Combustor

Abstract

A combustor has a main chamber and a trapped vortex chamber. The main chamber includes an outer liner and an inner liner. A trapped vortex cavity extends from at least one of the outer liner or the inner liner. A plurality of mixing assemblies are operable to inject a fuel-air mixture into the trapped vortex chamber to produce combustion gases. The trapped vortex chamber injects combustion gases into the main chamber. A steam system is in fluid communication with the main chamber. The steam system is operable to inject steam into the main chamber such that the steam flows downstream of the trapped vortex chamber.

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 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 According to the present disclosure Figure 2 The cross section 3-3 in Figure 2 Schematic cross-sectional view of a burner.

[0007] Figure 4 According to the present disclosure Figure 2 Schematic cross-sectional view of the burner taken at cross section 4-4 in FIG.

[0008] Figure 5 is a schematic cross-sectional view of a combustor taken at a latitudinal centerline axis of the combustor in accordance with the present disclosure.

[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.

[0016] Fig.13 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.

[0017] Fig.14 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.

[0018] Fig.15 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.

[0019] Fig.16 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.

[0020] Fig.17 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.

[0021] Fig.18 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

[0022] 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.

[0023] 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.

[0024] As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0025] 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.

[0026] 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.

[0027] 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, 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 that is configured to operate at a power output lower than a "high power" setting for the engine, while a "medium power" setting defines an engine 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.

[0028] The various power levels of the turbine engine or combustor detailed herein are defined as percentages of the maximum engine rated thrust at sea level static (SLS). Low power operation includes, for example, less than thirty percent (30%) of the SLS maximum engine rated thrust of the turbine engine. Medium power operation includes, for example, thirty percent (30%) to eighty-five percent (85%) of the SLS maximum engine rated thrust of the turbine engine. High power operation includes, 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 or combustor is exemplary only, and other values ​​of thrust can be used to define low power operation, medium power operation, and high power operation.

[0029] 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.

[0030] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0031] 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.

[0032] 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 chamber of the combustor and that at least partially mix fuel in a swirling vortex of compressed air within the one or more chambers.

[0033] 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.

[0034] 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.

[0035] 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 x Emissions. For example, the more steam injected into the combustor, the more the SFC will be reduced. However, steam in the combustor increases CO emissions and can cause flameouts because the steam blocks the flame (e.g., reduces 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.

[0036] 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 xThe invention relates to a turbine engine that is provided with a burner having a trapped vortex cavity (TVC) that is fluidly connected to a main chamber of the burner. Combustion occurs primarily in the TVC. In some embodiments, fuel is injected only in the TVC, and no fuel is injected into the main chamber, so that combustion does not occur in the main chamber. The turbine engine includes a steam system that generates steam from the exhaust gas of the turbine engine. The steam system injects steam into the main chamber from the liner of the burner, from the tip of the fuel nozzle, or from both the liner and the tip of the fuel nozzle. In some embodiments, the steam system injects steam downstream of the TVC. This configuration of injecting steam into the main chamber away from the TVC (e.g., downstream of the TVC) provides flame stability (e.g., reduces the risk of flameout) under various operating conditions (e.g., low power, medium power, and high power) by injecting steam away from the flame in the TVC.

[0037] Compared with the burner without the benefit of the present disclosure, TVC can inject more steam into the burner without sacrificing the operability of the burner. In a non-limiting example, steam is injected into the main chamber away from the TVC to avoid operability problems and avoid flameout when the steam is injected away from the flame in the TVC. Additionally or alternatively, the burner includes a plurality of TVCs, wherein steam is injected into the main chamber and downstream of a plurality of TVCs. In addition, steam can be injected between a plurality of TVCs. Additionally or alternatively, steam is mixed with air before being injected into the TVC. In the configuration where steam is also injected into the TVC, most of the steam is injected into the main chamber, and a lesser portion of steam is injected into the TVC. Compared with the burner without the benefit of the present disclosure, this configuration where most of the steam is injected into the main chamber enables a larger amount of steam to be injected into the burner to reduce emissions and reduce SFC while providing flame stability (e.g., avoiding flameout). The present disclosure provides up to 60% WAR, thereby enabling large amounts of steam to reduce emissions and reduce SFC while providing flame stability in the combustor (eg, avoiding flameout).

[0038] 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 1 As 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 .

[0039] 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.

[0040] 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 .

[0041] Still reference Figure 1 In 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 casing or nacelle 50 that circumferentially surrounds fan 38 or 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.

[0042] 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.

[0043] The combustion gases 66 are directed into and expanded through the HP turbine 28, wherein a portion of the heat or 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 or 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.

[0044] 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.

[0045] 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.

[0046] The turbine engine 10 includes a steam system 90 in fluid communication with the exhaust nozzle section 32. The steam system 90 includes one or more steam lines 92 to provide steam 69 to the combustion section 26, as described in further detail below. For example, the steam system 90 extracts steam 69 from the exhaust gas in the exhaust nozzle section 32. In some embodiments, the steam system 90 includes a water tank, etc., and a heater for generating steam 69 and supplying steam 69 to the combustion section 26.

[0047] 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.

[0048] 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 main 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.

[0049] 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 main chamber 202. The outer liner 204 defines the radial outer boundary of the main chamber 202, and the inner liner 206 defines the radial inner boundary of the main chamber 202. The outer liner 204 and the inner liner 206 are radially inwardly spaced from the outer combustor casing 208 and the inner combustor casing 209 extending circumferentially around the outer liner 204 and the inner liner 206, respectively. The outer liner 204 and the inner liner 206 include one or more liner steam holes 205, which are operable to guide steam 69 through the outer liner 204 and the inner liner 206 and into the main chamber 202, as further described below. The combustor 200 also includes an annular dome 210 installed upstream of the outer liner 204 and the inner liner 206. The annular dome 210 defines the upstream end of the main chamber 202. The main chamber 202 extends to a combustor outlet 211.

[0050] Multiple mixing components 212 ( Figure 2 Only one is shown) are spaced circumferentially around the annular dome 210. Figure 2 , the mixing assembly 212 is shown to include a main mixer 214. A plurality of fuel injectors 218 ( Figure 2 The plurality of fuel injectors 218 are circumferentially spaced about the annular dome 210 and extend radially from the outer combustor casing 208 to the plurality of mixing assemblies 212. In some embodiments, the plurality of 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. The plurality of fuel injectors 218 include a first fuel injector 218a and a second fuel injector 218b. The first fuel injector 218a includes one or more first fuel injection holes 220a for radially outwardly injecting fuel 67, as further described below. The second fuel injector 218b includes one or more second fuel injection holes 220b for radially inwardly injecting fuel 67, as further described below.

[0051] One or more steam injectors 222 are coupled in flow communication with the plurality of mixing assemblies 212. The one or more steam injectors 222 are spaced circumferentially about the annular dome 210 and extend radially from the outer combustor casing 208 to the plurality of mixing assemblies 212. In some embodiments, the one or more steam injectors 222 extend from the inner combustor casing 209. Each of the one or more steam injectors 222 includes one or more steam injection holes 224 for injecting steam 69 axially rearward or generally radially into the main chamber 202. For example, the steam system 90( Figure 1 ) through one or more steam lines 92 ( Figure 2) supplies steam 69 to one or more steam injectors 222, and one or more steam injectors 222 inject steam 69 therethrough, as further described below. One or more steam injection holes 224 include one or more discrete holes, some of which are circumferentially spaced around one or more steam injectors 222.

[0052] The combustor 200 includes a plurality of trapped vortex cavities (TVCs) 230 that each define a combustion zone 231. The plurality of TVCs 230 include a first TVC 230a extending from the outer liner 204 and a second TVC 230b extending from the inner liner 206. Each of the plurality of TVCs 230 is a cavity and is used to generate a trapped vortex of a fuel-air mixture, as further described below. For example, a plurality of fuel injectors 218 are positioned to radially inject fuel 67 into each of the plurality of TVCs 230, as further described below. Each of the plurality of TVCs 230 is positioned radially outward of the main chamber 202.

[0053] Each of the plurality of TVCs 230 is defined by one or more walls 232, 234, 236, 238 (collectively referred to as the walls of a corresponding one of the plurality of TVCs 230). For example, each of the plurality of TVCs 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 annular dome 210 defines at least a portion of the first wall 232 and the fourth wall 238. 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 from the outer liner 204 to a rearward end of the third wall 236. The third wall 236 is spaced radially outward from the fourth wall 238. The third wall 236 extends generally axially from a radially outer end of the first wall 232 to a radially outer end of the second wall 234.

[0054] The main mixer 214 extends through the annular dome 210 to separate the first TVC 230a and the second TVC 230b. In this way, the main mixer 214 is disposed between the fourth wall 238 of the first TVC 230a and the fourth wall 238 of the second TVC 230b. The fourth wall 238 of each TVC 230 extends axially from the radially inner end of the first wall 232 to a position axially forward of one or more first fuel injection holes 220a and one or more second fuel injection holes 220b. Each of the plurality of TVCs 230 also includes a TVC opening 240 defined between the second wall 234 and the main mixer 214.

[0055] Each of the plurality of TVCs 230 is defined between a first wall 232, a second wall 234, a third wall 236, and a fourth wall 238. In this manner, each of the plurality of TVCs 230 is generally located radially outward and axially forward (e.g., upstream) of the main chamber 202. The outer liner 204 and the inner liner 206 extend axially rearward from the plurality of TVCs 230, and the main chamber 202 is defined downstream of the plurality of TVCs 230. The outer liner 204 and the inner liner 206 are angled inwardly toward each other to define a converging nozzle to accelerate the combustion gases 66 therethrough to the combustor outlet 211. One or more liner steam holes 205 are positioned on the outer liner 204 and the inner liner 206 axially rearward of the plurality of TVCs 230 to inject steam 69 downstream of the plurality of TVCs 230, as described in further detail below. TVC openings 240 are openings in the outer liner 204 or the inner liner 206 to provide flow communication from each TVC 230 to the main chamber 202. Figure 2 The plurality of TVCs 230 shown in FIG. 2 include a substantially rectangular cross-section, but the plurality of TVCs 230 may include any shape.

[0056] Each of the plurality of TVCs 230 includes one or more TVC air holes 242 defined through at least one of the one or more walls 232, 234, 236, 238. As a non-limiting example, the one or more TVC air holes 242 are defined through the first wall 232 or the annular dome 210. The size of each of the one or more TVC air holes 242, the number of the one or more TVC air holes 242, and the circumferential spacing between the corresponding TVC air holes in the one or more TVC air holes 242 are based on the amount of airflow desired to generate the vortex 254 in each of the plurality of TVCs 230, as further described below. In addition, the one or more TVC air holes 242 are generally circular openings, but may include any other shape, such as an elliptical slot, etc. The combustor 200 also includes a diffuser section 244, which is defined between the outer combustor casing 208 and the inner combustor casing 209, and upstream of the main chamber 202 and the plurality of TVCs 230 (e.g., upstream of the annular dome 210).

[0057] In operation, the plurality of fuel injectors 218 radially inject fuel 67 into each of the plurality of TVCs 230 to generate a fuel flow 250 within each of the plurality of TVCs 230. For example, the first fuel injector 218a radially injects fuel 67 into the first TVC 230a, and the second fuel injector 218b radially injects fuel 67 into the second TVC 230b. At the same time, the combustor 200 receives fuel from the HP compressor 24 ( Figure 1 ) discharged compressed air 65. A portion of the compressed air 65 is directed through the one or more TVC air holes 242 to generate a compressed air flow 252. For example, the one or more TVC air holes 242 can be operated to direct the compressed air 65 axially rearward through the first wall 232 into each of the plurality of TVCs 230 (e.g., into the first TVC 230a and the second TVC 230b) and generate a vortex 254 within each of the plurality of TVCs 230.

[0058] In each of the plurality of TVCs 230, the compressed air stream 252 is mixed with the fuel stream 250 from each fuel injector 218. For example, the fuel stream 250 is injected substantially perpendicular to the compressed air stream 252. This configuration is referred to as a jet-in-crossflow fuel injection. The vortex 254 and the crossflow fuel injection of the fuel stream 250 facilitate mixing of the fuel stream 250 and the compressed air stream 252 to generate a fuel-air mixture. The fuel-air mixture is ignited by an igniter (for clarity, Figure 2The vortex 254 entraps the flame within each of the plurality of TVCs 230, such that the fuel-air mixture is completely combusted within each of the plurality of TVCs 230, and the combustion gases 66 are produced within each of the plurality of TVCs 230.

[0059] The plurality of TVCs 230 are operable to direct the combustion gases 66 through the TVC openings 240 and into the main chamber 202. The one or more steam injectors 222 inject steam 69 through the one or more steam injection holes 224 to generate a first steam flow 260. For example, the one or more steam injectors 222 inject steam 69 axially rearwardly into the main chamber 202 and downstream of the plurality of TVCs 230. The one or more liner steam holes 205 are operable to inject the compressed air 65 and steam from the steam system 90 ( Figure 1 ) is directed through the outer liner 204 and the inner liner 206 and into the main chamber 202, thereby generating a second steam flow 262 in the main chamber 202 downstream of the plurality of TVCs 230. In some embodiments, the combustor 200 includes a steam swirler at the steam injector 222 or at one or more liner steam holes 205 to swirl the first steam flow 260 or the second steam flow 262, respectively.

