 includes a partition wall 237 extending radially inward from the third wall 236 into the TVC 230. The partition wall 237 axially divides the TVC 230 into an upstream portion 231 and a downstream portion 233 downstream of the upstream portion 231. In this manner, the downstream portion 233 is axially rearward of the upstream portion 231. The upstream portion 231 is sized to contain the second combustion zone 202b so that a first vortex 247 of the compressed air 65 is formed within the upstream portion 231 and combustion occurs in the downstream portion 231, as described in further detail below. The downstream portion 233 is sized to receive the steam 69. For example, the upstream portion 231 is defined axially rearward from the first wall 232 to approximately 50% of the total axial length of the TVC 230. However, the upstream portion 231 may be confined to any portion of the total axial length of the TVC 230 as long as there is space within the upstream portion 231 for generating a vortex within the upstream portion 231 and there is space within the downstream portion 333 for steam injection within the downstream portion 333. The dividing wall 237 only partially extends into the TVC 230 such that a gap 239 is radially defined between the dividing wall 237 and the fourth wall 238. In some embodiments, the dividing wall 237 extends radially outward from the fourth wall 238 into the TVC 230 to axially divide the TVC 230 into the upstream portion 231 and the downstream portion 233. In such an embodiment, the gap 239 is radially defined between the dividing wall 237 and the third wall 236. The upstream portion 231 defines the second combustion zone 202b, and the TVC opening 240 is defined at the downstream portion 233. In Figure 2 In the embodiment of the present invention, the upstream portion 231 is a primary TVC and the downstream portion is a secondary TVC, as further described below. The volume of the upstream portion 231 is greater than the volume of the downstream portion 233. This configuration provides a sufficient amount of time for combustion to complete within the upstream portion 231. In some embodiments, the volume of the upstream portion 231 is less than the volume of the downstream portion 233. This configuration provides a sufficient amount of time for the steam 69 in the downstream portion 233 to mix with the combustion gases 66 from the upstream portion 231, as further described below. In some embodiments, the volume of the upstream portion 231 is substantially equal to or less than the downstream portion 233.

[0050] The fourth wall 238 is radially spaced from the outer liner 204 such that a gap 241 is defined between the fourth wall 238 and the outer liner 204. The gap 241 allows cooling air (e.g., compressed air 65) to cool a forward portion of the outer liner 204 (e.g., a portion forward of the TVC opening 240) and cool the fourth wall 238. The fourth wall 238 is coupled to the outer liner 204 by a liner extension 243 that extends from the outer liner 204 to a rearward end of the fourth wall 238. The liner extension 243 connects the fourth wall 238 and the outer liner 204. The liner extension 243 includes one or more liner extension holes 207 that extend generally axially through the liner extension 243. The one or more liner extension holes 207 are operable to direct the compressed air 65 through the liner extension 243 and into the combustion chamber 202 to cool the liner extension 243.

[0051] At least one of the walls defining the TVC 230 includes a steam path 242 defined therein. For example, the first wall 232, the second wall 234, the third wall 236, the fourth wall 238, and the partition wall 237 each include a portion of the steam path 242, such that the steam path 242 is disposed within the first wall 232, the second wall 234, the third wall 236, and the fourth wall 238. The steam system 90 ( Figure 1 ) includes a steam injector 244 in fluid communication with the steam path 242 for supplying steam 69 to the steam path 242. For example, the steam system 90 is connected to the steam path 242 by one or more steam lines 92 ( Figure 1 ) supplies steam 69 to the steam injector 244, and the steam 69 fills the steam path 242 within the wall of the TVC 230. In this manner, the steam 69 cools the wall of the TVC 230. The steam injector 244 is disposed through the third wall 236 and is positioned in general axial alignment with the second wall 234. However, the steam injector 244 may be positioned anywhere along the wall of the TVC 230.

[0052] The TVC 230 includes one or more TVC air holes 246 defined through the first wall 232. The one or more TVC air holes 246 are operable to direct the compressed air 65 through the first wall 232 into the TVC 230 and generate a first vortex 247. The size of each of the one or more TVC air holes 246, the number of the one or more TVC air holes 246, and the circumferential spacing between corresponding TVC air holes in the one or more TVC air holes 246 are based on the amount of swirling airflow desired to generate the first vortex 247 within the TVC 230. In addition, the one or more TVC air holes 246 are generally circular openings, but alternatively, other shapes may be implemented for the openings. For example, the one or more TVC air holes 246 may be an elliptical slot, etc.

[0053] The steam system 90 also includes one or more steam injection holes 248 and one or more steam cooling holes 250 defined through at least one of the walls of the TVC 230. For example, the one or more steam injection holes 248 are defined through the second wall 234. The one or more steam injection holes 248 provide fluid communication between the steam path 242 and the TVC 230. In this way, the steam injector 244 is in fluid communication with the TVC 230. The one or more steam injection holes 248 are operable to guide the steam 69 from the steam path 242 through the second wall 234 into the TVC 230 and generate a second vortex 249. The first vortex 247 and the second vortex 249 are counter-rotating. In some embodiments, the first vortex 247 and the second vortex 249 rotate in the same direction. The size of each of the one or more steam injection holes 248, the number of the one or more steam injection holes 248, and the circumferential spacing between the corresponding steam injection holes in the one or more steam injection holes 248 are based on the desired amount of vortex airflow desired to generate the second vortex 249 in the TVC 230. In addition, although Figure 2 In the embodiment of the present invention, one or more steam injection holes 248 are generally circular openings, but alternatively, other shapes can be implemented for the openings. For example, one or more steam injection holes 248 can be oval grooves, etc.

[0054] The TVC 230 includes one or more steam cooling holes 250 disposed through one or more of the walls of the TVC 230. The one or more steam cooling holes 250 provide fluid communication between the steam path 242 and the TVC 230, thereby cooling the walls of the TVC 230 with steam 69 (e.g., through film cooling). In particular, the one or more steam cooling holes 250 are disposed to provide fluid communication between the steam path 242 and the downstream portion 233. The one or more steam cooling holes 250 include one or more first steam cooling holes 250a disposed through the fourth wall 238 and one or more second steam cooling holes 250b disposed through the partition wall 237. The one or more first steam cooling holes 250a are operable to direct steam 69 from the steam path 242 therethrough to cool the fourth wall 238. The one or more second steam cooling holes 250b are operable to direct steam 69 from the steam path 242 therethrough to cool the partition wall 237. The combustor 200 also includes a diffuser section 260 defined between the outer combustor casing 208 and the inner combustor casing 209 and upstream of the combustion chamber 202 and the plurality of TVCs 230 (eg, upstream of the annular dome 210). The diffuser section 260 is connected to the HP compressor 24 ( Figure 1 ) is fluidly connected to receive compressed air 65 from the HP compressor 24.

[0055] In operation, the combustor 200 receives heat from the HP compressor 24 ( Figure 1 ) is discharged from the combustion chamber 202. A portion of the compressed air 65 is directed through the first mixing assembly 212. For example, the compressed air 65 is directed through the first mixing assembly swirler 216, and the first mixing assembly swirler 216 causes the compressed air 65 to swirl. At the first mixing assembly 212, the compressed air 65 is mixed with the fuel 67 from the first fuel injector 218 and discharged into the combustion chamber 202. The first fuel injector 218 injects the fuel 67 axially rearward into the first combustion zone 202a of the combustion chamber 202 to generate a first fuel flow 270. At the first mixer 214, the first fuel flow 270 is mixed with the first compressed air flow 272 to generate a first fuel-air mixture. The first fuel-air mixture is fuel-rich (e.g., a higher fuel-air ratio within the mixture). The first fuel-air mixture is ignited by an igniter (for clarity, Figure 2 ) is ignited to generate a first flame within the combustion chamber 202, the first flame combusting the first fuel-air mixture and providing combustion gases 66, which are directed downstream to the HP turbine 28 ( Figure 1 ) of the first stage turbine nozzle. The first flame burns within the first combustion zone 202a (eg, adjacent to the first mixer 214 and within the region of the annular dome 210) and generates combustion gases 66 within the combustion chamber 202.

[0056] A portion of the compressed air 65 is also injected into the TVC 230 through one or more TVC air holes 246. For example, the compressed air 65 is injected axially rearward into the upstream portion 231 through one or more TVC air holes 246. The compressed air 65 injected into the upstream portion 231 generates a first vortex 247 within the upstream portion 231. The second fuel injector 224 radially injects fuel 67 into the upstream portion 231. For example, a plurality of second mixing assemblies 220 are arranged through the third wall 236 so that the second fuel injectors 224 radially inject fuel 67 into the upstream portion 231. In the upstream portion 231, the fuel 67 includes a second fuel flow 274, which is mixed with a second compressed air flow 276 to generate a second fuel-air mixture. The second fuel-air mixture is leaner in fuel than the first fuel-air mixture (e.g., a lower fuel-air ratio in the mixture). The second fuel-air mixture is ignited by an igniter (for clarity, Figure 2The first vortex 247 is ignited in the upstream portion 231 (not shown) to generate a second flame in the upstream portion 231 (e.g., in the second combustion zone 202b), the second flame combusting the second fuel-air mixture and providing the combustion gas 66, which is directed downstream to the downstream portion 233. The first vortex 247 traps the second flame in the upstream portion 231, so that the fuel-air mixture is completely combusted in the upstream portion 232 and the combustion gas 66 is produced in the upstream portion 231. In this way, the upstream portion 231 is a primary TVC that traps the second flame via the first vortex 247.

[0057] The TVC 230 is operable to direct the combustion gases 66 from the upstream portion 231 through the gap 239 and into the downstream portion 233, where the combustion gases 66 are mixed with steam 69. For example, one or more steam injection holes 248 are operable to direct the steam 69 from the steam path 242 and into the downstream portion 233, thereby generating a steam injection flow 280 and generating a second vortex 249 within the downstream portion 233. In this manner, the steam injection flow 280 is downstream of the second fuel-air mixture. The one or more steam injection holes 248 are operable to direct the steam 69 axially forward into the downstream portion 233. The second vortex 249 is operable to mix the combustion gases 66 from the upstream portion 231 with the steam injection flow 280 to generate a first steam-combustion gas mixture 290. The downstream portion 233 is operable to direct the first steam-combustion gas mixture 290 through the TVC opening 240 and into the combustion chamber 202 downstream of the first combustion zone 202a. The combustion gases 66 from the first combustion zone 202a are mixed within the combustor 202 with the first steam-combustion gas mixture 290 from the TVC 230 to generate a second steam-combustion gas mixture 292. The combustor 202 is then operable to direct the second steam-combustion gas mixture 292 to exit the combustor 202 through the combustor outlet 211, and the second steam-combustion gas mixture 292 is directed downstream to the HP turbine 28 ( Figure 1 )'s first stage turbine nozzle.

[0058] The combustor 200 is an axially staged combustor. In particular, the plurality of second mixing assemblies 220 provide axial fuel staging in the second combustion zone 202b. For example, the TVC 230 is operable to direct the combustion gases 66 from the TVC 230 into the combustion chamber 202 axially downstream of the first combustion zone 202a. This configuration of the combustor 200 provides rich combustion provided by the plurality of first mixing assemblies 212 (e.g., by the first mixer 214) and lean combustion provided by the plurality of second mixing assemblies 220 to reduce NOx as compared to a combustor without the benefit of the present disclosure. x emission.

[0059] Steam system 90( Figure 1 ) can be in the turbine engine 10 ( Figure 1 ) during various operating conditions of a mission cycle. Mission cycles include, for example, low power operation, medium power operation, and high power operation. Low power operation includes, for example, engine start, idle, taxi, and approach. Medium power operation includes, for example, cruising. High power operation includes, for example, takeoff and climb. During engine start conditions or idle conditions, steam injector 244 does not inject steam 69 into TVC 230. During operating conditions above idle conditions (e.g., taxi and approach), during medium power conditions, and during high power conditions, steam injector 244 is operable to inject steam 69. During high power conditions, steam injector 244 is operable to inject a greater amount of steam 69 than during medium power conditions.