[0060] At the main chamber 202, the combustion gases 66 are mixed with the first steam flow 260 and the second steam flow 262 to generate a steam-combustion gas mixture 270. In some embodiments, one or more liner steam holes 205 are tangentially angled on the outer liner 204 or the inner liner 206 so that the second steam flow 262 is generated at an angle other than ninety degrees (90°), thereby improving the mixing of the second steam flow 262 with the combustion gases 66. The main chamber 202 is then operable to direct the steam-combustion gas mixture 270 to exit the main chamber 202 through the combustor outlet 211, and the steam-combustion gas mixture 270 is directed downstream to the HP turbine 28 ( Figure 1 )'s first stage turbine nozzle.

[0061] The steam system 90 may be located within the turbine engine 10 ( Figure 1) during various operating conditions of a mission cycle. The mission cycle includes, 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, the steam system 90 does not inject steam 69 into the main chamber 202. During operating conditions above idle conditions (e.g., taxi and approach), during medium power operation, and during high power operation, the steam system 90 is operable to inject steam 69. During high power operation, the steam system 90 is operable to inject a larger amount of steam 69 than during medium power operation.

[0062] When the steam system 90 injects steam 69 into the main chamber 202, the plurality of TVCs 230 provide an upstream chamber for combustion. This configuration enables a water-to-air ratio (WAR) of the steam 69 to the compressed air 65 within the main chamber 202 of up to 60%. For example, the WAR is 0.0% to 60%, and preferably 5% to 60%. In some embodiments, the WAR is 0.0% to 60% 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. For example, the WAR in the main chamber 202 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. In this way, during the turbine engine 10 ( Figure 1 ) or any operating condition of the combustor 200 above the idle condition, the steam 69 is injected into the main chamber 202. Therefore, the steam 69 injected into the main chamber 202 can achieve reduced emissions (NOx emissions, nvPM emissions, CO emissions, noise) and reduced specific fuel capacity (SFC) compared to a turbine engine without the benefit of the present disclosure, while avoiding flameout of the flames within the plurality of TVCs 230 because the steam 69 is injected into the main chamber 202 away from the flames within each of the plurality of TVCs 230.

[0063] Figure 3 According to the present disclosure Figure 2 Schematic cross-sectional view of the combustor 200 taken at cross section 3-3 in FIG. Figure 3 The first TVC 230a and the second TVC 230b are shown around the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1) is annular. The one or more TVC air holes 242 include a plurality of discrete air holes disposed through the first wall 232. In addition, the first fuel injector 218a and the second fuel injector 218b are disposed around the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1 ) is annular. The one or more first fuel injection holes 220a and the one or more second fuel injection holes 220b each include a plurality of discrete fuel injection holes circumferentially spaced around the first fuel injector 218a and the second fuel injector 218b, respectively. The one or more steam injectors 222 include a plurality of discrete fuel injection holes circumferentially spaced around the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1 ) is an annular steam injector. One or more steam injectors 222 include a steam injector 222 disposed around the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1 ) is a single steam injection channel in an annular shape. However, one or more steam injectors 222 may include one or more steam injection holes 224 to inject steam 69 into the main chamber 202.

[0064] In some embodiments, a portion of the steam 69 and the fuel 67 are injected into a plurality of TVCs 230. For example, one or more fuel injection holes 220 and one or more steam injection holes 224 are circumferentially alternated around the first fuel injector 218a and the second fuel injector 218b such that the portion of the steam 69 and the fuel 67 are radially injected into the first TVC 230a and the second TVC 230b. In some embodiments, one or more fuel injection holes 220 and one or more steam injection holes 224 are circumferentially positioned around the first fuel injector 218a and the second fuel injector 218b such that a plurality of fuel injection holes 220 and a plurality of steam injection holes 224 are alternated.

[0065] Figure 4 According to the present disclosure Figure 2 Schematic cross-sectional view of the combustor 200 taken at cross section 4-4 in FIG. Figure 4 One or more liner steam holes 205 are shown to include a plurality of discrete liner steam holes spaced circumferentially about outer liner 204 and inner liner 206. In this manner, one or more liner steam holes 205 are operable to direct a second steam flow 262 through outer liner 204 and inner liner 206 and into main chamber 202.

[0066] Figure 5 is a schematic cross-sectional view of a burner 500 taken at a latitudinal centerline axis of the burner 500 according to the present disclosure. Figure 2 The burner 200 is basically similar. Figure 5The combustor 500 is shown to include a plurality of fuel injectors 518 each having a plurality of fuel injection holes 520, a plurality of steam injectors 522 each having one or more steam injection holes 524, and a plurality of TVCs 530. Each TVC 530 is a discrete TVC annularly around a corresponding steam injector 522, and the plurality of TVCs 530 are circumferentially spaced around the combustor 500. For example, the plurality of TVCs 530 include a first TVC 530a and a second TVC 530b. Each TVC 530 includes one or more walls 532, 536 (collectively referred to as the walls of each TVC 530). Specifically, each TVC 530 is composed of a first wall 532, a second wall ( Figure 5 The TVC 530 is defined by a first wall 536 (not shown in the view of FIG. 5 ) and a third wall 536. The wall of each TVC 530 includes a generally circular cross-section, so that each TVC 530 includes a generally circular cross-section (eg, each TVC 520 is cylindrical).

[0067] Each TVC 530 has a corresponding fuel injector 518 and a corresponding steam injector 522 associated therewith. Each TVC 530 includes a plurality of TVC air holes 542 disposed through the first wall 532. The corresponding fuel injector 518 is cylindrical, wherein the plurality of fuel injection holes 520 are disposed circumferentially about the corresponding fuel injector 518. The corresponding fuel injector 518 of each TVC 530 injects fuel radially outward through the plurality of fuel injection holes 520 to generate a fuel flow 550. The corresponding steam injector 522 is cylindrical, wherein one or more steam injection holes 524 are disposed axially through the corresponding steam injector 522. The corresponding steam injector 522 injects steam axially rearward to generate a steam flow 560. In some embodiments, the one or more steam injection holes 524 include one or more steam injection holes 524 positioned to radially inject steam 69 into the first TVC 230a and the second TVC 230b.

[0068] Each TVC 530 is cylindrically shaped around the fuel injector 518 and the steam injector 522. The combustor 500 includes an outer liner and an inner liner ( Figure 5 ), similar to Figure 2 The outer lining 204 and the inner lining 206. For example, Figure 5 The outer liner and the inner liner in the embodiment are annular about the longitudinal centerline axis of the combustor 500.

[0069] Figure 6 FIG. 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 2The 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 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 600 includes components that are different from Figure 2 The combustor 600 does not include an annular dome 210, a plurality of mixing assemblies 212, and a plurality of TVCs 230. The combustor 600 does not include an annular dome 610, a plurality of mixing assemblies 612, and a plurality of TVCs 630. Figure 2 Steam injector 222 steam injector.

[0070] Each of the plurality of mixing assemblies 612 includes a main mixer 614 and a plurality of fuel injectors 618. The plurality of fuel injectors 618 include a first fuel injector 618a and a second fuel injector 618b. The first fuel injector 618a and the second fuel injector 618b extend axially, as described in further detail below. Each of the plurality of fuel injectors 618 includes one or more fuel injection holes 620 for injecting fuel 67 therethrough.

[0071] Each of the plurality of TVCs 630 defines a combustion zone 631. The plurality of TVCs 630 includes a first TVC 630a and a second TVC 630b. Each of the plurality of TVCs 630 is defined by one or more walls 632, 634, 636, 638 (collectively referred to as walls of the TVC 630). Specifically, each of the plurality of TVCs 630 is defined by a first wall 632, a second wall 634, a third wall 636, and a fourth wall 638. The walls of each of the plurality of TVCs 630 are connected to the first wall 632, the second wall 634, the third wall 636, and the fourth wall 638. Figure 2 The walls of each of the plurality of TVCs 230 of the embodiment are substantially similar. However, the fourth wall 638 extends axially from the first wall 632 to a TVC opening 640 defined between the fourth wall 638 and the outer liner 204 or the inner liner 206. The fourth walls 638 of each of the first TVC 630a and the second TVC 630b are spaced apart from each other such that a radial gap 641 is defined between the fourth wall 638 of the first TVC 630a and the fourth wall 638 of the second TVC 630b. The fourth wall 638 of the first TVC 630a and the fourth wall 638 of the second TVC 630b are coupled at the axial rearward end by a bushing extension 643 extending from the axial rearward end of the fourth wall 638 of the first TVC 630a to the axial rearward end of the fourth wall 638 of the second TVC 630b. The first fuel injector 618a is disposed through the first wall 632 of the first TVC 630a, and the second fuel injector 618b is disposed through the first wall 632 of the second TVC 630b.

[0072] Burner 600 with Figure 2The combustor 200 of the embodiment of the present invention operates substantially similarly. A plurality of fuel injectors 618 inject fuel 67 through one or more fuel injection holes 620 and into each corresponding TVC 630 to generate a fuel flow 650 within each of the plurality of TVCs 630. The fuel flow 650 is mixed with the compressed air flow 252 through the vortex 654 to generate a fuel-air mixture. The fuel-air mixture is ignited and generates combustion gases 666 within each of the plurality of TVCs 630. Each of the plurality of TVCs 630 is operable to direct the combustion gases 666 through the TVC opening 640 and into the main chamber 202. At the main chamber 202, the combustion gases 666 are mixed with the second steam flow 262 to generate a steam-combustion gas mixture 670, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0073] 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 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 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 700 includes components that are different from Figure 2 The combustor 700 includes an annular dome 210, a plurality of mixing assemblies 212, and a plurality of TVCs 230. The combustor 700 does not include a steam injector, such as Figure 2 The steam injector 222 shown in FIG.

[0074] Each of the plurality of mixing assemblies 712 includes a main mixer 714 and a plurality of fuel injectors 718. The plurality of fuel injectors 718 include a first fuel injector 718a and a second fuel injector 718b. The first fuel injector 718a and the second fuel injector 718b extend radially, as described in further detail below. Each of the plurality of fuel injectors 718 includes one or more fuel injection holes 720 for injecting the fuel 67 therethrough.

[0075] Each of the plurality of TVCs 730 defines a combustion zone 731. The plurality of TVCs 730 include a first TVC 730a and a second TVC 730b. Each of the plurality of TVCs 730 is defined by one or more walls 732, 734, 736, 738 (collectively referred to as walls of the TVC 730). Specifically, each TVC 730 is defined by a first wall 732, a second wall 734, a third wall 736, and a fourth wall 738. The walls of each of the plurality of TVCs 730 are connected to the first wall 732, the second wall 734, the third wall 736, and the fourth wall 738. Figure 6 The walls of each of the plurality of TVCs 630 are substantially similar. For example, the fourth wall 738 extends axially from the first wall 732 to a TVC opening 740 defined between the fourth wall 738 and the outer liner 204 or the inner liner 206. The fourth walls 738 of each of the first TVC 730a and the second TVC 730b are spaced apart from each other such that a radial gap 741 is defined between the fourth wall 738 of the first TVC 730a and the fourth wall 738 of the second TVC 730b. The fourth wall 738 of the first TVC 730a and the fourth wall 738 of the second TVC 730b are coupled at the axial rearward end by a bushing extension 743 extending from the axial rearward end of the fourth wall 738 of the first TVC 730a to the axial rearward end of the fourth wall 738 of the second TVC 730b. The first fuel injector 718a is disposed through the third wall 736 of the first TVC 730a so that the first fuel injector 718a radially injects the fuel 67 into the first TVC 730a. The second fuel injector 718b is disposed through the third wall 736 of the second TVC 730b so that the second fuel injector 718b radially injects the fuel 67 into the second TVC 730b.

[0076] Burner 700 with Figure 2 The combustor 200 of the embodiment of the present invention operates substantially similarly. A plurality of fuel injectors 718 radially inject fuel 67 into each corresponding TVC 730 through one or more fuel injection holes 720 to generate a fuel flow 750 within each of the plurality of TVCs 730. The fuel flow 750 is mixed with the compressed air flow 252 through the vortex 754 to generate a fuel-air mixture. The fuel-air mixture is ignited and generates combustion gases 766 within each of the plurality of TVCs 730. Each of the plurality of TVCs 730 is operable to direct the combustion gases 766 through the TVC opening 740 and into the main chamber 202. At the main chamber 202, the combustion gases 766 are mixed with the second steam flow 262 to generate a steam-combustion gas mixture 770, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0077] Figure 8FIG. 8 is a schematic cross-sectional view of a combustor 800 of a turbine engine according to another embodiment, taken along the longitudinal centerline axis of the turbine engine. Figure 2 and Figure 6 The same reference numerals will be used for the parts of the burner 800 that are the same as or similar to the parts of the above-mentioned burners 200 and 600. The above description of these parts also applies to the present embodiment, and the detailed description of these parts is omitted here. The burner 800 has a different Figure 6 Multiple TVC 630 and multiple TVC 830.

[0078] Each of the plurality of TVCs 830 defines a combustion zone 831. The plurality of TVCs 830 includes a first TVC 830a and a second TVC 830b. Each of the plurality of TVCs 830 is defined by one or more walls 832, 834, 836, 838 (collectively referred to as walls of the TVC 830). Specifically, each of the plurality of TVCs 830 is defined by a first wall 832, a second wall 834, a third wall 836, and a fourth wall 838. The walls of each of the plurality of TVCs 830 are connected to the first wall 832, the second wall 834, the third wall 836, and the fourth wall 838. Figure 6 The walls of each of the plurality of TVCs 630 are substantially similar. The first fuel injector 618a is disposed through the first wall 832 of the first TVC 830a such that the first fuel injector 618a injects the fuel 67 axially rearward into the first TVC 830a. The second fuel injector 618b is disposed through the first wall 832 of the second TVC 830b such that the second fuel injector 618b injects the fuel 67 axially rearward into the second TVC 830b.

[0079] Steam systems (e.g. Figure 1 The steam system 90 also includes a plurality of steam injectors 822 disposed through the third wall 836 of each of the plurality of TVCs 830. For example, the plurality of steam injectors 822 include a first steam injector 822a disposed through the third wall 836 of the first TVC 830a and a second steam injector 822b disposed through the third wall 836 of the second TVC 830b. Each steam injector 822 includes one or more steam injection holes 824, so that each steam injector 822 radially injects steam 69 into a corresponding TVC 830, as further described below.

[0080] Burner 800 with Figure 6The burner 600 of the embodiment of the present invention operates substantially similarly. A plurality of steam injectors 822 radially inject steam 69 into each corresponding TVC 830 through one or more steam injection holes 824 to generate a first steam flow 860. The first steam flow 860 includes steam and air. A plurality of fuel injectors 618 inject fuel 67 through one or more fuel injection holes 620 and into each corresponding TVC 830 to generate a fuel flow 650 in each of the plurality of TVCs 830. The fuel flow 650 is mixed with the compressed air flow 252 and the first steam flow 860 through the vortex 854 to generate a fuel-air-steam mixture. The fuel-air-steam mixture is ignited and generates a first steam-combustion gas mixture 869 in each of the plurality of TVCs 830. Each of the plurality of TVCs 830 is operable to direct the first steam-combustion gas mixture 869 through the TVC opening 840 and into the main chamber 202. At the main chamber 202, the first steam-combustion gas mixture 869 is mixed with the second steam flow 262 to generate a second steam-combustion gas mixture 870, which is directed downstream to the HP turbine (eg, Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0081] The first steam flow 860 in each respective TVC 830 includes up to 30% (e.g., in the range of 0.0% to 30%) WAR, and the second steam flow 262 in the main chamber 202 includes up to 60% (e.g., in the range of 0.0% to 60%) WAR. In this manner, more steam 69 is injected into the main chamber 202 than the steam 69 injected into the plurality of TVCs 830. This configuration provides flame stability in the plurality of TVCs 830 while providing reduced emissions and reduced SFC. In some embodiments, steam 69 is injected into the plurality of TVCs 830 and no steam is injected through one or more liner steam holes 205.

[0082] Fig. 9 FIG. 9 is a schematic cross-sectional view of a combustor 900 of a turbine engine according to another embodiment, taken along the longitudinal centerline axis of the turbine engine. Figure 2 , Figure 6 and Figure 8 The same reference numerals will be used for the parts of the burner 900 that are the same as or similar to the parts of the burners 200, 600, 800 described above. The above description of these parts also applies to the present embodiment, and the detailed description of these parts is omitted here. The burner 900 has different Figure 2 , Figure 6 and Figure 8Multiple TVCs 230, 630, 830 and multiple TVCs 930.

[0083] Each of the plurality of TVCs 930 defines a combustion zone 931. The plurality of TVCs 930 includes a first TVC 930a and a second TVC 930b. Each of the plurality of TVCs 930 is defined by one or more walls 932, 934, 936, 938 (collectively referred to as walls of the TVC 930). Specifically, each of the plurality of TVCs 930 is defined by a first wall 932, a second wall 934, a third wall 936, and a fourth wall 938. The walls of each of the plurality of TVCs 930 are connected to the first wall 932, the second wall 934, the third wall 936, and the fourth wall 938. Figure 6 The walls of each of the plurality of TVCs 630 are substantially similar. The first fuel injector 618a is disposed through the first wall 932 of the first TVC 930a such that the first fuel injector 618a injects the fuel 67 axially rearward into the first TVC 933a. The second fuel injector 618b is disposed through the first wall 932 of the second TVC 930b such that the second fuel injector 618b injects the fuel 67 axially rearward into the second TVC 930b.

[0084] The burner 900 also includes one or more steam injectors 922 disposed through the third wall 936 of the first TVC 930a. The burner 900 does not include a second steam injector disposed through the second TVC 930b. The one or more steam injectors 922 include one or more steam injection holes 924 such that each steam injector 922 radially injects steam 69 into the first TVC 930a, as described in further detail below.

[0085] The burners 900 are respectively Figure 2 , Figure 6 and Figure 8The combustors 200, 600, 800 of the present invention operate substantially similarly. One or more steam injectors 922 radially inject steam 69 into the first TVC 930a through one or more steam injection holes 924 to generate a first steam flow 960. The first steam flow 960 includes steam and air. A plurality of fuel injectors 618 inject fuel 67 through one or more fuel injection holes 620 and into each corresponding TVC 930 to generate a fuel flow 650 in each of the plurality of TVCs 930. In the first TVC 930a, the fuel flow 650 is mixed with the compressed air flow 252 and the first steam flow 960 through the first vortex 954a to generate a fuel-air-steam mixture in the first TVC 930a. The fuel-air-steam mixture is ignited and generates a first steam-combustion gas mixture 969 in each of the first TVC 930a. Within the second TVC 930b, the fuel flow 650 from the second fuel injector 618b is mixed with the compressed air flow 252 through the second vortex 954b to generate a fuel-air mixture in the second TVC 930b. The fuel-air mixture is ignited and generates combustion gases 66 within the second TVC 930b. The first TVC 930a is operable to direct the first steam-combustion gas mixture 969 through the TVC opening 940 and into the main chamber 202. The second TVC 930b is operable to direct the combustion gases 66 from the second TVC 930b through the TVC opening 940 and into the main chamber 202. At the main chamber 202, the first steam-combustion gas mixture 969 is mixed with the combustion gases 66 from the second TVC 930b and with the second steam flow 262 to generate a second steam-combustion gas mixture 970, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0086] Fig.10 FIG. 1 is a schematic cross-sectional view of a combustor 1000 of a turbine engine according to another embodiment, taken along a longitudinal centerline axis of the turbine engine. Figure 2 The same reference numerals will be used for the components of the burner 1000 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 1000 includes components that are different from Figure 2 The combustor 1000 includes an annular dome 210, a plurality of mixing assemblies 212, and a plurality of TVCs 230. The combustor 1000 does not include a steam injector, such as Figure 2 The steam injector 222 shown in FIG.

[0087] Each of the plurality of mixing assemblies 1012 includes a main mixer 1014 and a plurality of fuel injectors 1018. The plurality of fuel injectors 1018 extend axially, as described in further detail below. Each of the plurality of fuel injectors 1018 includes one or more fuel injection holes 1020 for injecting fuel 67 therethrough. For example, each of the plurality of fuel injectors 1018 includes one or more first fuel injection holes 1020a and one or more second fuel injection holes 1020b for radially injecting fuel 67.

[0088] Each of the plurality of TVCs 1030 defines a combustion zone 1031. The plurality of TVCs 1030 include a first TVC 1030a and a second TVC 1030b. Each of the plurality of TVCs 1030 is defined by one or more walls 1032, 1034, 1036, 1038 (collectively referred to as walls of the TVC 1030). Specifically, each of the plurality of TVCs 1030 is defined by a first wall 1032, a second wall 1034, a third wall 1036, and a fourth wall 1038. The walls of each of the plurality of TVCs 1030 are connected to Figure 2 The walls of each of the plurality of TVCs 230 of the embodiment are substantially similar. However, the fourth wall 1038 extends axially from the first wall 1032 to a TVC opening 1040 defined between the fourth wall 1038 and the outer liner 204 or the inner liner 206. The fourth walls 1038 of each of the first TVC 1030a and the second TVC 1030b are spaced apart from each other such that a radial gap 1041 is defined between the fourth wall 1038 of the first TVC 1030a and the fourth wall 1038 of the second TVC 1030b. The fourth wall 1038 of the first TVC 1030a and the fourth wall 1038 of the second TVC 1030b are coupled at the axial rearward end by a bushing extension 1043 extending from the axial rearward end of the fourth wall 1038 of the first TVC 1030a to the axial rearward end of the fourth wall 1038 of the second TVC 1030b. A plurality of fuel injectors 1018 are disposed through the radial gap 1041. One or more fuel injection holes 1020 extend through the fourth wall 1038 of each TVC 1030. For example, one or more first fuel injection holes 1020a extend through the fourth wall 1038 of the first TVC 1030a, such that the plurality of fuel injectors 1018 inject fuel 67 into the first TVC 1030a through the one or more first fuel injection holes 1020a. One or more second fuel injection holes 1020b extend through the fourth wall 1038 of the second TVC 1030b, such that the plurality of fuel injectors 1018 inject fuel 67 into the second TVC 1030b through the one or more second fuel injection holes 1020b.

[0089] Burner 1000 with Figure 2 The combustor 200 of the embodiment of the present invention operates substantially similarly. A plurality of fuel injectors 1018 inject fuel 67 through one or more fuel injection holes 1020 and into each corresponding TVC 1030 to generate a fuel flow 1050 within each of the plurality of TVCs 1030. The fuel flow 1050 is mixed with the compressed air flow 252 through the vortex 1054 to generate a fuel-air mixture. The fuel-air mixture is ignited and generates combustion gases 1066 within each of the plurality of TVCs 1030. Each of the plurality of TVCs 1030 is operable to direct the combustion gases 1066 through the TVC opening 1040 and into the main chamber 202. At the main chamber 202, the combustion gases 1066 are mixed with the second steam flow 262 to generate a steam-combustion gas mixture 1070, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0090] 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. Fig.10 The 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 1000 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 different Fig.10 Multiple mixing components 1012 and multiple mixing components 1112.

[0091] Each of the plurality of mixing assemblies 1112 includes a main mixer 1114 and a plurality of fuel injectors 1118. The plurality of fuel injectors 1118 extend axially, as described in further detail below. Each of the plurality of fuel injectors 1118 includes one or more fuel injection holes 1120 for injecting fuel 67 therethrough. For example, each of the plurality of fuel injectors 1118 includes one or more first fuel injection holes 1120a and one or more second fuel injection holes 1120b for radially injecting fuel 67, and one or more third fuel injection holes 1120c for axially injecting fuel 67, as described in further detail below.

[0092] A plurality of fuel injectors 1118 are disposed through the radial gap 1041. One or more first fuel injection holes 1120a extend through the fourth wall 1038 of the first TVC 1030a, such that the plurality of fuel injectors 1118 inject fuel 67 into the first TVC 1030a through the one or more first fuel injection holes 1120a. One or more second fuel injection holes 1120b extend through the fourth wall 1038 of the second TVC 1030b, such that the plurality of fuel injectors 1118 inject fuel 67 into the second TVC 1030b through the one or more second fuel injection holes 1120b. One or more third fuel injection holes 1120c extend through the bushing extension 1143, such that the plurality of fuel injectors 1118 inject fuel 67 into the main chamber 202 through the one or more third fuel injection holes 1120c, as described in further detail below.

[0093] Burner 1100 with Fig.10 The combustor 1000 of the present invention operates substantially similarly. A plurality of fuel injectors 1118 inject fuel 67 through one or more first fuel injection holes 1120a and one or more second fuel injection holes 1120b and into each corresponding TVC 1030 to generate a first fuel flow 1150 in each TVC 1030. The first fuel flow 1150 is mixed with the compressed air flow 252 through the vortex 1054 to generate a fuel-air mixture. The fuel-air mixture is ignited and generates a first combustion gas 1166a in each of the plurality of TVCs 1030. Each of the plurality of TVCs 1030 is operable to direct the first combustion gas 1166a through the TVC opening 1040 and into the main chamber 202. The plurality of fuel injectors 1118 inject fuel 67 into the main chamber 202 through one or more third fuel injection holes 1120c to generate a second fuel flow 1151. The second fuel flow 1151 is mixed with the compressed air 65 in the main chamber 202 (e.g., introduced through one or more liner steam holes 205) to generate a second fuel-air mixture, which is ignited to form a second flame, which burns within the main chamber 202 and generates second combustion gases 1166b. For example, the second steam flow 262 includes a mixture of steam 69 and compressed air 65. In some embodiments, a plurality of fuel injectors 1118 inject the compressed air 65 into the main chamber 202. At the main chamber 202, the first combustion gas 1166a from the plurality of TVCs 1030 is mixed with the second combustion gas 1166b in the main chamber 202 and with the second steam flow 262 to generate a steam-combustion gas mixture 1170, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0094] 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. Fig.10 The same reference numerals will be used for the components of the burner 1200 that are the same as or similar to the components of the burner 1000 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 1200 includes a different Fig.10 The combustor 1200 includes an outer liner 204 and an inner liner 206, an annular dome 1010, a plurality of mixing assemblies 1012, and a plurality of TVCs 1030. The outer liner 1204 and the inner liner 1206 do not include steam holes disposed therethrough. The combustor 1200 includes a main chamber 1202 defined by the outer liner 1204 and the inner liner 1206. The main chamber 1202 extends to a combustor outlet 1211.