[0060] The TVC 230 provides flame stability, and the steam 69 in the TVC 230 reduces the temperature of the combustion gases 66 in the TVC 230. In this way, the second flame operates at a higher temperature, and the steam 69 reduces the temperature of the second flame. The second vortex 249 provides residence time for the steam injection flow 280 to mix with the combustion gases 66 in the TVC 230. The TVC 230 enables a water-air ratio (WAR) of the steam 69 to the compressed air 65 in the combustion chamber 202 up to sixty percent (60%). For example, the WAR is 0.0% to 60%, and preferably 5% to 60%. In some embodiments, based on the operating conditions of the turbine engine (e.g., startup, idle, taxi, takeoff, climb, cruise, descent) or the operating conditions of the combustor 200, the WAR is zero to sixty percent (0.0% to 60%). For example, the WAR in the combustor 200 is zero to thirty percent (0% to 30%) during low power conditions, one to forty percent (1% to 40%) during medium power conditions, and two to sixty percent (2% to 60%) during high power conditions. Figure 1 ), steam 69 is injected into the combustor 200 during any operating condition above idle conditions. Thus, the steam 69 injected into the TVC 230 enables reduced emissions (NOx emissions, nvPM emissions, CO emissions, noise) and reduced specific fuel capacity (SFC) while avoiding flameout of the first flame within the first combustion zone 202a compared to a turbine engine without the benefit of the present disclosure.

[0061] Figure 3 FIG. 3 is a schematic cross-sectional view of a combustor 300 of a turbine engine according to another embodiment, taken along a longitudinal centerline axis of the turbine engine. Figure 2The same reference numerals will be used for the components of the burner 300 that are the same as or similar to the components of the burner 200 described above. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 300 includes the same Figure 2 The TVC 230 is different from the TVC 330.

[0062] The TVC 330 is defined by one or more walls (collectively referred to as the walls of the TVC 330). For example, the TVC 330 is defined by a first wall 332, a second wall 334, a third wall 336, and a fourth wall 338. The TVC 330 does not include a dividing wall, but includes an upstream portion 331 and a downstream portion 333 downstream of the upstream portion 331. The TVC 330 defines a second combustion zone 302b within the upstream portion 331 of the TVC 330. The size of the upstream portion 331 is designed to contain the second combustion zone 302b, so that a vortex 347 of the compressed air 65 is formed within the upstream portion 331, and combustion occurs in the upstream portion 331, as described in further detail below. The size of the downstream portion 333 is designed to receive the steam 69. For example, the upstream portion 331 is defined axially rearward from the first wall 332 to approximately 50% of the total axial length of the TVC 330. The third wall 336 extends axially from the first wall 332 to the second wall 334. The third wall 336 is angled radially inward at the downstream portion 333 of the TVC 330 such that the volume of the downstream portion 333 is less than the volume of the upstream portion 331. In this manner, the radial height of the downstream portion 333 of the TVC 330 decreases from the front end to the rear end of the downstream portion 333. The first wall 332 extends from the fourth wall 338 to the third wall 336 and is angled with the fourth wall 338 such that the angle between the first wall 332 and the fourth wall 338 is greater than ninety degrees (90°). In some embodiments, the angle between the first wall 332 and the fourth wall 338 is ninety degrees (90°) or less than ninety degrees (90°). The fourth wall 338 extends axially from the first wall 332 to the TVC opening 340 defined between the fourth wall 338 and the outer liner 204.

[0063] At least one of the walls defining the TVC 330 includes a steam path 342 defined therein. For example, the first wall 332, the second wall 334, the third wall 336, and the fourth wall 338 each include a portion of the steam path 342, such that the steam path 342 is disposed within the first wall 332, the second wall 334, the third wall 336, and the fourth wall 338. The steam system (e.g., Figure 1 The steam system 90 includes a steam injector 344 in fluid communication with the steam path 342 for supplying steam 69 to the steam path 342, as described above with respect to Figure 2 Describe in detail.

[0064] The TVC 330 includes one or more TVC air holes 346 defined through the first wall 332. The one or more TVC air holes 346 are operable to direct the compressed air 65 through the first wall 332 into the TVC 330 and generate a vortex 347. The TVC 330 also includes one or more steam injection holes 348 and one or more steam cooling holes 350 defined through the third wall 336. The one or more steam injection holes 348 provide fluid communication between the steam path 342 and the TVC 330. The one or more steam injection holes 348 are positioned through the third wall 336 at the downstream portion 333 of the TVC 330, and are positioned radially outward and generally axially aligned with the TVC opening 340. The one or more steam injection holes 348 are operable to direct steam 69 from the steam path 342 through the third wall 336 into the TVC 330. For example, the one or more steam injection holes 348 are operable to direct steam 69 generally radially into the downstream portion 333 of the TVC 330.

[0065] The TVC 330 includes one or more steam cooling holes 350 disposed through one or more of the walls of the TVC 330. For example, the one or more steam cooling holes 350 are disposed through the fourth wall 338 at the downstream portion 333 of the TVC 330. The one or more steam cooling holes 350 are operable to direct the steam 69 from the steam path 342 therethrough to cool the fourth wall 338.

[0066] TVC 330 and Figure 2 The TVC 230 of FIG. 24 operates substantially similarly. A second compressed air stream 376 is injected into the upstream portion 331 of the TVC 330 through one or more TVC air holes 346. The one or more TVC air holes 346 are angled due to the angled first wall 332, so that the one or more TVC air holes 346 are operably directed to guide the second compressed air stream 376 at an angle greater than zero degrees (0°) and less than ninety degrees (90°) relative to the axial direction A. In some embodiments, the TVC air holes 246 are angled to guide the second compressed air stream 376 at an angle equal to or greater than ninety degrees (90°) relative to the axial direction A. The second compressed air stream 376 is mixed with the second fuel stream 274 to generate a second fuel-air mixture, and the second fuel-air mixture is ignited to generate a second flame, as described above with respect to Figure 2Detailed description. The second flame burns in the upstream portion 331 of the TVC 330 (e.g., in the second combustion zone 302b) to generate combustion gases 66. The TVC 330 is operable to direct the combustion gases 66 from the upstream portion 331 of the TVC 330 to the downstream portion 333. At the downstream portion 333, one or more steam injection holes 348 are operable to direct steam 69 therethrough to generate a steam injection flow 380. The steam injection flow 380 mixes with the combustion gases 66 in the downstream portion 333 to generate a first steam-combustion gas mixture 390. The TVC 330 is operable to direct the first steam-combustion gas mixture 390 through the TVC opening 340 and into the combustion chamber 202 downstream of the first combustion zone 202a. The combustion gases 66 from the first combustion zone 202a are mixed with the first steam-combustion gas mixture 390 in the combustion chamber 202 to generate a second steam-combustion gas mixture 392. The second steam-combustion gas mixture 392 is then directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0067] Figure 4 FIG. 4 is a schematic cross-sectional view of a combustor 400 of a turbine engine according to another embodiment, taken along the longitudinal centerline axis of the turbine engine. Figure 2 and Figure 3 The same reference numerals will be used for the components of the burner 400 that are the same as or similar to the components of the above-mentioned burners 200 and 300. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 400 includes components that are different from Figure 2 and Figure 3 The plurality of second mixing components 220 and TVC 330 and the plurality of second mixing components 420 and TVC 430.

[0068] Each of the plurality of second mixing assemblies 420 includes a second mixer 422 and a second fuel injector 424. The TVC 430 is defined by one or more walls (collectively referred to as walls of the TVC 430). For example, the TVC 430 is defined by a first wall 432, a second wall 434, a third wall 436, and a fourth wall 438. The walls of the TVC 430 are connected to the Figure 3 The walls of TVC 330 are substantially similar, and TVC 430 similarly includes a second combustion zone 402b, an upstream portion 431, a downstream portion 433, and a TVC opening 440. A vortex 447 is formed in the upstream portion 431, similar to Figure 3 The vortex 347. The burner 400 and Figure 3The combustor 300 of 430 operates substantially similarly. A plurality of second mixing assemblies 420 are disposed through the first wall 432 such that the second fuel injectors 424 inject the fuel 67 axially forward into the upstream portion 431 of the TVC 430 .

[0069] Figure 5 FIG. 5 is a schematic cross-sectional view of a combustor 500 of a turbine engine according to another embodiment, taken along the longitudinal centerline axis of the turbine engine. Figure 2 and Figure 3 The same reference numerals will be used for the components of the burner 500 that are the same as or similar to the components of the above-mentioned burners 200 and 300. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 500 includes components that are different from Figure 3 TVC 330 and steam injector 344 and TVC 530 and steam injector 544 .

[0070] TVC 530 is defined by one or more walls (collectively referred to as walls of TVC 530). For example, TVC 530 is defined by a first wall 532, a second wall 534, a third wall 536, and a fourth wall 538. Figure 3 The walls of TVC 330 are substantially similar, and TVC 530 similarly includes a second combustion zone 502b, an upstream portion 531, a downstream portion 533, and a TVC opening 540. The upstream portion 531 is sized to contain the second combustion zone 502b so that a vortex 547 of the compressed air 65 is formed within the upstream portion 531 and combustion occurs within the upstream portion 531. The downstream portion 533 is sized to receive steam 69. For example, the upstream portion 531 is defined axially rearward from the first wall 532 to approximately 75% of the total axial length of the TVC 530. The third wall 536 extends substantially axially from the first wall 532 to the second wall 534 and is not radially inwardly angled at the downstream portion 533 of the TVC 530. In this manner, the radial height of the downstream portion 533 remains constant and does not decrease from the front end to the rear end of the downstream portion 533. At least one of the walls defining the TVC 530 also includes a steam path 542 defined therein for receiving steam 69. The steam path 542 extends through the first wall 532, the third wall 536, and the fourth wall 538. However, the steam path 542 does not extend through the second wall 534. In some embodiments, the steam path 542 may extend through the second wall 534, similar to Figures 2 to 4 Embodiment of the invention.

[0071] The steam injector 544 is disposed through the third wall 536 and is connected to the steam line ( Figure 5 ) provides a steam system (e.g., Figure 1 The steam system 90 of the TVC 530 is fluidly connected to the steam path 542. The steam injector 544 includes one or more steam injection holes 548 disposed through the steam injector 544. The one or more steam injection holes 548 include one or more first steam injection holes 548a and one or more second steam injection holes 548b. The one or more first steam injection holes 548a are positioned to operably guide the steam 69 into the downstream portion 533 of the TVC 530. The one or more second steam injection holes 548b are positioned on the steam injector 544 to inject the steam 69 outside the TVC 530 and outside the combustion chamber 202.

[0072] The steam injector 544 also includes a steam swirler 552 for swirling the steam 69 therethrough to generate a steam swirling flow 549. In operation, the steam injector 544 is operable to direct the steam 69 through one or more first steam injection holes 548a and into the downstream portion 533 of the TVC 530 to generate a first steam injection flow 580. The steam swirler 552 swirls the first steam injection flow 580 to generate a steam swirling flow 549. The steam swirling flow 549 promotes mixing of the combustion gases 66 from the upstream portion 531 (e.g., the second combustion zone 502b) of the TVC 530 with the first steam injection flow 580 in the downstream portion 533 of the TVC 530. The combustion gases 66 from the upstream portion 531 mix with the first steam injection flow 580 to generate a first steam-combustion gas mixture 590 within the downstream portion 533. The TVC 530 is operable to direct a first steam-combustion gas mixture 590 through the TVC opening 540 and into the combustion chamber 202. The first steam-combustion gas mixture 590 is mixed with the combustion gases 66 from the first combustion zone 202a within the combustion chamber 202 to generate a second steam-combustion gas mixture 592, which is then directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0073] The steam injector 544 is also operable to direct the steam 69 through one or more second steam injection holes 548b to generate a second steam injection flow 582 outside the TVC 530 and outside the combustion chamber 202. The combustor 500 is operable to direct the second steam injection flow 582 to at least one of the outer liner 204, the inner liner 206, or the annular dome 210 to cool the outer liner 204, the inner liner 206, or the annular dome 210, respectively. In some embodiments, the combustor 500 is operable to direct the second steam injection flow 582 to the high pressure turbine (e.g., Figure 1 The high-pressure turbine 28) is provided with cooling for the high-pressure turbine.