[0095] Each of the plurality of mixing assemblies 1212 includes a main mixer 1214 and a plurality of fuel injectors 1218. The plurality of fuel injectors 1218 extend axially, as described in further detail below. Each of the plurality of fuel injectors 1218 includes one or more fuel injection holes 1220 for injecting fuel 67 therethrough. The plurality of fuel injectors 1218 include a first fuel injector 1218a and a second fuel injector 1218b. A steam system (e.g., Figure 1 The steam system 90) includes one or more steam injectors 1222. The one or more steam injectors 1222 include one or more steam injection holes 1224 for injecting steam 69 therethrough.

[0096] Each of the plurality of TVCs 1230 defines a combustion zone 1231. The plurality of TVCs 1230 includes a first TVC 1230a and a second TVC 1230b. Each of the plurality of TVCs 1230 is defined by one or more walls 1232, 1234, 1236, 1238 (collectively referred to as walls of the TVC 1230). Specifically, each of the plurality of TVCs 1230 is defined by a first wall 1232, a second wall 1234, a third wall 1236, and a fourth wall 1238. The walls of each of the plurality of TVCs 1230 are connected to the first wall 1232, the second wall 1234, the third wall 1236, and the fourth wall 1238. Fig.10The walls of each of the plurality of TVCs 1030 are substantially similar. For example, the fourth wall 1238 extends axially from the first wall 1232 to a TVC opening 1240 defined between the fourth wall 1232 and the outer liner 1204 or the inner liner 1206. The fourth walls 1238 of each of the first TVC 1230a and the second TVC 1230b are spaced apart from each other such that a radial gap 1241 is defined between the fourth wall 1238 of the first TVC 1230a and the fourth wall 1238 of the second TVC 1230b. The fourth wall 1238 of the first TVC 1230a and the fourth wall 1238 of the second TVC 1230b are coupled at the axial rearward end by a bushing extension 1243 extending from the axial rearward end of the fourth wall 1238 of the first TVC 1230a to the axial rearward end of the fourth wall 1238 of the second TVC 1230b.

[0097] A plurality of fuel injectors 1218 are disposed through the first wall 1232 of each of the plurality of TVCs 1230. For example, a first fuel injector 1218a extends through the first wall 1232 of the first TVC 1230a such that the first fuel injector 1218a injects the fuel 67 axially rearwardly into the first TVC 1230a through one or more fuel injection holes 1220. A second fuel injector 1218b extends through the first wall 1232 of the second TVC 1230b such that the second fuel injector 1218b injects the fuel 67 axially rearwardly into the second TVC 1230b through one or more fuel injection holes 1220.

[0098] One or more steam injectors 1222 extend through radial gap 1241, and one or more steam injection holes 1224 extend through liner extension 1243. In this manner, one or more steam injectors 1222 inject steam 69 axially rearwardly into main chamber 202, as described in further detail below.

[0099] Burner 1200 with Fig.10The combustor 1000 of the embodiment of the present invention operates substantially similarly. A plurality of fuel injectors 1218 inject fuel 67 axially rearward into each corresponding TVC 1230 to generate a fuel flow 1250 within each of the plurality of TVCs 1230. The fuel flow 1250 is mixed with the compressed air flow 252 through the vortex 1254 to generate a fuel-air mixture. The fuel-air mixture is ignited and generates combustion gases 1266 within each of the plurality of TVCs 1230. Each of the plurality of TVCs 1230 is operable to direct the combustion gases 1266 through the TVC opening 1240 and into the main chamber 202. One or more steam injectors 1222 inject steam 69 axially rearward into the main chamber 202 through one or more steam injection holes 1224 to generate a steam flow 1260. At the main chamber 202, combustion gases 1266 from the plurality of TVCs 1230 are mixed with a steam flow 1260 to generate a steam-combustion gas mixture 1270 which is directed downstream to a HP turbine (eg, Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0100] Fig.13 FIG. 1 is a schematic cross-sectional view of a combustor 1300 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Fig.12 The same reference numerals will be used for the components of the burner 1300 that are the same as or similar to the components of the burner 1200 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 1300 includes components that are different from Fig.12 Multiple TVCs 1230 and one or more steam injectors 1222 and multiple TVCs 1330 and one or more steam injectors 1322.

[0101] Each of the plurality of TVCs 1330 defines a combustion zone 1331. The plurality of TVCs 1330 includes a first TVC 1330a and a second TVC 1330b. Each of the plurality of TVCs 1330 is defined by one or more walls 1332, 1334, 1336, 1338 (collectively referred to as walls of the TVC 1330). Specifically, each of the plurality of TVCs 1330 is defined by a first wall 1332, a second wall 1334, a third wall 1336, and a fourth wall 1338. The walls of each of the plurality of TVCs 1330 are connected to the first wall 1332, the second wall 1334, the third wall 1336, and the fourth wall 1338. Fig.12The walls of each of the plurality of TVCs 1230 are substantially similar. For example, the fourth wall 1338 extends axially from the first wall 1332 to a TVC opening 1340 defined between the fourth wall 1338 and the outer liner 1204 or the inner liner 1206. The fourth walls 1338 of each of the first TVC 1330a and the second TVC 1330b are spaced apart from each other such that a radial gap 1341 is defined between the fourth wall 1338 of the first TVC 1330a and the fourth wall 1338 of the second TVC 1330b. The fourth wall 1338 of the first TVC 1330a and the fourth wall 1338 of the second TVC 1330b are coupled at the axial rearward end by a bushing extension 1343 extending from the axial rearward end of the fourth wall 1338 of the first TVC 1330a to the axial rearward end of the fourth wall 1338 of the second TVC 1330b.

[0102] One or more steam injectors 1322 extend through the radial gap 1341 and include one or more steam injection holes 1324. The one or more steam injection holes 1324 include one or more first steam injection holes 1324a extending through the fourth wall 1338 of the first TVC 1330a, so that the one or more steam injectors 1322 inject steam 69 radially and axially backward into the first TVC 1330a. The one or more steam injection holes 1324 include one or more second steam injection holes 1324b extending through the fourth wall 1338 of the second TVC 1330b, so that the one or more steam injectors 1322 inject steam 69 radially and axially backward into the second TVC 1330b. The one or more steam injection holes 1324 include one or more third steam injection holes 1324c extending through the bushing extension 1343, so that the one or more steam injectors 1322 inject steam 69 axially backward into the main chamber 202.

[0103] Burner 1300 with Fig.12The burner 1200 of the embodiment of the present invention operates substantially similarly. One or more steam injectors 1322 inject steam 69 into each corresponding TVC 1330 through one or more first steam injection holes 1324a and one or more second steam injection holes 1324b to generate a first steam flow 1359 in each corresponding TVC 1330. The first steam flow 1359 is mixed with the fuel flow 1250 through the vortex 1354 at the combustion zone 1331 within each of the plurality of TVCs 1330 to generate a fuel-air-steam mixture. The fuel-air-steam mixture is ignited and generates a first steam-combustion gas mixture 1369. Each of the plurality of TVCs 1330 is operable to direct the first steam-combustion gas mixture 1369 through the TVC opening 1340 and into the main chamber 1202. One or more steam injectors 1322 inject steam 69 axially into the main chamber 1202 through one or more third steam injection holes 1324c to generate a second steam flow 1360. At the main chamber 1202, the second steam flow 1360 is mixed with the first steam-combustion gas mixture 1369 to generate a second steam-combustion gas mixture 1370, which is directed downstream to the HP turbine (eg, Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0104] Fig.14 FIG. 1 is a schematic cross-sectional view of a combustor 1400 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Fig.12 The same reference numerals will be used for the components of the burner 1400 that are the same as or similar to the components of the burner 1200 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 1400 includes a different Fig.12 The outer liner 1204 and the inner liner 1206 are provided with an outer liner 1404 and an inner liner 1406. Specifically, the outer liner 1404 and the inner liner 1406 include one or more liner steam holes 1405 extending therethrough. The combustor 1400 includes a main chamber 1402 defined by the outer liner 1404 and the inner liner 1406. The main chamber 1402 extends to a combustor outlet 1411.

[0105] Burner 1400 with Fig.12The combustor 1200 of FIG. 1200 operates substantially similarly. One or more steam injectors 1222 inject steam 69 axially into the main chamber 1402 to generate a first steam flow 1460. One or more liner steam holes 1405 are operable to direct steam 69 into the main chamber 1402 to generate a second steam flow 1462. At the main chamber 1402, combustion gases 1266 from the plurality of TVCs 1230 mix with the first steam flow 1460 and the second steam flow 1462 to generate a steam-combustion gas mixture 1470, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0106] Fig.15 FIG. 1 is a schematic cross-sectional view of a combustor 1500 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Combustor 1500 is similar to Figure 2 The same reference numerals will be used for components of the burner 1500 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 a detailed description of these components is omitted here. The burner 1500 includes a main chamber 1502, an outer liner 1504, an inner liner 1506, a plurality of mixing assemblies 1512, a plurality of steam injectors 1522, and a plurality of TVCs 1530, and the outer liner 1504, the inner liner 1506, the plurality of mixing assemblies 1512, the plurality of steam injectors 1522, and the plurality of TVCs 1530 are different from Figure 2 The outer liner 204, the inner liner 206, the plurality of mixing assemblies 212, the one or more steam injectors 222, and the plurality of TVCs 230.

[0107] The outer liner 1504 and the inner liner 1506 extend generally axially and do not include steam holes therethrough. The burner 1500 includes an annular dome 1510 coupled to the outer liner 1504 and the inner liner 1506. The main chamber 1502 extends to a burner outlet 1511. The diffuser section 1544 is defined between the outer burner casing 208 and the inner burner casing 209 upstream of the annular dome 1510. Each of the plurality of mixing assemblies 1512 includes a mixer 1514 and a fuel injector 1518. For example, the burner 1500 includes a first fuel injector 1518a and a second fuel injector 1518b. Each fuel injector 1518 includes one or more fuel injection holes 1520 for injecting fuel 67 therethrough. A plurality of steam injectors 1522 include a first steam injector 1522a, a second steam injector 1522b, and a third steam injector 1522c. Each of the plurality of steam injectors 1522 includes one or more steam injection holes 1524 for injecting steam 69 and compressed air 65 therethrough. A first steam injector 1522a is disposed through the annular dome 1510 to inject steam 69 into the main chamber 1502, as described in further detail below. Each of the plurality of steam injectors 1522 also receives a portion of the compressed air 65 and injects the portion of the compressed air 65, as described in further detail below. For example, each of the plurality of steam injectors 1522 can be coupled to a compressed air bleed flow path that injects the portion of the compressed air 65 from the HP compressor 24 ( Figure 1 ) or diffuser section 1544 is directed to each of the multiple steam injectors 1522.

[0108] The plurality of TVCs 1530 include a first TVC 1530a and a second TVC 1530b. Each of the plurality of TVCs 1530 is defined by one or more walls 1532, 1534, 1536 (collectively referred to as walls of the TVC 1530). Specifically, each of the plurality of TVCs 1530 is defined by a first wall 1532, a second wall 1534, and a third wall 1536. Each of the plurality of TVCs 1530 also includes a TVC opening 1540 defined in the outer liner 1504 or the inner liner 1506. The plurality of TVCs 1530 do not include a fourth wall. Instead, the plurality of TVCs 1530 are positioned axially rearward of the annular dome 1510, so that the plurality of TVCs 1530 are located downstream of the region of the annular dome 1510. Each of the plurality of TVCs 1530 also defines a combustion zone 1531 therein.

[0109] The first fuel injector 1518a extends through the first wall 1532 of the first TVC 1530a so that the first fuel injector 1518a injects the fuel 67 axially rearward into the first TVC 1530a. The second fuel injector 1518b extends through the first wall 1532 of the second TVC 1530b so that the second fuel injector 1518b injects the fuel 67 axially rearward into the second TVC 1530b. The second steam injector 1522b extends through the second wall 1534 of the first TVC 1530a so that the second steam injector 1522b injects the steam 69 and the compressed air 65 axially forward into the first TVC 1530a. The third steam injector 1522c extends through the second wall 1534 of the second TVC 1530b so that the third steam injector 1522c injects the steam 69 and the compressed air 65 axially forward into the second TVC 1530b.

[0110] In operation, the first steam injector 1522a injects steam 69 and compressed air 65 into the main chamber 1502 to generate a first steam-air flow 1560. The first steam injector 1522a injects the first steam-air flow 1560 axially forward of the plurality of TVCs 1530. The second steam injector 1522b and the third steam injector 1522c inject steam 69 and compressed air 65 axially forward into the respective TVCs 1530 to generate a second steam-air flow 1562 within each of the plurality of TVCs 1530. The plurality of TVCs 1530 swirl the second steam-air flow 1562 to generate a vortex 1554 within each respective TVC 1530. The fuel injector 1518 injects fuel 67 axially forward into the respective TVCs 1530 to generate a fuel flow 1550. The fuel flow 1550 is mixed with the second steam-air flow 1562 at the vortex 1554 to generate a fuel-steam-air mixture, which is ignited to generate a first steam-combustion gas mixture 1569. The plurality of TVCs 1530 are operable to direct the first steam-combustion gas mixture 1569 through the TVC openings 1540 and into the main chamber 1502. At the main chamber 1502, the first steam-air flow 1560 is directed axially aft, and the first steam-combustion gas mixture 1569 from two of the plurality of TVCs 1530 is directed downstream into the main chamber 1502 and mixed with the first steam-air flow 1560 to generate a second steam-combustion gas mixture 1570, which is directed downstream to the HP turbine (e.g., Figure 1The total amount of steam 69 injected into the main chamber 1502 comprises up to 30% WAR. In some embodiments, WAR varies between 0.0% and 30% based on the operating conditions of the turbine engine (e.g., start-up, idle, taxi, take-off, climb, cruise, descent), similar to the above detailed description. Figure 2 Embodiment of the invention.