[0074] Figure 6FIG. 6 is a schematic cross-sectional view of a combustor 600 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Figure 2 , Figure 3 and Figure 5 The same reference numerals will be used for the components of the burner 600 that are the same as or similar to the components of the above-mentioned burners 200, 300, 500. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 500 includes components that are different from Figure 2 , Figure 3 and Figure 5 The plurality of second mixing components 220 and TVCs 230, 330, 530 and the plurality of second mixing components 620 and TVCs 630.

[0075] Each of the plurality of second mixing assemblies 620 includes a second mixer 622 and a second fuel injector 624. The TVC 630 is defined by one or more walls (collectively referred to as walls of the TVC 630). For example, the TVC 630 is defined by a first wall 632, a second wall 634, a third wall 636, and a fourth wall 638. The walls of the TVC 630 are connected to the Figure 5 The walls of TVC 530 are substantially similar, and TVC 630 similarly includes a second combustion zone 602b, an upstream portion 631, a downstream portion 633, and a TVC opening 640. Figure 5 The combustor 500 of is operated substantially similarly. However, a plurality of second mixing assemblies 620 are disposed through the first wall 632 so that the second fuel injectors 624 inject the fuel 67 axially forward into the upstream portion 631 of the TVC 630 to generate the second fuel flow 274 that mixes with the second compressed air flow 376 at the vortex 647 .

[0076] Figure 7 FIG. 7 is a schematic cross-sectional view of a combustor 700 of a turbine engine according to another embodiment, taken along a longitudinal centerline axis of the turbine engine. Figure 2 , Figure 3 and Figure 5 The same reference numerals will be used for the components of the burner 700 that are the same as or similar to the components of the above-mentioned burners 200, 300, 500. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 700 includes components that are different from Figure 2 , Figure 3 and Figure 5 TVC 230 , 330 , 530 and steam injectors 244 , 344 , 544 and TVC 730 and steam injector 744 .

[0077] The TVC 730 is defined by one or more walls (collectively referred to as walls of the TVC 730). For example, the TVC 730 is defined by a first wall 732, a second wall 734, a third wall 736, and a fourth wall 738. Figure 5 The walls of TVC 530 are substantially similar, and TVC 730 similarly includes a second combustion zone 702b, an upstream portion 731, a downstream portion 733, and a TVC opening 740. A vortex 747 is formed in the upstream portion 731 to mix the second compressed air flow 376 and the second fuel flow 274. At least one of the walls defining TVC 730 also includes a steam path 742 defined therein for receiving steam 69. The steam path 742 extends through the first wall 732, the third wall 736, and the fourth wall 738. However, the steam path 742 does not extend through the second wall 734. The steam path 742 extends only a portion of the third wall 736, so that the steam path 742 does not extend the entire length of the third wall 736. However, the steam path 742 can extend the entire length of the third wall 736, or can also extend through the second wall 734.

[0078] Steam systems (e.g. Figure 1 The steam system 90 of the TVC 730 includes a steam injector 744 and one or more steam injection holes 748 disposed in at least one of the walls of the TVC 730. The one or more steam injection holes 748 include one or more first steam injection holes 748a and one or more second steam injection holes 748b. The one or more first steam injection holes 748a are disposed through the steam injector 744 and positioned on the steam injector 744 to inject steam 69 outside the TVC 730 and outside the combustion chamber 202. The one or more second steam injection holes 748b are disposed through the third wall 736 and positioned on the third wall 736 to operably direct the first steam injection flow 779 into the downstream portion 733 of the TVC 730 (e.g., downstream of the second combustion zone 702b).

[0079] In operation, the steam injector 744 is operable to direct steam 69 through one or more first steam injection holes 748a and outside the TVC 730 and outside the combustion chamber 202 to generate a first steam injection flow 779. The first steam injection flow 779 is mixed with the compressed air 65. The burner 700 is operable to direct a portion of the first steam injection flow 779 and a portion of the compressed air 65 through one or more second steam injection holes 748b and into the downstream portion 733 of the TVC 730 to generate a second steam injection flow 780. The compressed air 65 in the second steam injection flow 780 helps to burn any unburned fuel from the first combustion zone 202a and from the second combustion zone 202b. The combustion gases 66 from the upstream portion 731 are mixed with the second steam injection flow 780 to generate a first steam-combustion gas mixture 790. The TVC 730 is operable to direct the first steam-combustion gas mixture 790 through the TVC opening 740 and into the combustion chamber 202. The first steam-combustion gas mixture 790 is mixed with the combustion gases 66 from the first combustion zone 202a within the combustion chamber 202 to generate a second steam-combustion gas mixture 792 which is then directed downstream to the HP turbine (e.g., Figure 1 The combustor 700 is also operable to direct a portion of the first steam injection flow 779 to at least one of the outer liner 204, the inner liner 206, or the annular dome 210 to cool the outer liner 204, the inner liner 206, or the annular dome 210, respectively.

[0080] Figure 8 FIG. 8 is a schematic cross-sectional view of a combustor 800 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Figure 2 , Figure 3 and Figure 7 The same reference numerals will be used for the components of the burner 800 that are the same as or similar to the components of the above-mentioned burners 200, 300, 700. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 800 includes components that are different from Figure 2 , Figure 3 and Figure 7 The plurality of second mixing components 220 and TVC 230, 330, 730 and the plurality of second mixing components 820 and TVC 830.

[0081] Each of the plurality of second mixing assemblies 820 includes a second mixer 822 and a second fuel injector 824. The TVC 830 is defined by one or more walls (collectively referred to as walls of the TVC 830). For example, the TVC 830 is defined by a first wall 832, a second wall 834, a third wall 836, and a fourth wall 838. The walls of the TVC 830 are connected to the Figure 7 The walls of TVC 730 are substantially similar, and TVC 830 similarly includes combustion zone 802b, upstream portion 831, downstream portion 833, and TVC opening 840. Figure 7 The combustor 700 of is operated substantially similarly. However, a plurality of second mixing assemblies 820 are disposed through the first wall 832 so that the second fuel injectors 824 inject the fuel 67 axially forward into the upstream portion 831 of the TVC 830 to generate the second fuel flow 274 that mixes with the second compressed air flow 376 at the vortex 847 .

[0082] exist Figure 8 In the embodiment of the present invention, the one or more second steam injection holes 748b further include a steam injection hole extension 851 disposed about the one or more second steam injection holes 748b. The steam injection hole extension 851 extends generally radially from the third wall 836. For example, the steam injection hole extension 851 extends radially outward from the third wall 836. In this manner, the steam injection hole extension 851 is disposed outside the TVC 830. In operation, the steam injection hole extension 851 is operable to direct the first steam injection flow 779 into the one or more second steam injection holes 748b and subsequently into the TVC 830. In this manner, the steam injection hole extension 851 helps direct the first steam injection flow 779 into the one or more second steam injection holes 748b and helps the first steam injection flow 779 penetrate into the combustion gases 66 within the TVC 830.

[0083] Fig. 9 FIG. 9 is a schematic cross-sectional view of a combustor 900 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Figure 2 The same reference numerals will be used for the components of the burner 900 that are the same as or similar to the components of the burner 200 described above. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 900 includes components that are different from Figure 2The plurality of first mixing assemblies 212, the plurality of second mixing assemblies 220, the plurality of first mixing assemblies 912, the plurality of second mixing assemblies 920, the plurality of trapped vortex chambers (TVCs) 930, and the plurality of steam injectors 944 of the plurality of first mixing assemblies 212, the plurality of second mixing assemblies 220, the TVCs 230, and the plurality of steam injectors 944. The plurality of TVCs 930 include a first TVC 930a extending from the outer liner 204 and a second TVC 930b extending from the inner liner 206.

[0084] Each of the plurality of first mixing assemblies 912 includes a first mixer 914 and a first mixing assembly swirler 916. The plurality of first fuel injectors 918 ( Fig. 9 A plurality of first fuel injectors 918 are coupled to a fuel injector line 919 that is coupled to a fuel system (e.g., Figure 1 The fuel system 80) is flow-connected for supplying fuel 67 to multiple first fuel injectors 918.

[0085] Each of the plurality of second mixing assemblies 920 includes a second mixer 922. The plurality of second fuel injectors 924 ( Fig. 9 The plurality of second mixing assemblies 920 are connected in fluid communication with each corresponding second mixing assembly 920 (only one is shown in FIG. 1 ). The plurality of second mixing assemblies 920 are in fluid communication with the fuel injector line 919. The plurality of second mixing assemblies 920 include a first plurality of second mixing assemblies 920a in fluid communication with the first TVC 930a and a second plurality of second mixing assemblies 920b in fluid communication with the second TVC 930b. In this manner, the first plurality of second mixing assemblies 920a provide compressed air 65 and fuel 67 to the first TVC 930a, and the second plurality of second mixing assemblies 920b provide compressed air 65 and fuel 67 to the second TVC 930b, as further described below.

[0086] Each of the plurality of TVCs 930 is defined by one or more walls (collectively referred to as walls of each TVC 930). For example, each TVC 930 is defined by a first wall 932, a second wall 934, a third wall 936, a fourth wall 938, and a partition wall 937. In this manner, each of the plurality of TVCs 930 is connected to a plurality of TVCs 930. Figure 2 The TVC 230 of the plurality of TVCs 930 is substantially similar. Each of the plurality of TVCs 930 further includes a second combustion zone 902b, an upstream portion 931, a downstream portion 933 downstream of the upstream portion 931, and a TVC opening 940. The partition wall 937 is spaced apart from the fourth wall 938 to define a radial gap 939 therebetween. At least one of the walls defining each of the plurality of TVCs 930 includes a steam path 942 defined therein.

[0087] Steam systems (e.g. Figure 1 The steam system 90 of the embodiment of the present invention includes a plurality of steam injectors 944 and one or more steam injection holes 948. The plurality of steam injectors 944 include a first steam injector 944a disposed through the third wall 936 of the first TVC 930a and a second steam injector 944b disposed through the third wall 936 of the second TVC 930b. One or more steam injection holes 948 are disposed through the second wall 934 of each corresponding TVC 930 for injecting steam 69 from the steam path 942 into each corresponding TVC 930.

[0088] Each of the plurality of TVCs 930 includes one or more TVC air holes 946 defined through the third wall 936. The one or more TVC air holes 946 are operable to radially direct the compressed air 65 through the third wall 936 into each of the plurality of TVCs 930 to generate a first vortex 947 within the upstream portion 931. A plurality of second fuel injectors 924 are disposed through the first wall 932 to inject the fuel 67 axially through the first wall 932.

[0089] Burner 900 with Figure 2 The combustor 200 of the embodiment of the present invention operates substantially similarly. A plurality of second fuel injectors 924 inject fuel 67 into the upstream portion 931 to generate a second fuel flow 974. One or more TVC air holes 946 are operable to direct a second compressed air flow 976 therethrough into the upstream portion 931 of the TVC 930. The fuel 67 is mixed with the second compressed air flow 976 through the first vortex 947 to generate a fuel-air mixture, which is ignited to generate combustion gases 66. The combustion gases 66 pass from the upstream portion 931 through the radial gap 939 and enter the downstream portion 933. A plurality of steam injectors 944 are operable to inject steam 69 through one or more steam injection holes 948 and into the corresponding TVC 930 to generate a steam injection flow 980, which generates a second vortex 949. The combustion gases 66 are mixed with the steam injection flow 980 through the second vortex 949 within the downstream portion 933 to generate a first steam-combustion gas mixture 990. The first steam-combustion gas mixture 990 is directed through the TVC opening 940 and into the combustion chamber 202 downstream of the first combustion zone 202a. In the combustion chamber 202, the first steam-combustion gas mixture 990 is mixed with the combustion gases 66 from the first combustion zone 202a to generate a second steam-combustion gas mixture 992. The second steam-combustion gas mixture 992 is then directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0090] Fig.10FIG. 1 is a schematic cross-sectional view of a combustor 1000 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. The combustor 1000 may be Figure 1 The combustor 1000 is used in the combustion section 26 of the turbine engine 10. However, the combustor 1000 is a radial combustor in which the first fuel-air mixture is radially injected, as described in further detail below.