[0111] Fig.16 FIG. 1 is a schematic cross-sectional view of a combustor 1600 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Fig.15 The same reference numerals will be used for the components of the burner 1600 that are the same as or similar to the components of the burner 1500 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 1600 includes components that are different from Fig.15 Multiple steam injectors 1522 and multiple TVCs 1530, multiple steam injectors 1622 and multiple TVCs 1630.

[0112] The plurality of steam injectors 1622 include a first steam injector 1622a, a second steam injector 1622b, and a third steam injector 1622c. Each of the plurality of steam injectors 1622 includes one or more steam injection holes 1624 for injecting steam 69 therethrough. Fig.16 In the embodiment of the present invention, the plurality of steam injectors 1622 do not inject compressed air 65. Instead, the compressed air 65 is directed from the diffuser section 1544 and enters the plurality of TVCs 1630, as further described below. The first steam injector 1622a is disposed through the annular dome 1510 to inject steam 69 into the main chamber 1502.

[0113] Each of the plurality of TVCs 1630 defines a combustion zone 1631. The plurality of TVCs 1630 include a first TVC 1630a and a second TVC 1630b. Each of the plurality of TVCs 1630 is defined by one or more walls 1632, 1634, 1636 (collectively referred to as walls of the TVC 1630). Specifically, each of the plurality of TVCs 1630 is defined by a first wall 1632, a second wall 1634, and a third wall 1636. Each TVC 1630 also includes a TVC opening 1640 defined in the outer liner 1504 or the inner liner 1506. Each of the plurality of TVCs 1630 includes one or more TVC air holes 1642 disposed through the second wall 1634, the one or more TVC air holes 1642 being operable to direct the compressed air 65 therethrough.

[0114] In operation, the first steam injector 1622a injects steam 69 into the main chamber 1502 to generate a first steam flow 1660. The second steam injector 1622b and the third steam injector 1622c inject steam 69 axially forward into the corresponding TVC 1630 to generate a second steam flow 1662. One or more TVC air holes 1642 are operable to direct compressed air 65 into each of the plurality of TVCs 1630 to generate a compressed air flow 1652 within each TVC 1630. The fuel injector 1518 injects fuel 67 axially forward into the corresponding TVC 1530 to generate a fuel flow 1550. The fuel flow 1550 mixes with the compressed air flow 1652 and the second steam flow 1662 at the vortex 1654 to generate a fuel-air-steam mixture, which is ignited to generate a first steam-combustion gas mixture 1669. The plurality of TVCs 1630 are operable to direct a first steam-combustion gas mixture 1669 through TVC openings 1640 and into the main chamber 1502. At the main chamber 1502, the first steam flow 1660 is directed axially aft, and the first steam-combustion gas mixture 1669 from two of the plurality of TVCs 1630 is directed downstream into the main chamber 1502 and mixed with the first steam flow 1660 to generate a second steam-combustion gas mixture 1670, which is directed downstream to the HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0115] Fig.17 FIG. 1 is a schematic cross-sectional view of a combustor 1700 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Combustor 1700 is similar to Figure 2 The same reference numerals will be used for components of the burner 1700 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 a detailed description of these components is omitted here. The burner 1700 includes a main chamber 1702, an outer liner 1704, an inner liner 1706, a plurality of mixing assemblies 1712, a plurality of steam injectors 1722, and one or more TVCs 1730, and the outer liner 1704, the inner liner 1706, the plurality of mixing assemblies 1712, the plurality of steam injectors 1722, and the one or more TVCs 1730 are different from Figure 2 The outer liner 204, the inner liner 206, the plurality of mixing assemblies 212, the one or more steam injectors 222, and the plurality of TVCs 230.

[0116] The outer liner 1704 and the inner liner 1706 extend generally axially and do not include steam holes therethrough. The combustor 1700 includes an annular dome 1710 coupled to the outer liner 1704 and the inner liner 1706. The main chamber 1702 extends to a combustor outlet 1711. A diffuser section 1744 is defined between the outer combustor casing 208 and the inner combustor casing 209 upstream of the annular dome 1710. Each of the plurality of mixing assemblies 1712 includes a mixer 1714 and a fuel injector 1718. Each fuel injector 1718 includes one or more fuel injection holes 1720 for injecting fuel 67 therethrough. The plurality of fuel injectors 1718 are positioned only on the outer liner 1704 and not on the inner liner 1706. The plurality of steam injectors 1722 include a first steam injector 1722a and a second steam injector 1722b. Each of the plurality of steam injectors 1722 includes one or more steam injection holes 1724 for injecting steam 69 and compressed air 65 therethrough. A first steam injector 1722a is disposed through the annular dome 1710 to inject steam 69 into the main chamber 1702, as described in further detail below. Each of the plurality of steam injectors 1722 also receives a portion of the compressed air 65 and injects the portion of the compressed air 65, as described in further detail below. For example, each of the plurality of steam injectors 1722 can be coupled to a compressed air bleed flow path that injects steam 69 from the HP compressor 24 ( Figure 1 ) or diffuser section 1744 is directed to each of the plurality of steam injectors 1722.

[0117] The one or more TVCs 1730 are each defined by one or more walls 1732, 1734, 1736 (collectively referred to as walls of the TVC 1730). Specifically, each of the one or more TVCs 1730 is defined by a first wall 1732, a second wall 1734, and a third wall 1736. Fig.17 , one or more TVCs 1730 extend from the outer liner 1704. In some embodiments, one or more TVCs 1730 extend from the inner liner 1706. One or more TVCs 1730 also include a TVC opening 1740 defined in the outer liner 1704. One or more TVCs 1730 do not include a fourth wall. Instead, one or more TVCs 1730 are positioned axially rearward of the annular dome 1710 such that one or more TVCs 1730 are located downstream of the region of the annular dome 1710. One or more TVCs 1730 also define a combustion zone 1731 therein.

[0118] A plurality of fuel injectors 1718 extend through a first wall 1732 of the one or more TVCs 1730 such that the plurality of fuel injectors 1718 inject fuel 67 axially rearwardly into the one or more TVCs 1730. A second steam injector 1722b extends through a second wall 1734 of the one or more TVCs 1730 such that the second steam injector 1722b injects steam 69 and compressed air 65 axially forwardly into the one or more TVCs 1730.

[0119] In operation, the first steam injector 1722a injects steam 69 and compressed air 65 into the main chamber 1702 to generate a first steam-air flow 1760. The first steam injector 1722a injects the first steam-air flow 1760 axially forward of the one or more TVCs 1730. The second steam injector 1722b injects steam 69 and compressed air 65 axially forward into the one or more TVCs 1730 to generate a second steam-air flow 1762 within the one or more TVCs 1730. The one or more TVCs 1730 swirl the second steam-air flow 1762 to generate a vortex 1754 within the one or more TVCs 1730. The plurality of fuel injectors 1518 inject fuel 67 axially forward into the one or more TVCs 1730 to generate a fuel flow 1750. The fuel flow 1750 mixes with the second steam-air flow 1762 at the vortex 1754 to generate a first steam-combustion gas mixture 1769. One or more TVCs 1730 are operable to direct a first steam-combustion gas mixture 1769 through TVC openings 1740 and into main chamber 1702. At main chamber 1702, first steam-air flow 1760 is directed axially aft, and first steam-combustion gas mixture 1769 from one or more TVCs 1730 is directed downstream into main chamber 1702 and mixed with first steam-air flow 1760 to generate second steam-combustion gas mixture 1770, which is directed downstream to a HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0120] Fig.18 FIG. 1 is a schematic cross-sectional view of a combustor 1800 of a turbine engine taken along a longitudinal centerline axis of the turbine engine according to another embodiment. Fig.17 The same reference numerals will be used for the components of the burner 1800 that are the same as or similar to the components of the burner 1700 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 1800 includes components that are different from Fig.17Multiple steam injectors 1722 and one or more TVCs 1730 Multiple steam injectors 1822 and one or more TVCs 1830.

[0121] The plurality of steam injectors 1822 include a first steam injector 1822a and a second steam injector 1822b. Each of the plurality of steam injectors 1822 includes one or more steam injection holes 1824 for injecting steam 69 therethrough. Fig.18 In the embodiment of the present invention, the plurality of steam injectors 1822 do not inject compressed air 65. Instead, the compressed air 65 is directed from the diffuser section 1744 and enters one or more TVCs 1830, as further described below. The first steam injector 1822a is disposed through the annular dome 1710 to inject steam 69 into the main chamber 1702.

[0122] One or more TVCs 1830 define a combustion zone 1831. One or more TVCs 1830 are each defined by one or more walls 1832, 1834, 1836 (collectively, walls of the TVC 1830). Specifically, one or more TVCs 1830 are defined by a first wall 1832, a second wall 1834, and a third wall 1836. Each of the one or more TVCs 1830 also includes a TVC opening 1840 defined in the outer liner 1704 or the inner liner 1706. Each of the one or more TVCs 1830 includes one or more TVC air holes 1842 disposed through the second wall 1834, and the one or more TVC air holes 1842 are operable to direct the compressed air 65 therethrough.

[0123] In operation, the first steam injector 1822a injects steam 69 into the main chamber 1702 to generate a first steam flow 1860. The second steam injector 1822b injects steam 69 axially forward into the one or more TVCs 1830 to generate a second steam flow 1862. The one or more TVC air holes 1842 are operable to direct the compressed air 65 into the one or more TVCs 1830 to generate a compressed air flow 1852 within the one or more TVCs 1830. The fuel injector 1718 injects fuel 67 axially forward into the one or more TVCs 1830 to generate a fuel flow 1750. The fuel flow 1750 mixes with the compressed air flow 1852 at the vortex 1854 to generate a fuel-air mixture, which is ignited to generate a first steam-combustion gas mixture 1869. One or more TVCs 1830 are operable to direct a first steam-combustion gas mixture 1869 through TVC openings 1840 and into main chamber 1702. At main chamber 1702, first steam flow 1860 is directed axially aft, and first steam-combustion gas mixture 1869 from one or more TVCs 1830 is directed downstream into main chamber 1702 and mixed with first steam flow 1860 to generate second steam-combustion gas mixture 1870, which is directed downstream to a HP turbine (e.g., Figure 1 The first stage turbine nozzle of the HP turbine 28).

[0124] Therefore, the embodiment of the present disclosure described in detail herein provides a burner with a main chamber and multiple TVCs, wherein multiple TVCs are burned and steam is injected into the main chamber. This configuration provides flame stability in the burner under different operating conditions (e.g., low power, medium power, and high power). Compared with a burner without the benefits of the present disclosure, an embodiment of the present disclosure 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 can cause the flame to extinguish, but the present disclosure provides injecting most of the steam into the main chamber away from multiple TVCs to avoid the flame extinguishing in multiple TVCs. Compared with a burner without the benefits of the present disclosure, this configuration of injecting steam into the main chamber and away from multiple TVCs enables a larger amount of steam to be injected into the burner. For example, the combustion in multiple TVCs and most of the steam entering the main chamber away from multiple TVCs (and downstream of multiple TVCs) prevents most of the steam from flowing near the flame in multiple TVCs. In this manner, the present disclosure allows for greater amounts of steam to be injected into the combustor while preventing steam from blocking the flames within multiple TVCs, thereby reducing emissions (e.g., NO xemissions, nvPM emissions, CO, and noise) and reduce SFC while providing flame stability (e.g., avoiding flameout).

[0125] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0126] A turbine engine including 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 including: a main chamber, the main chamber including an outer liner and an inner liner; a trapped vortex chamber, the trapped vortex chamber extending from at least one of the outer liner or the inner liner; a plurality of mixing assemblies, the plurality of mixing assemblies operable to inject a fuel-air mixture into the trapped vortex chamber to produce combustion gases. The trapped vortex chamber injects the combustion gases into the main chamber. The turbine engine includes a steam system in fluid communication with the main chamber, the steam system operable to inject steam into the main chamber so that the steam flows downstream of the trapped vortex chamber.

[0127] According to the turbine engine of the preceding clause, the water-to-air ratio of said steam and compressed air in said main chamber is between 0.0% and 60%.

[0128] A turbine engine according to any preceding clause, wherein the water-to-air ratio of the steam and compressed air in the main chamber is between 5% and 60%.

[0129] A turbine engine as claimed in any preceding clause, wherein said main chamber is defined downstream of said trapped vortex cavity.

[0130] A turbine engine as claimed in any preceding clause, wherein said steam system injects said steam downstream of said trapped vortex cavity.

[0131] A turbine engine as recited in any preceding clause, said plurality of mixing assemblies comprising a plurality of fuel injectors operable to inject said fuel into said trapped vortex cavity.

[0132] According to a turbine engine as described in any preceding clause, the trapped vortex cavity defines a combustion zone, the combustion gases are generated in the combustion zone, and the steam system injects the steam into the main chamber so that the combustion gases flow from the combustion zone to the steam in the main chamber.

[0133] A turbine engine as described in any preceding clause, wherein the trapped vortex chamber defines a trapped vortex chamber opening such that the trapped vortex chamber is in fluid communication with the main chamber, and the trapped vortex chamber injects the combustion gases into the main chamber through the trapped vortex chamber opening.