[0091] The combustor 1000 includes a combustion chamber 1002 defined by an outer liner 1004 and an inner liner 1006. The outer liner 1004 and the inner liner 1006 surround the turbine engine 10 ( Figure 1 ) is annular about the longitudinal centerline axis 12 of the combustion chamber 1002. The outer liner 204 defines the radial outer boundary of the combustion chamber 1002, and the inner liner 1006 defines the radial inner boundary of the combustion chamber 202. The outer liner 1004 and the inner liner 1006 are radially spaced inward from the outer combustor casing 1008 and the inner combustor casing 1009, respectively, and the outer combustor casing 1008 and the inner combustor casing 1009 extend circumferentially around the outer liner 1004 and the inner liner 1006. The outer liner 1004 and the inner liner 1006 include one or more liner air holes 1005, and the one or more liner air holes 1005 are operable to guide the compressed air 65 through the outer liner 1004 and the inner liner 1006 and into the combustion chamber 1002 to cool the outer liner 1004 and the inner liner 1006 (for example, through film cooling). Combustor 1000 also includes an annular dome 1010 upstream of and coupled to outer liner 1004 and inner liner 1006. Annular dome 1010 defines an upstream end of combustion chamber 1002.

[0092] The combustion chamber 1002 extends from the annular dome 1010 to the combustion chamber outlet 1011. In particular, the annular dome 1010 extends axially, and the outer liner 204 and the inner liner 206 extend radially inward from the annular dome 1010 and define a first combustion zone 1002a therebetween. The outer liner 1004 and the inner liner 1006 are bent downstream of the first combustion zone 1002a, and then extend axially to the combustion chamber outlet 1011.

[0093] A plurality of first mixing components 1012 ( Fig.10 The plurality of first mixing assemblies 1012 are circumferentially spaced about the annular dome 1010 to deliver a first mixture of fuel and air to the combustion chamber 1002. For example, each of the plurality of first mixing assemblies 1012 delivers a first mixture of fuel and air to a first combustion zone 1002a of the combustion chamber 1002, as described in further detail below. Each first mixing assembly 1012 includes a first mixer 1014 and a first mixing assembly swirler 1016. A plurality of first fuel injectors 1018 ( Fig.10A plurality of first fuel injectors 1018 are circumferentially spaced about the annular dome 1010 and extend radially from the outer combustor casing 1008 to the plurality of first mixing assemblies 1012.

[0094] Multiple second mixing components 1020 ( Fig.10 The plurality of second mixing assemblies 1020 are circumferentially spaced about the outer liner 1004 to deliver a second mixture of fuel and air to the second combustion zone 1002b, as described in further detail below. The second combustion zone 1002b is configured to inject combustion gases 66 from the second combustion zone 1002b axially rearward of the first combustion zone 1002a, as described in further detail below. Each of the plurality of second mixing assemblies 1020 includes a second mixer 1022. The plurality of second fuel injectors 1024 ( Fig.10 The plurality of second fuel injectors 1024 are circumferentially spaced about the outer liner 1004 and extend radially from the outer combustor casing 1008 to the plurality of second mixing assemblies 1020. The plurality of second mixing assemblies 1020 include a first plurality of second mixing assemblies 1020a and a second plurality of second mixing assemblies 1020b.

[0095] The combustor 1000 includes a plurality of trapped vortex cavities (TVCs) 1030 formed in the outer liner 1004 and the inner liner 1006, defining the second combustion zone 202b. For example, the plurality of TVCs 1030 include a first TVC 1030a extending from the inner liner 1006 and a second TVC 1030b extending from the outer liner 1004. Each of the plurality of TVCs 1030 is defined by a first wall 1032, a second wall 1034, a third wall 1036, a fourth wall 1038, and a partition wall 1037 (collectively referred to as walls of the plurality of TVCs 1030). The first wall 1032 and the second wall 1034 extend generally axially, and the third wall 1036 and the fourth wall 1038 extend generally radially. The first wall 1032 defines a first axial wall of each of the plurality of TVCs 1030, the second wall 1034 defines a second axial wall of each of the plurality of TVCs 1030, the third wall 1036 defines a first radial wall of each of the plurality of TVCs 1030, and the fourth wall 1038 defines a second radial wall of each of the plurality of TVCs 1030. The second wall 1034 is radially inwardly spaced from the first wall 1032. The first wall 1032 extends generally axially from a radially outer end of the third wall 1036 to a radially outer end of the fourth wall 1038. The second wall 1034 extends generally axially from the outer liner 1004 or the inner liner 1006 to a radially inner end of the third wall 1036. The third wall 1036 extends generally radially from the first wall 1032 to the second wall 1034. The fourth wall 1038 is axially spaced apart from the third wall 1036 and extends generally radially from the first wall 1032 to a TVC opening 1040 defined between a radially inner end of the fourth wall 1038 and a radially outer surface of either the outer liner 1004 or the inner liner 1006 .

[0096] Each of the plurality of TVCs 1030 is defined between a first wall 1032, a second wall 1034, a third wall 1036, and a fourth wall 1038. In this manner, the plurality of TVCs 1030 are axially located on either axial side of the first combustion zone 1002a of the combustion chamber 1002. The TVC openings 1040 are openings in the outer liner 1004 or the inner liner 1006 to provide flow communication from the plurality of TVCs 1030 to the combustion chamber 1002. Although Fig.10 The plurality of TVCs 1030 shown in 1030 each include a substantially rectangular cross-section, but the plurality of TVCs 1030 may include any shape.

[0097] The partition wall 1037 extends axially from the third wall 1036 into the corresponding TVC 1030. The partition wall 1037 radially divides each of the plurality of TVCs 1030 into an upstream portion 1031 and a downstream portion 1033 downstream of the upstream portion 1031. In this manner, the downstream portion 1033 is radially inside the upstream portion 1031. The partition wall 1037 only partially extends into each of the plurality of TVCs 1030 such that a gap 1041 is axially defined between the partition wall 1037 and the fourth wall 1038. In some embodiments, the partition wall 1037 extends axially from the fourth wall 1038 into each corresponding TVC 1030 to axially divide each corresponding TVC 1030 into the upstream portion 1031 and the downstream portion 1033. In such embodiments, an axial gap 1039 is defined between the partition wall 1037 and the third wall 1036. The upstream portion 1031 defines the second combustion zone 1002b, and the TVC opening 1040 is defined at the downstream portion 1033. Fig.10 In the embodiment of the present invention, the upstream portion 1031 is a primary TVC and the downstream portion is a secondary TVC, as described in further detail below. The volume of the upstream portion 1031 is greater than the volume of the downstream portion 1033. In some embodiments, the volume of the upstream portion 1031 is substantially equal to or less than the volume of the downstream portion 1033.

[0098] The fourth wall 1038 is axially spaced from the outer liner 1004 or the inner liner 1006 such that a gap 1041 is defined between the fourth wall 1036 and the outer liner 1004 or the inner liner 1006. The fourth wall 1038 is coupled to the outer liner 1004 or the inner liner 1006 by a liner extension 1043 extending from the outer liner 1004 or the inner liner 1006 to a radially inner end of the fourth wall 1038. The liner extension 1043 connects the fourth wall 1038 and the outer liner 1004 or the inner liner 1006. The liner extension 1043 includes one or more liner extension holes 1007 extending generally radially through the liner extension 1043. The one or more liner extension holes 1007 are operable to direct the compressed air 65 through the liner extension 1043 and into the combustion chamber 1002 to cool the liner extension 1043.

[0099] At least one of the walls defining each of the plurality of TVCs 1030 includes a steam path 1042 defined therein. For example, the first wall 1032, the second wall 1034, the third wall 1036, the fourth wall 1038, and the partition wall 1037 each include a portion of the steam path 1042, such that the steam path 1042 is disposed within the first wall 1032, the second wall 1034, the third wall 1036, and the fourth wall 1038. The steam system (e.g., Figure 1The steam system 90 of the embodiment of the present invention includes a steam injector 1044 in fluid communication with the steam path 1042 of each TVC 1030 for supplying steam 69 to the steam path 1042. In this manner, the steam 69 cools the wall of each of the plurality of TVCs 1030. The steam injector 1044 is disposed through the third wall 1036 and is positioned in general radial alignment with the second wall 1034. However, the steam injector 1044 can be positioned anywhere along the wall of each respective TVC 1030.

[0100] Each TVC 1030 includes one or more TVC air holes 1046 defined through the first wall 1032. The one or more TVC air holes 1046 are operable to direct the compressed air 65 through the first wall 1032 into each TVC 1030 and generate a first vortex 1047. The steam system also includes one or more steam injection holes 1048 and one or more steam cooling holes 1050 defined through the second wall 1034. The one or more steam injection holes 1048 are operable to direct steam 69 from the steam path 1042 through the second wall 1034 into each TVC 1030 to generate a second vortex 1049.

[0101] Each TVC 1030 includes one or more steam cooling holes 1050 disposed through at least one of the walls of each TVC 1030. The one or more steam cooling holes 1050 provide fluid communication between the steam path 1042 and each TVC 1030, thereby cooling the walls of each TVC 1030 with steam 69 (e.g., through film cooling). In particular, the one or more steam cooling holes 1050 are disposed to provide fluid communication between the steam path 1042 and the downstream portion 1033. The one or more steam cooling holes 1050 include one or more first steam cooling holes 1050a disposed through the fourth wall 1038 and one or more second steam cooling holes 1050b disposed through the partition wall 1037. The one or more first steam cooling holes 1050a are operable to direct steam 69 from the steam path 1042 therethrough to cool the fourth wall 1038. The one or more second steam cooling holes 1050b are operable to direct steam 69 from the steam path 1042 therethrough to cool the dividing wall 1037. The combustor 1000 also includes a diffuser section 1060 defined between the outer combustor casing 1008 and the inner combustor casing 1009 and defined upstream of the combustion chamber 1002 and the plurality of TVCs 1030 (e.g., upstream of the annular dome 1010). The diffuser section 1060 is connected to the HP compressor 24 ( Figure 1 ) is fluidly connected to receive compressed air 65 from the HP compressor 24.

[0102] In operation, the combustor 1000 receives heat from an HP compressor (e.g., Figure 1 HP compressor 24). A portion of the compressed air 65 is directed through a first mixing assembly 1012. For example, the compressed air 65 is directed through a first mixing assembly swirler 1016, and the first mixing assembly swirler 1016 causes the compressed air 65 to swirl. At the first mixing assembly 1012, the compressed air 65 is mixed with the fuel 67 from the first fuel injector 1018 and discharged into the combustion chamber 1002. The first fuel injector 1018 injects the fuel 67 radially inward into the first combustion zone 1002a of the combustion chamber 1002 to generate a first fuel stream 1070. At the first mixer 1014, the first fuel stream 1070 is mixed with the first compressed air stream 1072 to generate a first fuel-air mixture. The first fuel-air mixture is ignited by an igniter (for clarity, Fig.10 ) is ignited to generate a first flame within the combustion chamber 1002 that combusts the first fuel-air mixture and provides combustion gases 66 that are directed downstream to the HP turbine (e.g., Figure 1 The first flame burns in the first combustion zone 1002a (eg, adjacent to the first mixer 1014 and in the region of the annular dome 1010) and generates combustion gases 66 in the combustion chamber 1002.

[0103] A portion of the compressed air 65 is also injected into each TVC 1030 through one or more TVC air holes 1046. For example, the compressed air 65 is injected radially inward into the upstream portion 1031 through one or more TVC air holes 1046. The compressed air 65 injected into the upstream portion 1031 generates a first vortex 1047 within the upstream portion 1031. The second fuel injector 1024 injects the fuel 67 axially into the upstream portion 1031 (e.g., axially backward into the first TVC 1030a, and axially forward into the second TVC 1030b). For example, the plurality of second mixing assemblies 1020 are disposed through the third wall 1036 so that the second fuel injectors 1024 inject the fuel 67 axially into the upstream portion 1031. In the upstream portion 1031, the fuel 67 includes a second fuel flow 1074, which is mixed with a second compressed air flow 1076 to generate a second fuel-air mixture. The second fuel-air mixture is ignited by the igniter (for clarity, Fig.10The first vortex 1047 is used to ignite the second flame in the upstream portion 1031, which burns the second fuel-air mixture and provides the combustion gas 66, which is directed downstream to the downstream portion 1033. The second flame burns in the second combustion zone 1002b in the plurality of TVCs 1030. The first vortex 1047 traps the second flame in the upstream portion 1031, so that the fuel-air mixture is completely burned in the upstream portion 1031, and the combustion gas 66 is generated in the upstream portion 1031. In this way, the upstream portion 1031 is a primary TVC that traps the second flame via the first vortex 1047.

[0104] Each TVC 1030 is operable to direct the combustion gases 66 from the upstream portion 1031 through the axial gap 1039 and into the downstream portion 1033, where the combustion gases 66 are mixed with the steam 69. For example, one or more steam injection holes 1048 are operable to direct the steam 69 from the steam path 1042 and into the downstream portion 1033, thereby generating a steam injection flow 1080 and generating a second vortex 1049 within the downstream portion 1033. In this manner, the steam injection flow 1080 is downstream of the second fuel-air mixture. One or more steam injection holes 1048 are operable to direct the steam 69 radially outward into the downstream portion 1033. The second vortex 1049 is operable to mix the combustion gases 66 from the upstream portion 1031 with the steam injection flow 1080 to generate a first steam-combustion gas mixture 1090. The downstream portion 1033 is operable to direct the first steam-combustion gas mixture 1090 through the TVC opening 1040 and into the combustion chamber 1002 downstream of the first combustion zone 1002a. The combustion gases 66 from the first combustion zone 1002a are mixed with the first steam-combustion gas mixture 1090 from each TVC 1030 within the combustion chamber 1002 to generate a second steam-combustion gas mixture 1092. The combustion chamber 1002 is then operable to direct the second steam-combustion gas mixture 1092 to exit the combustion chamber 1002 through the combustion chamber outlet 1011, and the second steam-combustion gas mixture 1090 is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0105] Fig.11 FIG. 1 is a schematic cross-sectional view of a combustor 1100 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Figure 2The same reference numerals will be used for the components of the burner 1100 that are the same as or similar to the components of the burner 200 described above. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 1100 includes a Figure 2 The plurality of first mixing assemblies 212 and the annular dome 210 are the plurality of first mixing assemblies 1112 and the annular dome 1110 .

[0106] The plurality of first mixing assemblies 1112 include a first mixer 1114. The plurality of first fuel injectors 1118 ( Fig.11 The plurality of first fuel injectors 1118 include a first fuel injector line 1118a and a second fuel injector line 1118b. The first fuel injector line 1118a injects the fuel 67 radially outward into the combustion chamber 202, and the second fuel injector line 1118b injects the fuel 67 radially inward into the combustion chamber 202, as further described below. The first fuel injector line 1118a and the second fuel injector line 1118b are annular and include one or more fuel orifices 1119 circumferentially spaced around the first fuel injector line 1118a and the second fuel injector line 1118b, and the one or more fuel orifices 1119 inject the fuel 67 therethrough and into the combustion chamber 202.

[0107] Steam systems (e.g. Figure 1 The steam system 90 includes a plurality of steam injectors 1144. The plurality of steam injectors 1144 include a first steam injector 1144a and a second steam injector 1144b. The first steam injector 1144a is disposed within the first fuel injector 1118 and injects the steam 69 axially backward into the combustion chamber 202, as further described below.

[0108] The second steam injector 1144b and Figure 2 The steam injector 244 is substantially similar and is disposed through the third wall 236. The annular dome 1110 includes one or more dome holes 1113 extending axially therethrough.

[0109] In operation, a plurality of first fuel injectors 1118 radially inject fuel 67 into the first combustion zone 202a to generate a first fuel stream 1170. For example, a first fuel injector line 1118a radially injects fuel 67 into the first combustion zone 202a through one or more fuel orifices 1119, and a second fuel injector line 1118b radially injects fuel 67 into the first combustion zone 202a through one or more fuel orifices 1119. One or more dome holes 1113 are operable to direct compressed air 65 therethrough to generate a first compressed air stream 1172 therethrough and into the first combustion zone 202a. The first mixer 214 mixes the first fuel stream 1170 and the first compressed air stream 1172 to generate a first fuel-air mixture that is ignited within the first combustion zone 202a. The first steam injector 1144a injects steam 69 therethrough and into the first combustion zone 202a to generate a first steam injection stream 1179. The second steam injector 1144b injects steam 69 through the one or more steam injection holes 248 and into the downstream portion 233 to generate a second steam injection stream 1180. The combustion gases 66 from the first combustion zone 202a are mixed with the first steam injection stream 1179 to generate a first steam-combustion gas mixture 1189 within the first combustion zone 202a, which is directed downstream within the combustor 202.

[0110] Combustion gases 66 from upstream portion 231 of TVC 230 are mixed with second steam injection stream 1180 within downstream portion 233 to generate second steam-combustion gas mixture 1190. Second steam-combustion gas mixture 1190 is directed through TVC opening 240 and into combustor 202 downstream of first combustion zone 202a. Second steam-combustion gas mixture 1190 is mixed with first steam-combustion gas mixture 1189 to generate third steam-combustion gas mixture 1192, which is directed downstream to an HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0111] The first steam injector 1144a injects steam 69 such that the first steam injection stream 1179 includes a smaller amount of steam 69 than the second steam injection stream 1180 within the TVC 230. For example, zero to thirty percent (0% to 30%) of the steam 69 injected into the combustor 1100 is injected through the first steam injector 1144a, while seventy to one hundred percent (70% to 100%) of the steam 69 injected into the combustor 1100 is injected through the second steam injector 1144b. Under some operating conditions, the first steam injector 1144a does not inject steam 69 into the first combustion zone 202a such that no steam is injected into the first combustion zone 202a. For example, the total WAR in the combustor 1100 provided by the first steam injector 1144a and the second steam injector 1144b is zero to thirty percent (0% to 30%) during low power conditions, one to forty percent (1% to 40%) during medium power conditions, and two to sixty percent (2% to 60%) during high power conditions. Thus, the combustor 1100 provides reduced SFC while also enabling improved operability (e.g., avoiding flameout) compared to a combustor without the benefit of the present disclosure.

[0112] Fig.12 FIG. 1 is a schematic cross-sectional view of a combustor 1200 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Figure 2 However, the burner 1200 includes components which are different from Figure 2 TVC 230 and steam injector 244 TVC 1230 and steam injector 1244.

[0113] The TVC 1230 is defined by one or more walls (collectively referred to as walls of the TVC 1230). For example, the TVC 1230 is defined by a first wall 1232, a second wall 1234, a third wall 1236, and a fourth wall 1238. The TVC 1230 does not include a radial partition wall, but includes a second combustion zone 1202b, an upstream portion 1231, and a downstream portion 1233 downstream of the upstream portion 1231. The TVC 1230 also includes a TVC opening 1240 defined between the fourth wall 1238 and the outer liner 204. The outer liner 204 is bent radially outward and extends axially to define the TVC opening 1240, so that the TVC opening 1240 is formed as a nozzle that converges from the downstream portion 1233 of the TVC 1230. In Fig.12 , the second combustion zone 1202b is in the downstream portion 1233 of the TVC 1230, and steam 69 is injected into the upstream portion 1231.

[0114] At least one of the walls defining the TVC 1230 includes a steam path 1242. For example, the steam path 1242 is defined in a portion of the third wall 1236. The steam path 1242 can be defined in any wall defining the TVC 1230, similar to any of the embodiments detailed herein. In some embodiments, the compressed air 65 is directed around the walls of the TVC 1230 to cool the walls. The TVC 1230 includes one or more TVC cooling holes 1245 disposed through one or more of the walls of the TVC 1230. For example, the one or more TVC cooling holes 1245 are disposed through the first wall 1232 and the fourth wall 1238. The TVC 1230 also includes one or more TVC air holes 1246 disposed through the second wall 1234.

[0115] Steam systems (e.g. Figure 1 The steam system 90 of the TVC 1230 includes a steam injector 1244. The steam injector 1244 is disposed through the third wall 1236 and is positioned upstream of the plurality of second fuel injectors 224. In this manner, the steam injector 1244 radially injects steam 69 into the upstream portion 1231 of the TVC 1230, as further described below. The steam injector 1244 includes one or more steam injection holes 1248 disposed through the third wall 1236 to inject steam 69 into the upstream portion 1231.

[0116] Burner 1200 with Figure 2 The combustor 200 of the TVC 1230 operates substantially similarly. One or more TVC air holes 1246 direct the compressed air 65 therethrough to generate a second compressed air stream 1276 in the TVC 1230. The steam injector 1244 injects steam 69 into the upstream portion 1231 to generate a steam injection stream 1280 in the upstream portion 1231 of the TVC 1230. The steam injection stream 1280 is injected upstream of the second fuel stream 274 and upstream of the second combustion zone 202b. The TVC 1230 is operable to direct the steam injection stream 1280 downstream, and the steam injection stream 1280 is mixed with the combustion gases 66 through the vortex 1247 in the TVC 1230 to generate a first steam-combustion gas mixture 1290. The TVC 1230 is operable to direct the first steam-combustion gas mixture 1290 downstream and through the TVC opening 1240, and into the combustion chamber 202 downstream of the first combustion zone 202a. The first steam-combustion gas mixture 1290 is mixed with the combustion gases 66 from the first combustion zone 202a to generate a second steam-combustion gas mixture 1292. The second steam-combustion gas mixture 1292 is then directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0117] Therefore, the embodiment of the present disclosure described in detail herein provides a first flame in the first combustion zone in the combustion chamber, provides a second flame in the second combustion zone in the TVC, and injects steam into the TVC. The first flame in the first combustion zone provides flame stability in the burner under different operating conditions (e.g., low power, medium power and high power). Compared with the burner without the benefit of the present disclosure, the TVC can inject a larger amount of steam into the burner without sacrificing the operability of the burner. For example, a large amount of steam usually injected into the burner causes flame extinguishment, but the present disclosure provides the steam injected into the TVC away from the first combustion zone in the combustion chamber to avoid the first flame extinguishment in the first combustion zone. Compared with the burner without the benefit of the present disclosure, this configuration of injecting steam in the flame downstream and TVC away from the first combustion zone enables a larger amount of steam to be injected into the burner. For example, the combustion in the first combustion zone and the steam injection into the TVC prevent steam from flowing near the first flame in the combustion chamber. In this manner, the present disclosure allows for a greater amount of steam to be injected into the burner while preventing the steam from blocking the flame within the combustion chamber, thereby reducing emissions (e.g., NO x emissions, nvPM emissions, CO, and noise) and reduce SFC while providing flame stability (e.g., avoiding flameout).