[0134] A turbine engine as described in any preceding clause, wherein the main chamber mixes the combustion gases with the steam to generate a steam-combustion gas mixture in the main chamber.

[0135] A turbine engine as claimed in any preceding clause, wherein said main chamber generates said steam-combustion gas mixture downstream of said trapped vortex cavity.

[0136] According to the turbine engine described in any preceding clause, the trapped vortex chamber includes one or more walls and one or more trapped vortex chamber air holes arranged in at least one of the one or more walls, and the one or more trapped vortex chamber air holes are operable to guide compressed air into the trapped vortex chamber.

[0137] A turbine engine as described in any preceding clause, wherein the one or more trapped vortex chamber air holes are operable to direct the compressed air into the trapped vortex chamber to generate a vortex in the trapped vortex chamber.

[0138] A turbine engine as claimed in any preceding clause, wherein the steam system comprises one or more steam lines for providing the steam to a steam injector.

[0139] A turbine engine as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0140] A turbine engine as described in any preceding clause, wherein the steam system includes one or more liner steam holes in the outer liner or the inner liner, the one or more liner steam holes being operable to direct the steam through the outer liner or the inner liner into the main chamber.

[0141] A turbine engine as described in any preceding clause, wherein said plurality of mixing assemblies comprises a plurality of fuel injectors.

[0142] A turbine engine as in any preceding clause, said plurality of fuel injectors comprising a first fuel injector and a second fuel injector.

[0143] A turbine engine as described in any preceding clause, wherein the first fuel injector comprises one or more first fuel injection holes operable to inject the fuel radially outwardly.

[0144] A turbine engine as claimed in any preceding clause, wherein the second fuel injector comprises one or more second fuel injection holes operable to inject the fuel radially inwardly.

[0145] A turbine engine as described in any preceding clause, wherein the steam system further comprises one or more steam injectors.

[0146] A turbine engine as described in any preceding clause, wherein said one or more steam injectors are coupled to said plurality of mixing assemblies.

[0147] A turbine engine as claimed in any preceding clause, said one or more steam injectors comprising one or more steam injection holes for operatively injecting said steam therethrough.

[0148] A turbine engine as claimed in any preceding clause, wherein said one or more steam injection holes are located on said one or more steam injectors so as to be operable to inject said steam axially rearwardly into said main chamber.

[0149] A turbine engine as claimed in any preceding clause, wherein said one or more steam injection holes are located on said one or more steam injectors so as to be operable to radially inject said steam into said main chamber.

[0150] A turbine engine as described in any preceding clause, wherein the trapped vortex chamber comprises a plurality of trapped vortex chambers.

[0151] The turbine engine of the preceding clause, wherein the plurality of trapped vortex chambers comprises a first trapped vortex chamber and a second trapped vortex chamber.

[0152] A turbine engine as claimed in any preceding clause, wherein said plurality of fuel injectors are positioned to inject said fuel radially into each trapped vortex cavity.

[0153] A turbine engine as described in any preceding clause, each trapped vortex cavity being defined by a first wall, a second wall and a third wall.

[0154] A turbine engine according to the preceding clause, wherein each trapped vortex cavity is further defined by a fourth wall.

[0155] A turbine engine as claimed in any preceding clause, each trapped vortex cavity having a generally rectangular cross-section.

[0156] A turbine engine as claimed in any preceding clause, each trapped vortex cavity having a substantially circular cross-section.

[0157] A turbine engine according to any preceding clause, further comprising an annular dome positioned at a forward end of the outer liner or the inner liner.

[0158] A turbine engine as described in any preceding clause, wherein said plurality of fuel injectors extend through said annular dome to separate said first trapped vortex cavity and said second trapped vortex cavity.

[0159] A turbine engine as described in any preceding clause, wherein the plurality of fuel injectors are disposed between the fourth wall of the first trapped vortex cavity and the fourth wall of the second trapped vortex cavity.

[0160] A turbine engine as claimed in any preceding clause, wherein each trapped vortex cavity is located radially outwardly of the main chamber.

[0161] A turbine engine as claimed in any preceding clause, wherein said main chamber is defined downstream of said plurality of trapped vortex chambers.

[0162] A turbine engine as described in any preceding clause, wherein the outer liner and the inner liner are angled toward each other to define a converging nozzle.

[0163] A turbine engine as described in any preceding clause, wherein said one or more liner steam holes are positioned axially rearward of said plurality of trapped vortex cavities.

[0164] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex cavity apertures are defined through said first wall of each trapped vortex cavity.

[0165] A turbine engine as described in any preceding clause, wherein the plurality of fuel injectors radially inject the fuel into each trapped vortex cavity to generate a fuel flow within each trapped vortex cavity.

[0166] A turbine engine as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are operable to inject said compressed air into each trapped vortex chamber.

[0167] A turbine engine as described in any preceding clause, each trapped vortex cavity mixing said fuel and said compressed air to generate said fuel-air mixture.

[0168] A turbine engine as claimed in any preceding clause, wherein said one or more trapped vortex cavity air holes are operable to inject said compressed air axially rearwardly into each trapped vortex cavity.

[0169] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors are operable to inject said steam to generate a first steam flow in said main chamber.

[0170] According to the turbine engine of the preceding clause, said one or more liner steam holes are operable to inject said steam into said main chamber to generate a second steam flow in said main chamber.

[0171] A turbine engine as recited in any preceding clause, said combustor being operable to mix said combustion gases with said first and second steam flows to generate a steam-combustion gas mixture.

[0172] A turbine engine as described in any preceding clause, wherein said one or more liner steam holes are angled such that said second steam flow is at an angle other than ninety degrees relative to a longitudinal centerline axis of said combustor.

[0173] A turbine engine according to any preceding clause, further comprising a combustor outlet at the aft end of the main chamber.

[0174] A turbine engine as described in any preceding clause, wherein the main chamber is operable to direct the steam-combustion gas mixture through the combustor outlet.

[0175] A turbine engine as claimed in any preceding clause, wherein during low power operation of the turbine engine, the steam system does not inject the steam into the main chamber.

[0176] A turbine engine as claimed in any preceding clause, wherein said water-to-air ratio varies between 0.0% and 60% based on said operating conditions of said turbine engine.

[0177] 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.

[0178] A turbine engine as described in any preceding clause, wherein said one or more trapped vortex cavity apertures comprises a plurality of discrete apertures.

[0179] A turbine engine as described in any preceding clause, wherein said plurality of fuel injectors are annular about said longitudinal centerline axis.

[0180] A turbine engine as described in any preceding clause, wherein the one or more fuel injection holes include a plurality of discrete fuel injection holes spaced circumferentially about the plurality of fuel injectors.

[0181] A turbine engine as described in any preceding clause, wherein said one or more steam injectors are annular about said longitudinal centerline axis.

[0182] A turbine engine as described in any preceding clause, wherein said one or more fuel injection holes and said one or more steam injection holes are alternated circumferentially about said plurality of fuel injectors such that said fuel and said steam are radially injected into said plurality of trapped vortex cavities.

[0183] A turbine engine as described in any preceding clause, wherein the one or more liner steam holes include a plurality of discrete liner steam holes spaced circumferentially about the outer liner or the inner liner.

[0184] A turbine engine as described in any preceding clause, wherein said plurality of trapped vortex cavities are annular about said plurality of fuel injectors.

[0185] A turbine engine as described in any preceding clause, wherein said plurality of fuel injectors are cylindrical.

[0186] A turbine engine as claimed in any preceding clause, said plurality of fuel injectors comprising a first fuel injector arranged to inject said fuel into said first trapped vortex cavity.

[0187] A turbine engine as claimed in any preceding clause, said plurality of fuel injectors comprising a second fuel injector arranged to inject said fuel into said second trapped vortex cavity.

[0188] A turbine engine as recited in any preceding clause, wherein the first fuel injector is disposed through the first wall of the first trapped vortex cavity such that the first fuel injector injects the fuel axially rearwardly into the first trapped vortex cavity.

[0189] A turbine engine as recited in any preceding clause, wherein the second fuel injector is disposed through the first wall of the second trapped vortex cavity such that the second fuel injector injects the fuel axially rearwardly into the second trapped vortex cavity.

[0190] A turbine engine as recited in any preceding clause, wherein the first fuel injector is disposed through the third wall of the first trapped vortex cavity such that the first fuel injector radially injects the fuel into the first trapped vortex cavity.

[0191] A turbine engine as recited in any preceding clause, wherein the second fuel injector is disposed through the third wall of the second trapped vortex cavity such that the second fuel injector injects the fuel radially into the second trapped vortex cavity.

[0192] A turbine engine as described in any preceding clause, further comprising a liner extension extending from the fourth wall of the first trapped vortex cavity to the fourth wall of the second trapped vortex cavity.

[0193] A turbine engine according to any preceding clause, wherein the fourth wall of the first trapped vortex cavity is spaced apart from the fourth wall of the second trapped vortex cavity such that a gap is defined between the fourth wall of the first trapped vortex cavity and the fourth wall of the second trapped vortex cavity.

[0194] A turbine engine as claimed in any preceding clause, wherein the one or more steam injectors include a first steam injector arranged to inject the steam into the first trapped vortex cavity.

[0195] A turbine engine as claimed in any preceding clause, wherein the one or more steam injectors include a second steam injector arranged to inject the steam into the second trapped vortex cavity.

[0196] A turbine engine as described in any preceding clause, wherein the first steam injector is disposed through the third wall of the first trapped vortex cavity to radially inject the steam into the first trapped vortex cavity.

[0197] A turbine engine as described in any preceding clause, wherein the first steam injector is disposed through the third wall of the second trapped vortex cavity to radially inject the steam into the second trapped vortex cavity.

[0198] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors are arranged to inject said steam into said first trapped vortex cavity.

[0199] A turbine engine as described in any preceding clause, wherein the one or more steam injectors are disposed through the third wall of the first trapped vortex cavity to radially inject the steam into the first trapped vortex cavity.

[0200] A turbine engine as recited in any preceding clause, said plurality of fuel injectors being disposed in said gap defined between said fourth wall of said first trapped vortex cavity and said fourth wall of said second trapped vortex cavity.

[0201] A turbine engine as claimed in any preceding clause, said plurality of fuel injectors comprising said one or more fuel injection holes for injecting said fuel therethrough.

[0202] A turbine engine as claimed in any preceding clause, wherein said one or more fuel injection holes are arranged to inject said fuel radially into said plurality of trapped vortex cavities.

[0203] A turbine engine as claimed in any preceding clause, wherein said one or more fuel injection holes comprise one or more first fuel injection holes for injecting said fuel into said first trapped vortex cavity.

[0204] A turbine engine as claimed in any preceding clause, wherein said one or more fuel injection holes include one or more second fuel injection holes for injecting said fuel into said second trapped vortex cavity.

[0205] A turbine engine as claimed in any preceding clause, wherein said one or more fuel injection holes include one or more third fuel injection holes for axially injecting said fuel into said main chamber.

[0206] According to a turbine engine described in any of the preceding clauses, the fuel flow in the multiple TVCs is a first fuel flow, and the one or more fuel injectors inject the fuel through the one or more third fuel injection holes to generate a second fuel flow, thereby generating a second fuel-air mixture in the main chamber.

[0207] A turbine engine as recited in any preceding clause, wherein said one or more steam injectors are disposed through said gap between said fourth wall of said first trapped vortex cavity and said fourth wall of said second trapped vortex cavity.

[0208] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors comprise one or more first steam injection holes for axially injecting said steam into said main chamber.

[0209] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors include one or more second steam injection holes for injecting said steam into said plurality of trapped vortex chambers.

[0210] A turbine engine as claimed in any preceding clause, wherein said plurality of trapped vortex chambers are disposed axially rearwardly of said annular dome.

[0211] A turbine engine according to any preceding clause, further comprising a plurality of steam injectors.

[0212] A turbine engine as described in any preceding clause, said plurality of steam injectors comprising a first steam injector disposed through said annular dome to inject said steam into said main chamber.

[0213] A turbine engine as recited in any preceding clause, said plurality of steam injectors comprising a second steam injector configured to inject said steam into said first trapped vortex cavity downstream of said combustion zone.

[0214] A turbine engine as described in any preceding clause, wherein said plurality of steam injectors includes a third steam injector configured to inject said steam into said second trapped vortex cavity downstream of said combustion zone.

[0215] A turbine engine as claimed in any preceding clause, wherein said one or more trapped vortex cavity apertures are provided through said second wall of each trapped vortex cavity.

[0216] A turbine engine as in any preceding clause, said first steam injector injecting said steam upstream of said trapped vortex cavity openings of said plurality of trapped vortex cavities.

[0217] A turbine engine as described in any preceding clause, wherein said plurality of trapped vortex cavities are provided in said outer liner.

[0218] A turbine engine as described in any preceding clause, wherein said plurality of trapped vortex cavities are provided in said liner.

[0219] A combustor comprises: a main chamber, the main chamber including an outer liner and an inner liner; a trapped vortex chamber, the trapped vortex chamber extending from at least one of the outer liner or the inner liner; a plurality of mixing assemblies, the plurality of mixing assemblies being operable to inject a fuel-air mixture into the trapped vortex chamber to produce combustion gases, the trapped vortex chamber injecting the combustion gases into the main chamber; and a steam system, the steam system being fluidly connected to the main chamber, the steam system being operable to inject steam into the main chamber so that the steam flows downstream of the trapped vortex chamber.

[0220] According to the burner of the preceding clause, the water-air ratio of the steam and compressed air in the main chamber is 0.0% to 60%.

[0221] A burner according to any preceding clause, wherein the water-to-air ratio of the steam and compressed air in the main chamber is between 5% and 60%.

[0222] A burner as claimed in any preceding clause, wherein said main chamber is defined downstream of said trapped vortex cavity.

[0223] A burner as claimed in any preceding clause, wherein said steam system injects said steam downstream of said trapped vortex chamber.

[0224] The combustor of any preceding clause, said plurality of mixing assemblies comprising a plurality of fuel injectors operable to inject said fuel into said trapped vortex cavity.

[0225] A burner according to any preceding clause, wherein the trapped vortex chamber defines a combustion zone in which the combustion gases are produced, and the steam system injects the steam into the main chamber such that the combustion gases flow from the combustion zone to the steam in the main chamber.

[0226] A burner as described in any preceding clause, wherein the trapped vortex chamber defines a trapped vortex chamber opening such that the trapped vortex chamber is in fluid communication with the main chamber, and the trapped vortex chamber injects the combustion gases into the main chamber through the trapped vortex chamber opening.

[0227] A burner as claimed in any preceding clause, wherein the main chamber mixes the combustion gas with the steam to generate a steam-combustion gas mixture in the main chamber.

[0228] A burner as claimed in any preceding clause, wherein said main chamber generates said steam-combustion gas mixture downstream of said trapped vortex cavity.

[0229] According to the combustor of any preceding clause, the trapped vortex chamber comprises one or more walls and one or more trapped vortex chamber air holes disposed in at least one of the one or more walls, the one or more trapped vortex chamber air holes being operable to direct compressed air into the trapped vortex chamber.

[0230] A combustor as claimed in any preceding clause, wherein the one or more trapped vortex chamber air holes are operable to direct the compressed air into the trapped vortex chamber to generate a vortex in the trapped vortex chamber.

[0231] A burner as claimed in any preceding clause, wherein the steam system comprises one or more steam lines for providing the steam to a steam injector.

[0232] A combustor as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0233] The combustor of any preceding clause, the steam system comprising one or more liner steam holes in the outer liner or the inner liner, the one or more liner steam holes operable to direct the steam through the outer liner or the inner liner into the main chamber.

[0234] A combustor as claimed in any preceding clause, wherein the plurality of mixing assemblies comprises a plurality of fuel injectors.

[0235] A combustor as in any preceding clause, said plurality of fuel injectors comprising a first fuel injector and a second fuel injector.

[0236] A combustor as claimed in any preceding clause, wherein the first fuel injector comprises one or more first fuel injection holes operable to inject the fuel radially outwardly.

[0237] A combustor as claimed in any preceding clause, wherein the second fuel injector comprises one or more second fuel injection holes operable to inject the fuel radially inwardly.

[0238] A burner as claimed in any preceding clause, wherein the steam system further comprises one or more steam injectors.

[0239] The combustor of any preceding clause, wherein the one or more steam injectors are coupled to the plurality of mixing assemblies.

[0240] A burner as claimed in any preceding clause, said one or more steam injectors comprising one or more steam injection holes for operatively injecting said steam therethrough.

[0241] A burner as claimed in any preceding clause, wherein said one or more steam injection holes are located on said one or more steam injectors to be operable to inject said steam axially rearwardly into said main chamber.

[0242] A burner as claimed in any preceding clause, wherein said one or more steam injection holes are located on said one or more steam injectors so as to be operable to radially inject said steam into said main chamber.

[0243] A combustor as claimed in any preceding clause, wherein the trapped vortex chamber comprises a plurality of trapped vortex chambers.

[0244] The combustor of the preceding clause, wherein the plurality of trapped vortex chambers comprises a first trapped vortex chamber and a second trapped vortex chamber.

[0245] A combustor as claimed in any preceding clause, wherein the plurality of fuel injectors are positioned to inject the fuel radially into each trapped vortex cavity.

[0246] A burner as claimed in any preceding clause, each trapped vortex chamber being defined by a first wall, a second wall and a third wall.

[0247] A burner according to the preceding clause, wherein each trapped vortex chamber is further defined by a fourth wall.

[0248] A burner as claimed in any preceding clause, each trapped vortex cavity having a generally rectangular cross-section.

[0249] A burner as claimed in any preceding clause, each trapped vortex cavity having a substantially circular cross-section.

[0250] The combustor of any preceding clause, further comprising an annular dome positioned at a forward end of the outer liner or the inner liner.

[0251] The combustor of any preceding clause, wherein the plurality of fuel injectors extend through the annular dome to separate the first trapped vortex chamber and the second trapped vortex chamber.

[0252] The combustor of any preceding clause, said plurality of fuel injectors being disposed between said fourth wall of said first trapped vortex cavity and said fourth wall of said second trapped vortex cavity.

[0253] A burner as claimed in any preceding clause, wherein each trapped vortex cavity is located radially outwardly of the main chamber.

[0254] A combustor as claimed in any preceding clause, wherein said main chamber is defined downstream of said plurality of trapped vortex cavities.

[0255] A combustor as in any preceding clause, wherein the outer liner and the inner liner are angled toward each other to define a converging nozzle.

[0256] A combustor as in any preceding clause, wherein said one or more liner steam holes are positioned axially rearward of said plurality of trapped vortex cavities.

[0257] A burner as claimed in any preceding clause, said one or more trapped vortex chamber air holes being defined through said first wall of each trapped vortex chamber.

[0258] A combustor as claimed in any preceding clause, wherein the plurality of fuel injectors radially inject the fuel into each trapped vortex cavity to generate a fuel flow within each trapped vortex cavity.

[0259] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are operable to inject said compressed air into each trapped vortex chamber.

[0260] A combustor as claimed in any preceding clause, each trapped vortex chamber mixing said fuel and said compressed air to generate said fuel-air mixture.

[0261] A combustor as claimed in any preceding clause, wherein said one or more trapped vortex chamber air holes are operable to inject said compressed air axially rearwardly into each trapped vortex chamber.

[0262] A burner as claimed in any preceding clause, wherein said one or more steam injectors are operable to inject said steam to generate a first steam flow in said main chamber.

[0263] According to the combustor of the preceding clause, the one or more liner steam holes are operable to inject the steam into the main chamber to generate a secondary steam flow in the main chamber.

[0264] A combustor as claimed in any preceding clause, operable to mix the combustion gases with the first and second steam flows to generate a steam-combustion gas mixture.

[0265] The combustor of any preceding clause, wherein the one or more liner steam holes are angled such that the second steam flow is at an angle other than ninety degrees relative to a longitudinal centerline axis of the combustor.

[0266] A burner according to any preceding clause, further comprising a burner outlet at a rearward end of the main chamber.

[0267] A burner as claimed in any preceding clause, wherein the main chamber is operable to direct the steam-combustion gas mixture through the burner outlet.

[0268] The combustor of any preceding clause, wherein during low power operation of the turbine engine, the steam system does not inject the steam into the main chamber.

[0269] The combustor of any preceding clause, water-to-air ratio varying between 0.0% and 60% based on said operating conditions of said turbine engine.

[0270] 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.

[0271] A burner as claimed in any preceding clause, wherein the one or more trapped vortex chamber holes comprise a plurality of discrete holes.

[0272] A combustor as in any preceding clause, said plurality of fuel injectors being annular about said longitudinal centerline axis.

[0273] The combustor of any preceding clause, the one or more fuel injection holes comprising a plurality of discrete fuel injection holes spaced circumferentially about the plurality of fuel injectors.

[0274] A combustor as claimed in any preceding clause, wherein said one or more steam injectors are annular about said longitudinal centreline axis.

[0275] A combustor as in any preceding clause, wherein said one or more fuel injection holes and said one or more steam injection holes are alternated circumferentially about said plurality of fuel injectors such that said fuel and said steam are radially injected into said plurality of trapped vortex cavities.

[0276] The combustor of any preceding clause, the one or more liner steam holes comprising a plurality of discrete liner steam holes spaced circumferentially about the outer liner or the inner liner.

[0277] A combustor as in any preceding clause, said plurality of trapped vortex cavities being annular about said plurality of fuel injectors.

[0278] A combustor as claimed in any preceding clause, wherein said plurality of fuel injectors are cylindrical in shape.

[0279] A combustor as claimed in any preceding clause, said plurality of fuel injectors comprising a first fuel injector arranged to inject said fuel into said first trapped vortex cavity.

[0280] A combustor as claimed in any preceding clause, said plurality of fuel injectors comprising a second fuel injector arranged to inject said fuel into said second trapped vortex cavity.

[0281] The combustor of any preceding clause, the first fuel injector being disposed through the first wall of the first trapped vortex cavity such that the first fuel injector injects the fuel axially rearwardly into the first trapped vortex cavity.

[0282] The combustor of any preceding clause, the second fuel injector being disposed through the first wall of the second trapped vortex cavity such that the second fuel injector injects the fuel axially rearwardly into the second trapped vortex cavity.

[0283] The combustor of any preceding clause, the first fuel injector being disposed through the third wall of the first trapped vortex cavity such that the first fuel injector radially injects the fuel into the first trapped vortex cavity.

[0284] The combustor of any preceding clause, the second fuel injector being disposed through the third wall of the second trapped vortex cavity such that the second fuel injector radially injects the fuel into the second trapped vortex cavity.

[0285] A combustor as in any preceding clause, further comprising a liner extension extending from the fourth wall of the first trapped vortex cavity to the fourth wall of the second trapped vortex cavity.

[0286] A combustor as in any preceding clause, wherein the fourth wall of the first trapped vortex cavity is spaced apart from the fourth wall of the second trapped vortex cavity such that a gap is defined therebetween.

[0287] A burner as claimed in any preceding clause, wherein the one or more steam injectors include a first steam injector arranged to inject the steam into the first trapped vortex chamber.

[0288] A burner as claimed in any preceding clause, wherein the one or more steam injectors include a second steam injector arranged to inject the steam into the second trapped vortex chamber.

[0289] The combustor of any preceding clause, wherein the first steam injector is disposed through the third wall of the first trapped vortex cavity to radially inject the steam into the first trapped vortex cavity.

[0290] The combustor of any preceding clause, wherein the first steam injector is disposed through the third wall of the second trapped vortex chamber to radially inject the steam into the second trapped vortex chamber.

[0291] A burner as claimed in any preceding clause, wherein the one or more steam injectors are arranged to inject the steam into the first trapped vortex chamber.

[0292] The combustor of any preceding clause, wherein the one or more steam injectors are disposed through the third wall of the first trapped vortex cavity to radially inject the steam into the first trapped vortex cavity.

[0293] A combustor as in any preceding clause, said plurality of fuel injectors being disposed in said gap defined between said fourth wall of said first trapped vortex cavity and said fourth wall of said second trapped vortex cavity.

[0294] A burner as claimed in any preceding clause, said plurality of fuel injectors comprising said one or more fuel injection holes for injecting said fuel therethrough.

[0295] A combustor as claimed in any preceding clause, wherein said one or more fuel injection holes are arranged to inject said fuel radially into said plurality of trapped vortex cavities.

[0296] A combustor as claimed in any preceding clause, wherein the one or more fuel injection holes comprise one or more first fuel injection holes for injecting the fuel into the first trapped vortex cavity.

[0297] A combustor as claimed in any preceding clause, wherein the one or more fuel injection holes include one or more second fuel injection holes for injecting the fuel into the second trapped vortex cavity.

[0298] A burner as claimed in any preceding clause, wherein said one or more fuel injection holes include one or more third fuel injection holes for axially injecting said fuel into said main chamber.

[0299] According to the burner described in any of the preceding items, the fuel flow in the multiple trapped vortex chambers is a first fuel flow, and the one or more fuel injectors inject the fuel through the one or more third fuel injection holes to generate a second fuel flow, thereby generating a second fuel-air mixture in the main chamber.

[0300] The burner of any preceding clause, said one or more steam injectors being disposed through said gap between said fourth wall of said first trapped vortex cavity and said fourth wall of said second trapped vortex cavity.

[0301] A burner as claimed in any preceding clause, said one or more steam injectors comprising one or more first steam injection holes for injecting said steam axially into said main chamber.

[0302] A burner as in any preceding clause, said one or more steam injectors comprising one or more second steam injection holes for injecting said steam into said plurality of trapped vortex chambers.

[0303] A combustor as claimed in any preceding clause, wherein said plurality of trapped vortex chambers are disposed axially rearwardly of said annular dome.

[0304] A combustor according to any preceding clause, further comprising a plurality of steam injectors.

[0305] A burner as in any preceding clause, said plurality of steam injectors comprising a first steam injector disposed through said annular dome to inject said steam into said main chamber.

[0306] The combustor of any preceding clause, said plurality of steam injectors comprising a second steam injector configured to inject said steam into said first trapped vortex cavity downstream of said combustion zone.

[0307] The combustor of any preceding clause, said plurality of steam injectors comprising a third steam injector configured to inject said steam into said second trapped vortex cavity downstream of said combustion zone.

[0308] A burner as claimed in any preceding clause, wherein the one or more trapped vortex chamber air holes are provided through the second wall of each trapped vortex chamber.

[0309] A combustor as in any preceding clause, said first steam injector injecting said steam upstream of said trapped vortex cavity openings of said plurality of trapped vortex cavities.

[0310] A combustor as in any preceding clause, said plurality of trapped vortex cavities being disposed in said outer liner.