[0118] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0119] A burner includes a combustion chamber, an annular dome and a trapped vortex chamber. The combustion chamber includes an outer liner and an inner liner and defines a first combustion zone. The annular dome is connected to the outer liner and the inner liner at the front end of the combustion chamber. The trapped vortex chamber extends from at least one of the outer liner or the inner liner and defines a second combustion zone. A plurality of first mixing assemblies are arranged to pass through the annular dome, and the plurality of first mixing assemblies are operable to inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are arranged to pass through the outer liner or the inner liner at the trapped vortex chamber, and the plurality of second mixing assemblies are operable to inject a second fuel-air mixture into the second combustion zone to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex chamber, the steam injector is operable to inject steam into the trapped vortex chamber, and the combustion gases are mixed with the steam in the trapped vortex chamber.

[0120] The combustor of the preceding clause, wherein the steam injector is positioned to operably inject the steam into the trapped vortex cavity upstream or downstream of the second combustion zone.

[0121] A combustor as described in any preceding clause, wherein the trapped vortex chamber comprises a trapped vortex chamber opening defined in the outer liner or the inner liner such that the trapped vortex chamber is in fluid communication with the combustion chamber.

[0122] A combustor as in any preceding clause, wherein the trapped vortex cavity opening is positioned downstream of the first combustion zone.

[0123] According to the burner described in any preceding item, the trapped vortex chamber mixes the combustion gas with the steam to generate a steam-combustion gas mixture in the trapped vortex chamber, and the trapped vortex chamber is operable to inject the steam-combustion gas mixture downstream of the first combustion zone through the trapped vortex chamber opening.

[0124] A burner as claimed in any preceding clause, wherein the trapped vortex chamber is defined by one or more walls.

[0125] The combustor of any preceding clause, at least one of the one or more walls being spaced apart from the outer liner or the inner liner such that a gap is defined between the at least one of the one or more walls and the outer liner or the inner liner.

[0126] A burner as recited in any preceding clause, further comprising a steam path defined in at least one of said one or more walls, said steam path operable to direct said steam through said at least one of said one or more walls.

[0127] A burner as claimed in any preceding clause, at least one of said one or more walls comprising a steam injection hole operable to inject said steam therethrough and into said trapped vortex chamber.

[0128] A combustor as claimed in any preceding clause, at least one of said one or more walls comprising steam cooling holes operable to direct said steam therethrough to cool said at least one of said one or more walls.

[0129] A burner as claimed in any preceding clause, wherein the steam system comprises one or more steam lines for providing the steam to the steam injector.

[0130] A combustor as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0131] A burner as claimed in any preceding clause, wherein the steam injected into the trapped vortex chamber has a water-to-air ratio of 0.0% to 60%.

[0132] A burner as claimed in any preceding clause, wherein the water-to-air ratio of the steam injected into the trapped vortex chamber is between 5% and 60%.

[0133] A burner according to any preceding clause, wherein the water-air ratio is zero to thirty percent (0% to 30%) during low power conditions, one to forty percent (1% to 40%) during medium power conditions, and two to sixty percent (2% to 60%) during high power conditions.

[0134] A combustor as claimed in any preceding clause, wherein the steam injector is operable to inject the steam downstream of the second combustion zone.

[0135] A combustor as claimed in any preceding clause, wherein the steam injector is operable to inject the steam upstream of the second combustion zone.

[0136] The combustor of any preceding clause, the outer liner and the inner liner comprising one or more liner holes operable to direct compressed air into the combustion chamber.

[0137] A combustor as in any preceding clause, wherein said first combustion zone is defined within said combustion chamber adjacent said annular dome.

[0138] The combustor of any preceding clause, each of the plurality of first mixing assemblies comprising a first mixer and a first fuel injector.

[0139] A combustor as in any preceding clause, each of said plurality of first mixing assemblies comprising a first mixing assembly swirler operable to swirl said compressed air.

[0140] A combustor as in any preceding clause, each of the plurality of second mixing assemblies comprising a second fuel injector.

[0141] A combustor as claimed in any preceding clause, the combustor defining an axial direction, a radial direction and a circumferential direction.

[0142] A combustor as described in any preceding clause, wherein the one or more walls defining the trapped vortex chamber include a first wall, a second wall, a third wall, and a fourth wall.

[0143] The burner of the preceding clause, wherein the first wall is angled relative to the axial direction.

[0144] A burner as claimed in any preceding clause, wherein the first wall is angled relative to the axial direction greater than 0° and less than 90°.

[0145] A burner as claimed in any preceding clause, wherein the first wall is at 90° relative to the axial direction.

[0146] A burner as claimed in any preceding clause, wherein the first wall is angled greater than 90° relative to the axial direction.

[0147] A combustor as claimed in any preceding clause, wherein the trapped vortex chamber opening is located axially rearward of the annular dome.

[0148] A combustor as claimed in any preceding clause, wherein the first wall and the second wall extend generally radially and the third wall and the fourth wall extend generally axially.

[0149] A combustor as claimed in any preceding clause, wherein the first wall and the second wall extend generally axially and the third wall and the fourth wall extend generally radially.

[0150] A burner as claimed in any preceding clause, wherein the trapped vortex chamber has a generally rectangular cross-section.

[0151] The combustor of any preceding clause, wherein the fourth wall is spaced apart from the outer liner or the inner liner such that the gap is defined between the fourth wall and the outer liner.

[0152] A burner according to any preceding clause, wherein the gap is radial.

[0153] A burner according to any preceding clause, wherein the gap is axial.

[0154] The combustor of any preceding clause, wherein the fourth wall is coupled to the outer liner or the inner liner via a liner extension.

[0155] A combustor as claimed in any preceding clause, said liner extension comprising one or more liner extension holes operable to direct said compressed air therethrough.

[0156] A combustor as claimed in any preceding clause, wherein the trapped vortex chamber comprises an upstream portion and a downstream portion.

[0157] A combustor as described in any preceding clause, wherein the second combustion zone is defined in the upstream portion of the trapped vortex cavity.

[0158] A combustor as in any preceding clause, wherein said steam injector injects said steam in said downstream portion of said trapped vortex chamber.

[0159] The combustor of any preceding clause, wherein the plurality of second mixing assemblies inject the compressed air into the trapped vortex chamber to generate a first vortex within the trapped vortex chamber.

[0160] The burner of any preceding clause, wherein the steam injector injects the steam through the one or more steam injection holes to generate a second vortex in the trapped vortex chamber.

[0161] A combustor as claimed in any preceding clause, wherein the first vortex is generated in the upstream portion of the trapped vortex chamber.

[0162] A combustor as claimed in any preceding clause, wherein the second vortex is generated in the downstream portion of the trapped vortex chamber.

[0163] A combustor as described in any preceding clause, wherein the trapped vortex chamber opening is defined at the downstream portion of the trapped vortex chamber.

[0164] A combustor as claimed in any preceding clause, at least one of the one or more walls defining the trapped vortex chamber comprises a dividing wall extending into the trapped vortex chamber.

[0165] A combustor as claimed in any preceding clause, wherein the dividing wall divides the trapped vortex chamber into the upstream portion and the downstream portion.

[0166] A combustor as claimed in any preceding clause, wherein the volume of the upstream portion is greater than the volume of the downstream portion.

[0167] A combustor as in any preceding clause, at least one of said one or more walls of said trapped vortex chamber comprising one or more trapped vortex chamber air holes operable to direct said compressed air into said trapped vortex chamber.

[0168] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are operable to direct said compressed air into said upstream portion of said trapped vortex chamber.

[0169] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are positioned through said first wall to operatively direct said compressed air substantially axially rearwardly into said trapped vortex chamber.

[0170] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are positioned through said second wall to operatively direct said compressed air substantially axially forwardly into said trapped vortex chamber.

[0171] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are positioned through said third wall to operatively direct said compressed air substantially radially into said trapped vortex chamber.

[0172] A burner as in any preceding clause, said one or more steam injection holes being positioned through said second wall to operatively direct said steam axially forwardly into said trapped vortex chamber.

[0173] A burner as claimed in any preceding clause, wherein said one or more steam injection holes are positioned through said third wall to operatively direct said steam radially into said trapped vortex chamber.

[0174] A combustor as claimed in any preceding clause, wherein the second fuel injector is disposed through the third wall to operatively inject the fuel radially into the trapped vortex cavity.

[0175] A combustor as claimed in any preceding clause, wherein the second fuel injector is disposed through the first wall to operatively inject the fuel axially rearwardly into the trapped vortex cavity.

[0176] A combustor as described in any preceding clause, wherein the first fuel injector is arranged through the annular dome to inject the fuel axially rearwardly into the first combustion zone.

[0177] A combustor as described in any preceding clause, wherein the first fuel injector is arranged through the annular dome to radially inject the fuel into the first combustion zone.

[0178] The combustor of any preceding clause, wherein the outer liner and the inner liner extend radially inwardly.

[0179] A combustor as claimed in any preceding clause, wherein said outer liner and said inner liner extend substantially axially.

[0180] The combustor of any preceding clause, the first fuel injector comprising one or more fuel injector lines that radially inject the fuel into the combustion chamber.

[0181] A combustor as in any preceding clause, the first fuel injector comprising a first fuel injector line and a second fuel injector line.

[0182] The burner of any preceding clause, the first fuel injector line and the second fuel injector line being annular.

[0183] According to the burner described in any of the preceding items, the first fuel injector pipeline and the second fuel injector pipeline include one or more fuel orifices spaced circumferentially around the first fuel injector pipeline and the second fuel injector pipeline, and the one or more fuel orifices are operable to guide the fuel into the combustion chamber.

[0184] A combustor as claimed in any preceding clause, wherein the steam injector comprises a steam swirler operable to swirl the steam to generate a steam swirl in the trapped vortex chamber.

[0185] According to the burner described in any of the preceding items, the one or more steam injection holes include one or more first steam injection holes and one or more second steam injection holes, the one or more first steam injection holes are positioned on the steam injector outside the retained vortex chamber, and the one or more second steam injection holes are positioned to inject the steam into the retained vortex chamber.

[0186] According to the turbine engine of the preceding clause, the one or more second steam injection holes are separate from the steam injector, and the one or more second steam injection holes are operable to direct the compressed air and the steam from outside the trapped vortex cavity into the trapped vortex cavity.

[0187] A burner as in any preceding clause, said trapped vortex chamber comprising a steam injection hole extension surrounding said one or more second steam injection holes, said one or more second steam injection holes being operable to direct said steam through said steam injection hole extension.

[0188] A burner according to any preceding clause, wherein the steam-combustion gas mixture is a first steam-combustion gas mixture, and the combustion chamber is operable to mix the first steam-combustion gas mixture with the combustion gas from the first combustion zone to generate a second steam-combustion gas mixture.

[0189] According to the burner described in any preceding item, the steam injector includes a first steam injector and a second steam injector, the first steam injector is configured to pass through the annular dome to inject the steam into the first combustion zone, and the second steam injector is configured to pass through the wall of the trapped vortex chamber to inject the steam into the trapped vortex chamber.

[0190] The combustor of any preceding clause, said first plurality of mixing assemblies comprising said first fuel injector and said first steam injector.

[0191] The combustor of any preceding clause, the trapped vortex chamber comprising a plurality of trapped vortex chambers including a first trapped vortex chamber defined in the outer liner and a second trapped vortex chamber defined in the inner liner.

[0192] A combustor as in any preceding clause, wherein the first trapped vortex cavity is radially outward from the outer liner.

[0193] A combustor as in any preceding clause, wherein the second trapped vortex cavity is radially inward from the liner.

[0194] A combustor as in any preceding clause, wherein the first trapped vortex chamber is axially forward of the liner.

[0195] A combustor as in any preceding clause, wherein the second trapped vortex chamber is axially rearward of the outer liner.

[0196] A turbine engine includes a fan and a core turbine engine, the core turbine engine including a compressor section, a combustion section and a turbine section. The combustion section includes a combustor, the combustor includes a combustion chamber, an annular dome and a trapped vortex cavity. The combustion chamber includes an outer liner and an inner liner and defines a first combustion zone. The annular dome is connected to the outer liner and the inner liner at the front end of the combustion chamber. The trapped vortex cavity extends from at least one of the outer liner or the inner liner and defines a second combustion zone. A plurality of first mixing assemblies are arranged to pass through the annular dome, and the plurality of first mixing assemblies are operable to inject a first fuel-air mixture into the first combustion zone. A plurality of second mixing assemblies are arranged to pass through the outer liner or the inner liner at the trapped vortex cavity, and the plurality of second mixing assemblies are operable to inject a second fuel-air mixture into the second combustion zone to produce combustion gases. A steam system includes a steam injector in fluid communication with the trapped vortex chamber, the steam injector operable to inject steam into the trapped vortex chamber, and the steam mixes with the combustion gases in the trapped vortex chamber.

[0197] According to the turbine engine of the preceding clause, the steam injector is positioned to operatively inject the steam into the trapped vortex cavity upstream or downstream of the second combustion zone.

[0198] A turbine engine as described in any preceding clause, wherein the trapped vortex cavity comprises a trapped vortex cavity opening defined in the outer liner or the inner liner such that the trapped vortex cavity is in fluid communication with the combustion chamber.

[0199] A turbine engine as described in any preceding clause, wherein the trapped vortex cavity opening is positioned downstream of the first combustion zone.

[0200] According to a turbine engine described in any preceding clause, the trapped vortex chamber mixes the combustion gases with the steam to generate a steam-combustion gas mixture in the trapped vortex chamber, and the trapped vortex chamber is operable to inject the steam-combustion gas mixture downstream of the first combustion zone through the trapped vortex chamber opening.

[0201] A turbine engine as claimed in any preceding clause, wherein the trapped vortex chamber is defined by one or more walls.

[0202] A turbine engine according to any preceding clause, wherein at least one of the one or more walls is spaced apart from the outer liner or the inner liner such that a gap is defined between the at least one of the one or more walls and the outer liner or the inner liner.

[0203] A turbine engine as recited in any preceding clause, further comprising a steam path defined in at least one of said one or more walls, said steam path operable to direct said steam through said at least one of said one or more walls.

[0204] A turbine engine as recited in any preceding clause, at least one of said one or more walls comprising a steam injection hole operable to inject said steam therethrough and into said trapped vortex cavity.

[0205] A turbine engine as recited in any preceding clause, at least one of said one or more walls comprising steam cooling holes operable to direct said steam therethrough to cool said at least one of said one or more walls.

[0206] A turbine engine as claimed in any preceding clause, wherein the steam system comprises one or more steam lines for providing the steam to the steam injectors.

[0207] A turbine engine as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0208] A turbine engine as claimed in any preceding clause, wherein the steam injected into the trapped vortex cavity has a water-to-air ratio of 0.0% to 60%.

[0209] A turbine engine as claimed in any preceding clause, wherein the water-to-air ratio of the steam injected into the trapped vortex cavity is between 5% and 60%.

[0210] A turbine engine according to any preceding clause, wherein the water-to-air ratio is zero to thirty percent (0% to 30%) during low power conditions, one to forty percent (1% to 40%) during medium power conditions, and two to sixty percent (2% to 60%) during high power conditions.

[0211] A turbine engine as described in any preceding clause, wherein the steam injector is operable to inject the steam downstream of the second combustion zone.

[0212] A turbine engine as described in any preceding clause, wherein the steam injector is operable to inject the steam upstream of the second combustion zone.

[0213] A turbine engine as described in any preceding clause, said outer liner and said inner liner comprising one or more liner holes operable to direct compressed air into said combustion chamber.

[0214] A turbine engine as described in any preceding clause, wherein the first combustion zone is defined within the combustion chamber adjacent the annular dome.

[0215] A turbine engine as described in any preceding clause, each of the plurality of first mixing assemblies comprising a first mixer and a first fuel injector.

[0216] A turbine engine as recited in any preceding clause, each of said plurality of first mixing assemblies comprising a first mixing assembly swirler operable to swirl said compressed air.

[0217] A turbine engine as described in any preceding clause, each of said plurality of second mixing assemblies comprising a second fuel injector.

[0218] A turbine engine as described in any preceding clause, wherein the combustor defines an axial direction, a radial direction and a circumferential direction.

[0219] A turbine engine as described in any preceding clause, wherein the one or more walls defining the trapped vortex chamber include a first wall, a second wall, a third wall, and a fourth wall.

[0220] Turbine engine according to the preceding clause, wherein said first wall is angled relative to said axial direction.

[0221] A turbine engine according to any preceding clause, wherein the first wall is angled relative to the axial direction greater than 0° and less than 90°.

[0222] A turbine engine as claimed in any preceding clause, wherein the first wall is at 90° relative to the axial direction.

[0223] A turbine engine as claimed in any preceding clause, wherein the first wall is angled more than 90° relative to the axial direction.

[0224] A turbine engine as claimed in any preceding clause, wherein the trapped vortex chamber opening is located axially rearward of the annular dome.

[0225] A turbine engine according to any preceding clause, wherein the first wall and the second wall extend generally radially, and the third wall and the fourth wall extend generally axially.

[0226] A turbine engine according to any preceding clause, wherein the first wall and the second wall extend generally axially and the third wall and the fourth wall extend generally radially.

[0227] A turbine engine as claimed in any preceding clause, wherein the trapped vortex chamber has a generally rectangular cross-section.

[0228] A turbine engine as described in any preceding clause, wherein the fourth wall is spaced apart from the outer liner or the inner liner such that the gap is defined between the fourth wall and the outer liner.

[0229] A turbine engine according to any preceding clause, wherein said clearance is radial.

[0230] A turbine engine according to any preceding clause, wherein said clearance is axial.

[0231] A turbine engine as claimed in any preceding clause, wherein the fourth wall is coupled to the outer liner or the inner liner via a liner extension.

[0232] A turbine engine as described in any preceding clause, wherein the liner extension includes one or more liner extension holes operable to direct the compressed air therethrough.

[0233] A turbine engine as described in any preceding clause, wherein the trapped vortex chamber comprises an upstream portion and a downstream portion.

[0234] A turbine engine as described in any preceding clause, wherein the second combustion zone is defined in the upstream portion of the trapped vortex cavity.

[0235] A turbine engine as claimed in any preceding clause, wherein said steam injector injects said steam in said downstream portion of said trapped vortex cavity.

[0236] A turbine engine as recited in any preceding clause, wherein said plurality of second mixing assemblies inject said compressed air into said trapped vortex chamber to generate a first vortex within said trapped vortex chamber.

[0237] A turbine engine as claimed in any preceding clause, wherein the steam injector injects the steam through the one or more steam injection holes to generate a second vortex in the trapped vortex chamber.

[0238] A turbine engine as claimed in any preceding clause, wherein the first vortex is generated in the upstream portion of the trapped vortex cavity.

[0239] A turbine engine as claimed in any preceding clause, wherein the second vortex is generated in the downstream portion of the trapped vortex chamber.

[0240] A turbine engine as described in any preceding clause, wherein the trapped vortex chamber opening is defined at the downstream portion of the trapped vortex chamber.

[0241] A turbine engine as claimed in any preceding clause, wherein at least one of said one or more walls defining said trapped vortex chamber comprises a dividing wall extending into said trapped vortex chamber.

[0242] A turbine engine as claimed in any preceding clause, wherein said dividing wall divides said trapped vortex chamber into said upstream portion and said downstream portion.

[0243] A turbine engine as claimed in any preceding clause, wherein the volume of the upstream portion is greater than the volume of the downstream portion.

[0244] A turbine engine as recited in any preceding clause, at least one of said one or more walls of said trapped vortex chamber comprising one or more trapped vortex chamber air holes operable to direct said compressed air into said trapped vortex chamber.

[0245] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex chamber air holes are operable to direct said compressed air into said upstream portion of said trapped vortex chamber.

[0246] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex chamber air holes are positioned through said first wall to operatively direct said compressed air substantially axially rearwardly into said trapped vortex chamber.

[0247] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex chamber apertures are positioned through said second wall to operatively direct said compressed air substantially axially forwardly into said trapped vortex chamber.

[0248] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex chamber air holes are positioned through said third wall to operatively direct said compressed air substantially radially into said trapped vortex chamber.

[0249] A turbine engine as described in any preceding clause, wherein said one or more steam injection holes are positioned through said second wall to operatively direct said steam axially forwardly into said trapped vortex chamber.

[0250] A turbine engine as described in any preceding clause, wherein said one or more steam injection holes are positioned through said third wall to operatively direct said steam radially into said trapped vortex chamber.

[0251] A turbine engine as described in any preceding clause, wherein the second fuel injector is disposed through the third wall to operatively inject the fuel radially into the trapped vortex cavity.

[0252] A turbine engine as described in any preceding clause, wherein the second fuel injector is disposed through the first wall to operatively inject the fuel axially rearwardly into the trapped vortex cavity.

[0253] A turbine engine as described in any preceding clause, wherein the first fuel injector is arranged through the annular dome to inject the fuel axially rearwardly into the first combustion zone.

[0254] A turbine engine as described in any preceding clause, wherein the first fuel injector is arranged through the annular dome to inject the fuel radially into the first combustion zone.

[0255] A turbine engine as described in any preceding clause, wherein said outer liner and said inner liner extend radially inwardly.

[0256] A turbine engine as claimed in any preceding clause, wherein said outer liner and said inner liner extend substantially axially.

[0257] A turbine engine as claimed in any preceding clause, wherein the first fuel injector comprises one or more fuel injector lines which radially inject the fuel into the combustion chamber.

[0258] A turbine engine as in any preceding clause, the first fuel injector comprising a first fuel injector line and a second fuel injector line.

[0259] A turbine engine as described in any preceding clause, wherein the first fuel injector line and the second fuel injector line are annular.

[0260] According to any of the preceding clauses, the first fuel injector line and the second fuel injector line include one or more fuel orifices spaced circumferentially around the first fuel injector line and the second fuel injector line, and the one or more fuel orifices are operable to direct the fuel into the combustion chamber.

[0261] A turbine engine as recited in any preceding clause, said steam injector comprising a steam swirler operable to swirl said steam to generate a steam swirl in said trapped vortex chamber.

[0262] According to the turbine engine described in any of the preceding items, the one or more steam injection holes include one or more first steam injection holes and one or more second steam injection holes, the one or more first steam injection holes are positioned on the steam injector outside the retained vortex cavity, and the one or more second steam injection holes are positioned to inject the steam into the retained vortex cavity.

[0263] According to the turbine engine of the preceding clause, the one or more second steam injection holes are separate from the steam injector, and the one or more second steam injection holes are operable to direct the compressed air and the steam from outside the trapped vortex cavity into the trapped vortex cavity.

[0264] A turbine engine as described in any preceding clause, wherein the trapped vortex chamber includes a steam injection hole extension surrounding the one or more second steam injection holes, the one or more second steam injection holes being operable to direct the steam through the steam injection hole extension.

[0265] A turbine engine according to any preceding clause, wherein the steam-combustion gas mixture is a first steam-combustion gas mixture, and the combustor is operable to mix the first steam-combustion gas mixture with the combustion gas from the first combustion zone to generate a second steam-combustion gas mixture.

[0266] According to a turbine engine described in any preceding item, the steam injector includes a first steam injector and a second steam injector, the first steam injector is configured to pass through the annular dome to inject the steam into the first combustion zone, and the second steam injector is configured to pass through the wall of the trapped vortex cavity to inject the steam into the trapped vortex cavity.

[0267] A turbine engine as in any preceding clause, said first plurality of mixing assemblies comprising said first fuel injector and said first steam injector.

[0268] A turbine engine as in any preceding clause, the trapped vortex cavity comprising a plurality of TVC trapped vortex cavities including a first trapped vortex cavity defined in the outer liner and a second trapped vortex cavity defined in the inner liner.

[0269] A turbine engine as claimed in any preceding clause, wherein said first trapped vortex cavity is radially outward from said outer liner.

[0270] A turbine engine as claimed in any preceding clause, wherein said second trapped vortex cavity is radially inward from said liner.

[0271] A turbine engine as claimed in any preceding clause, wherein said first trapped vortex chamber is axially forward of said liner.

[0272] A turbine engine as claimed in any preceding clause, wherein the second trapped vortex chamber is axially rearward of the outer liner.

[0273] A method for operating a combustor or turbine engine according to any of the preceding clauses, the method comprising: generating the first fuel-air mixture using the plurality of first mixing assemblies; injecting the first fuel-air mixture into the first combustion zone of the combustion chamber to generate a first flame; generating the second fuel-air mixture using the plurality of second mixing assemblies; injecting the second fuel-air mixture into the second combustion zone of the trapped vortex cavity to generate a second flame that produces combustion gases; and injecting the steam into the trapped vortex cavity using the steam injector so that the steam mixes with the combustion gases in the trapped vortex cavity.

[0274] A method as in any preceding clause, further comprising injecting the steam into the trapped vortex chamber upstream or downstream of the second combustion zone.

[0275] A method as in any preceding clause, further comprising generating a vortex within the trapped vortex chamber, the vortex mixing with the second fuel-air mixture within the trapped vortex chamber.

[0276] A method as in any preceding clause, further comprising generating the vortex within the trapped vortex chamber such that the second flame is trapped within the trapped vortex chamber.

[0277] A method as in any preceding clause, wherein the trapped vortex chamber comprises one or more walls and a steam path defined in at least one of the one or more walls, the method further comprising directing the steam through the steam path of the at least one of the one or more walls.

[0278] A method as in any preceding clause, wherein the trapped vortex chamber comprises one or more walls, and at least one of the one or more walls comprises a steam injection hole, the method further comprising injecting the steam through the steam injection hole and into the trapped vortex chamber.

[0279] A method according to any preceding clause, wherein the trapped vortex chamber comprises one or more walls, and at least one of the one or more walls comprises a steam cooling hole, the method further comprising directing the steam through the steam cooling hole to cool the at least one of the one or more walls.

[0280] A method as in any preceding clause, further comprising injecting the steam with the steam injector during operating conditions of the turbine engine above an idle condition of the turbine engine.

[0281] A method as in any preceding clause, further comprising injecting a greater amount of said steam during said high power condition than during said medium power condition.

[0282] A method as in any preceding clause, further comprising mixing the combustion gas with the steam to generate a steam-combustion gas mixture in the trapped vortex chamber.

[0283] The method of any preceding clause, further comprising injecting the steam-combustion gas mixture from the trapped vortex cavity into the combustion chamber downstream of the first combustion zone.

[0284] A method as in any preceding clause, further comprising providing the steam from the steam system to the steam injector via a steam line.

[0285] A method as in any preceding clause, further comprising extracting said steam from exhaust gas of said turbine engine using said steam system.

[0286] A method as claimed in any preceding clause wherein the steam injected into the trapped vortex chamber has a water-to-air ratio of 0.0% to 60%.

[0287] A method as claimed in any preceding clause wherein the steam injected into the trapped vortex chamber has a water-to-air ratio of 5% to 60%.

[0288] A method as described in any preceding clause, wherein the water-to-air ratio is zero to thirty percent (0% to 30%) during low power conditions, one to forty percent (1% to 40%) during medium power conditions, and two to sixty percent (2% to 60%) during high power conditions.

[0289] A method as in any preceding clause, further comprising injecting the steam downstream of the second combustion zone.

[0290] A method as in any preceding clause, further comprising injecting the steam upstream of the second combustion zone.

[0291] The method of any preceding clause, further comprising directing compressed air into the combustion chamber through one or more liner air holes to cool the outer liner or the inner liner.

[0292] A method as in any preceding clause, wherein the plurality of first mixing assemblies comprises a first mixing assembly swirler, the method further comprising swirling the compressed air using the first mixing assembly swirler.

[0293] A method as in any preceding clause, further comprising injecting the combustion gases from the trapped vortex cavity into the combustion chamber axially rearward of the first combustion zone.

[0294] The method of any preceding clause, further comprising directing the steam through the steam path within the one or more walls of the trapped vortex chamber to cool the one or more walls of the trapped vortex chamber.

[0295] A method as in any preceding clause, the trapped vortex chamber comprising an upstream portion and a downstream portion, the method further comprising injecting the steam into the downstream portion of the trapped vortex chamber using the steam injector.

[0296] A method as in any preceding clause, the trapped vortex chamber comprising an upstream portion and a downstream portion, the method further comprising injecting the steam into the upstream portion of the trapped vortex chamber using the steam injector.

[0297] A method as defined in any preceding clause, further comprising injecting the compressed air into the trapped vortex chamber and generating a first vortex of the compressed air within the trapped vortex chamber.

[0298] A method as in any preceding clause, further comprising injecting the steam into the trapped vortex chamber and generating a second vortex of the steam within the trapped vortex chamber.

[0299] A method as in any preceding clause, further comprising generating the first vortex in the upstream portion of the trapped vortex chamber.

[0300] A method as in any preceding clause, further comprising generating the second vortex in the downstream portion of the trapped vortex chamber.

[0301] The method of any preceding clause, further comprising generating a first fuel flow in the first combustion zone using the plurality of first mixing assemblies.

[0302] The method of any preceding clause, further comprising generating a first compressed air flow in the first combustion zone using the plurality of first mixing assemblies.

[0303] The method of any preceding clause, further comprising mixing the first fuel flow and the first compressed air flow to generate the first fuel-air mixture in the first combustion zone.

[0304] A method as in any preceding clause, wherein at least one of the one or more walls comprises one or more trapped vortex chamber air holes, the method further comprising directing the compressed air into the trapped vortex chamber through the one or more trapped vortex chamber air holes.

[0305] A method as in any preceding clause, further comprising directing the compressed air into the upstream portion of the trapped vortex chamber through the one or more trapped vortex chamber air holes.

[0306] A method as in any preceding clause, further comprising directing the compressed air axially forwardly into the trapped vortex chamber through the one or more trapped vortex chamber air holes.

[0307] A method as in any preceding clause, further comprising directing the compressed air radially into the trapped vortex chamber through the one or more trapped vortex chamber air holes.

[0308] A method as in any preceding clause, further comprising directing the compressed air into the trapped vortex chamber at an angle greater than 0° and less than 90° relative to the axial direction.

[0309] A method as in any preceding clause, wherein the first wall is at 90° relative to the axial direction.

[0310] A method as in any preceding clause, wherein the first wall is angled greater than 90° relative to the axial direction.

[0311] The method of any preceding clause, further comprising generating a second fuel flow in the second combustion zone using the plurality of second mixing assemblies.

[0312] The method of any preceding clause, further comprising generating a second compressed air flow in the second combustion zone using the plurality of second mixing assemblies.

[0313] The method of any preceding clause, further comprising mixing the second fuel flow and the second compressed air flow to generate the second fuel-air mixture in the second combustion zone.

[0314] A method as in any preceding clause, further comprising injecting the steam axially forwardly into the trapped vortex chamber.

[0315] A method as in any preceding clause, further comprising radially injecting the steam into the trapped vortex chamber.

[0316] A method as in any preceding clause, the steam injector comprising a steam swirler, the method further comprising swirling the steam through the steam swirler to generate a steam swirl in the trapped vortex chamber.

[0317] A method as in any preceding clause, further comprising injecting the first fuel stream axially rearwardly into the first combustion zone.

[0318] A method as in any preceding clause, further comprising radially injecting the first fuel stream into the first combustion zone.

[0319] A method as defined in any preceding clause, further comprising injecting the second fuel stream axially rearwardly into the trapped vortex cavity.

[0320] A method as in any preceding clause, further comprising injecting the second fuel flow radially into the trapped vortex cavity.

[0321] A method as in any preceding clause, wherein the steam injector comprises one or more first steam injection holes, the method further comprising injecting the steam external to the trapped vortex chamber through the one or more first steam injection holes.

[0322] A method as in any preceding clause, wherein the steam injector comprises one or more second steam injection holes, the method further comprising injecting the steam into the trapped vortex chamber through the one or more second steam injection holes.

[0323] The method of any preceding clause, further comprising injecting the steam through the one or more first steam injection holes to generate a first steam injection flow outside of the trapped vortex chamber.

[0324] The method of any preceding clause, further comprising injecting the first steam injection stream through the one or more second steam injection holes to generate a second steam injection stream in the trapped vortex chamber.

[0325] A method as in any preceding clause, wherein the trapped vortex chamber comprises a steam injection hole extension surrounding the one or more second steam injection holes, the method further comprising directing the first steam injection flow through the steam injection hole extension.

[0326] A method as in any preceding clause, further comprising mixing the first steam injection flow with the compressed air outside of the trapped vortex chamber.

[0327] A method as in any preceding clause, wherein the steam-combustion gas mixture is a first steam-combustion gas mixture, the method further comprising mixing the first steam-combustion gas mixture with the combustion gas from the first combustion zone to generate a second steam-combustion gas mixture.

[0328] The method of any preceding clause, the steam injector comprising a first steam injector, the method further comprising injecting the steam into the first combustion zone via the first steam injector.

[0329] A method as in any preceding clause, the steam injector comprising a second steam injector, the method further comprising injecting the steam into the second combustion zone via the second steam injector.

[0330] Although the foregoing description is directed to the preferred embodiments of the present disclosure, other changes and modifications are apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that: include: a combustion chamber including an outer liner and an inner liner and defining a first combustion zone; an annular dome coupled to the outer liner and the inner liner at a forward end of the combustion chamber; a trapped vortex chamber extending from at least one of the outer liner or the inner liner and defining a second combustion zone; a plurality of first mixing assemblies disposed through the annular dome, the plurality of first mixing assemblies operable to inject a first fuel-air mixture into the first combustion zone; a plurality of second mixing assemblies disposed through the outer liner or the inner liner at the trapped vortex cavity, the plurality of second mixing assemblies operable to inject a second fuel-air mixture into the second combustion zone to generate combustion gases; as well as A steam system includes a steam injector in fluid communication with the trapped vortex chamber, the steam injector operable to inject steam into the trapped vortex chamber and the steam mixes with the combustion gases in the trapped vortex chamber.

2. The burner according to claim 1, characterized in that in, The steam injector is positioned to operably inject the steam into the trapped vortex chamber upstream or downstream of the second combustion zone.

3. The burner according to claim 1, characterized in that in, The steam injected into the trapped vortex chamber has a water-to-air ratio of 0.0% to 60%.

4. The burner according to claim 1, characterized in that in, The trapped vortex chamber includes a trapped vortex chamber opening defined in the outer liner or the inner liner such that the trapped vortex chamber is in fluid communication with the combustion chamber.

5. The burner according to claim 4, characterized in that in, The trapped vortex cavity opening is positioned downstream of the first combustion zone.

6. The burner according to claim 4, characterized in that in, The trapped vortex chamber mixes the combustion gases with the steam to generate a steam-combustion gas mixture in the trapped vortex chamber, and the trapped vortex chamber is operable to inject the steam-combustion gas mixture downstream of the first combustion zone through the trapped vortex chamber opening.

7. The burner according to claim 1, characterized in that in, The trapped vortex chamber is defined by one or more walls, and wherein at least one of the one or more walls is spaced apart from the outer liner or the inner liner such that a gap is defined between the at least one of the one or more walls and the outer liner or the inner liner.

8. The burner according to claim 7, characterized in that Further included is a steam path defined in at least one of the one or more walls, the steam path operable to direct the steam through the at least one of the one or more walls.

9. The burner according to claim 7, characterized in that in, At least one of the one or more walls includes a steam injection hole operable to inject the steam therethrough and into the trapped vortex chamber.

10. The burner according to claim 7, characterized in that in, At least one of the one or more walls includes steam cooling holes operable to direct the steam therethrough to cool the at least one of the one or more walls.

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