[0311] A combustor as described in any preceding clause, wherein the plurality of trapped vortex cavities are provided in the liner.

[0312] A method of operating a burner according to any of the preceding clauses, the method comprising: generating the fuel-air mixture using the plurality of mixing assemblies; injecting the fuel-air mixture into the trapped vortex chamber to generate a flame, the flame producing combustion gases within the trapped vortex chamber; injecting the combustion gases into the main chamber; injecting the steam into the main chamber using the steam system; and flowing the steam downstream of the trapped vortex chamber.

[0313] The method of the preceding clause, further comprising injecting the steam using the steam system during medium power operation of the burner and during high power operation of the burner.

[0314] A method according to any preceding clause, further comprising injecting the steam such that a water-to-air ratio of the steam to compressed air in the main chamber is between 0.0% and 60%.

[0315] A method as claimed in any preceding clause, wherein the water-to-air ratio of the steam and compressed air in the main chamber is between 5% and 60%.

[0316] A method as in any preceding clause, said trapped vortex chamber defining a combustion zone, and further comprising causing said combustion to enter said combustion zone and causing said combustion gases to flow from said combustion zone to said steam in said main chamber.

[0317] A method as defined in any preceding clause, further comprising injecting compressed air into the trapped vortex chamber.

[0318] A method as in any preceding clause, further comprising generating a vortex in the trapped vortex chamber using the compressed air.

[0319] A method as in any preceding clause, further comprising injecting the combustion gases from the trapped vortex chamber into the main chamber.

[0320] A method as in any preceding clause, further comprising mixing the combustion with the steam to generate a steam-combustion gas mixture in the main chamber.

[0321] A method as in any preceding clause, further comprising generating the steam-combustion gas mixture downstream of the trapped vortex chamber.

[0322] A method as defined in any preceding clause, further comprising providing the steam to the burner via one or more steam lines.

[0323] A method as in any preceding clause, further comprising generating the steam from exhaust gas of the combustor.

[0324] A method as in any preceding clause, wherein the steam system comprises one or more liner steam holes in the outer liner or the inner liner, the method further comprising directing the steam through the one or more liner steam holes into the main chamber.

[0325] A method as in any preceding clause, the plurality of mixing assemblies comprising a plurality of fuel injectors.

[0326] A method as in any preceding clause, the plurality of fuel injectors comprising a first fuel injector and a second fuel injector.

[0327] A method as in any preceding clause, wherein the first fuel injector comprises one or more first fuel injection holes, the method further comprising injecting the fuel radially outwardly through the one or more first fuel injection holes.

[0328] A method as in any preceding clause, wherein the second fuel injector comprises one or more second fuel injection holes, the method further comprising injecting the fuel radially inwardly through the one or more second fuel injection holes.

[0329] A method as in any preceding clause, the steam system further comprising one or more steam injectors.

[0330] A method as in any preceding clause, wherein the one or more steam injectors are coupled to the plurality of mixing assemblies.

[0331] A method as in any preceding clause, wherein the one or more steam injectors comprise one or more steam injection holes, the method further comprising injecting the steam through the one or more steam injection holes.

[0332] A method as in any preceding clause, further comprising injecting the steam axially rearwardly into the main chamber.

[0333] A method as in any preceding clause, further comprising injecting the steam radially into the main chamber.

[0334] A method as in any preceding clause, the trapped vortex chamber comprising a plurality of trapped vortex chambers.

[0335] A method as described in the preceding clause, wherein the plurality of trapped vortex chambers comprises a first trapped vortex chamber and a second trapped vortex chamber.

[0336] A method as defined in any preceding clause, further comprising injecting the fuel radially into each trapped vortex cavity.

[0337] A method as in any preceding clause, each trapped vortex chamber being defined by a first wall, a second wall and a third wall.

[0338] A method as recited in the preceding clause, wherein each trapped vortex chamber is further defined by a fourth wall.

[0339] A method as in any preceding clause, each trapped vortex chamber having a generally rectangular cross-section.

[0340] A method as in any preceding clause, each trapped vortex chamber having a substantially circular cross-section.

[0341] A method as in any preceding clause, further comprising an annular dome positioned at a forward end of the outer liner or the inner liner.

[0342] A method as in any preceding clause, wherein the plurality of fuel injectors extend through the annular dome to separate the first trapped vortex chamber and the second trapped vortex chamber.

[0343] A method as in any preceding clause, wherein the plurality of fuel injectors are disposed between the fourth wall of the first trapped vortex cavity and the fourth wall of the second trapped vortex cavity.

[0344] A method as in any preceding clause, each trapped vortex chamber being located radially outwardly of the main chamber.

[0345] A method as in any preceding clause, wherein the main chamber is defined downstream of the plurality of trapped vortex chambers.

[0346] A method as in any preceding clause, wherein the outer liner and the inner liner are angled toward one another to define a converging nozzle.

[0347] A method as in any preceding clause, further comprising injecting said steam through said one or more liner steam holes axially rearward of said plurality of trapped vortex chambers.

[0348] A method as in any preceding clause, wherein the one or more trapped vortex chamber air holes are defined through the first wall of each trapped vortex chamber.

[0349] A method as defined in any preceding clause, further comprising injecting the fuel radially into each trapped vortex cavity to generate a fuel flow within each trapped vortex cavity.

[0350] A method as defined in any preceding clause, further comprising injecting the compressed air into each trapped vortex chamber through the one or more trapped vortex chamber air holes.

[0351] A method as in any preceding clause, further comprising mixing the fuel and the compressed air in each trapped vortex cavity to generate the fuel-air mixture.

[0352] A method as defined in any preceding clause, further comprising injecting the compressed air axially rearwardly into each trapped vortex cavity.

[0353] A method as in any preceding clause, further comprising injecting the steam using the one or more steam injectors to generate a first steam flow in the main chamber.

[0354] The method of any preceding clause, further comprising injecting the steam into the main chamber through the one or more liner steam holes to generate a second steam flow in the main chamber.

[0355] A method as in any preceding clause, further comprising mixing the combustion gas with the first steam stream and the second steam stream to generate a steam-combustion gas mixture.

[0356] A method as in any preceding clause, further comprising injecting the second steam flow at an angle other than ninety degrees relative to a longitudinal centerline axis of the combustor.

[0357] A method as in any preceding clause, further comprising a burner outlet at a rearward end of the main chamber.

[0358] The method of the preceding clause, further comprising directing the steam-combustion gas mixture through the burner outlet.

[0359] The method of any preceding clause, further comprising not injecting steam into the main chamber during low power operation of the turbine engine.

[0360] A method as in any preceding clause, said water-to-air ratio being varied between 0.0% and 60% based on said operating conditions of said turbine engine.

[0361] 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.

[0362] A method as in any preceding clause, wherein the one or more trapped vortex chamber pores comprise a plurality of discrete pores.

[0363] A method as in any preceding clause, said plurality of fuel injectors being annular about said longitudinal centerline axis.

[0364] A method as in any preceding clause, wherein the one or more fuel injection holes comprise a plurality of discrete fuel injection holes spaced circumferentially about the plurality of fuel injectors.

[0365] A method as in any preceding clause, wherein said one or more steam injectors are annular about said longitudinal centreline axis.

[0366] A method as in any preceding clause, further comprising radially injecting the fuel and the steam into the plurality of trapped vortex cavities.

[0367] The method of any preceding clause, wherein the one or more liner steam holes comprise a plurality of discrete liner steam holes spaced circumferentially about the outer liner or the inner liner.

[0368] A method as in any preceding clause, wherein the plurality of trapped vortex cavities are annular about the plurality of fuel injectors.

[0369] A method as in any preceding clause, wherein the plurality of fuel injectors are cylindrical.

[0370] A method as in any preceding clause, further comprising injecting the fuel into the first trapped vortex chamber using the first fuel injector.

[0371] A method as defined in any preceding clause, further comprising injecting the fuel into the second trapped vortex cavity.

[0372] A method as in any preceding clause, further comprising injecting the fuel axially rearward of the first trapped vortex cavity.

[0373] A method as in any preceding clause, further comprising injecting the fuel axially rearwardly into the second trapped vortex cavity.

[0374] A method as in any preceding clause, further comprising injecting the fuel radially into the first trapped vortex cavity.

[0375] A method as in any preceding clause, further comprising injecting the fuel radially into the second trapped vortex cavity.

[0376] A method as in any preceding clause, the combustor further comprising a liner extension extending from the fourth wall of the first trapped vortex cavity to the fourth wall of the second trapped vortex cavity.

[0377] A method as in any preceding clause, wherein the fourth wall of the first trapped vortex chamber is spaced apart from the fourth wall of the second trapped vortex chamber such that a gap is defined therebetween.

[0378] A method as in any preceding clause, further comprising injecting the steam into the first trapped vortex chamber.

[0379] A method as defined in any preceding clause, further comprising injecting the steam into the second trapped vortex chamber.

[0380] A method as in any preceding clause, further comprising radially injecting the steam into the first trapped vortex chamber.

[0381] A method as in any preceding clause, further comprising radially injecting the steam into the second trapped vortex chamber.

[0382] A method as in any preceding clause, wherein the plurality of fuel injectors are disposed in the gap defined between the fourth wall of the first trapped vortex cavity and the fourth wall of the second trapped vortex cavity.

[0383] A method as in any preceding clause, wherein the plurality of fuel injectors comprises the one or more fuel injection holes, the method further comprising injecting the fuel through the one or more fuel injection holes.

[0384] A method as in any preceding clause, further comprising injecting the fuel radially into the plurality of trapped vortex cavities.

[0385] A method as in any preceding clause, further comprising injecting the fuel into the first trapped vortex chamber through one or more first fuel injection holes.

[0386] A method as in any preceding clause, further comprising injecting the fuel into the second trapped vortex chamber through one or more second fuel injection holes.

[0387] A method as in any preceding clause, further comprising injecting the fuel axially into the main chamber through one or more third fuel injection holes.

[0388] According to the method of any preceding clause, the fuel flow in the plurality of trapped vortex cavities is a first fuel flow, the method further comprising injecting the fuel through the one or more third fuel injection holes to generate a second fuel flow, thereby generating a second fuel-air mixture in the main chamber.

[0389] A method as in any preceding clause, wherein the one or more steam injectors are disposed through the gap between the fourth wall of the first trapped vortex chamber and the fourth wall of the second trapped vortex chamber.

[0390] A method as in any preceding clause, further comprising injecting the steam axially into the main chamber through one or more first steam injection holes.

[0391] The method of any preceding clause, further comprising injecting the steam into the plurality of trapped vortex chambers through one or more second steam injection holes.

[0392] A method as in any preceding clause, wherein the plurality of trapped vortex chambers are disposed axially rearwardly of the annular dome.

[0393] A method as defined in the preceding clause, further comprising a plurality of steam injectors.

[0394] A method as in any preceding clause, further comprising injecting the steam into the main chamber using a first steam injector.

[0395] The method of any preceding clause, further comprising injecting the steam into the first trapped vortex cavity downstream of the combustion zone using a second steam injector.

[0396] The method of any preceding clause, further comprising injecting the steam into the second trapped vortex cavity downstream of the combustion zone using a third steam injector.

[0397] A method as in any preceding clause, wherein the one or more trapped vortex chamber air holes are provided through the second wall of each trapped vortex chamber.

[0398] A method as in any preceding clause, further comprising injecting the steam upstream of the trapped vortex chamber openings of the plurality of trapped vortex chambers.

[0399] A method as in any preceding clause, wherein the plurality of trapped vortex chambers are provided in the outer liner.

[0400] A method as in any preceding clause, said plurality of trapped vortex chambers being provided in said liner.

[0401] A method as in any preceding clause, further comprising mixing the combustion gas and the second steam flow to generate a first steam-combustion gas mixture in the trapped vortex chamber.

[0402] A method as in any preceding clause, further comprising injecting the first steam-combustion gas mixture from the trapped vortex cavity into the main chamber.

[0403] The method of any preceding clause, further comprising mixing the first steam flow with the first steam-combustion gas mixture to generate a second steam-combustion gas mixture.

[0404] The method of any preceding clause, further comprising directing the second steam-combustion gas mixture through the burner outlet.

[0405] 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 main chamber, the main chamber comprising an outer liner and an inner liner; a trapped vortex chamber extending from at least one of the outer liner or the inner liner; a plurality of mixing assemblies operable to inject a fuel-air mixture into the trapped vortex chamber to produce combustion gases, the trapped vortex chamber injecting the combustion gases into the main chamber; and A steam system is in fluid communication with the main chamber, the steam system being operable to inject steam into the main chamber such that the steam flows downstream of the trapped vortex chamber.

2. The burner according to claim 1, characterized in that in, The water-to-air ratio of the steam and compressed air in the main chamber is 0.0% to 60%.

3. The burner according to claim 1, characterized in that in, The main chamber is defined downstream of the trapped vortex chamber.

4. The burner according to claim 1, characterized in that The plurality of mixing assemblies includes a plurality of fuel injectors operable to inject the fuel into the trapped vortex cavity.

5. The burner according to claim 1, characterized in that in, The trapped vortex chamber defines a combustion zone in which the combustion gases are generated, and the steam system injects the steam into the main chamber such that the combustion gases flow from the combustion zone to the steam in the main chamber.

6. The burner according to claim 1, characterized in that in, The trapped vortex chamber includes one or more walls and one or more trapped vortex chamber air holes disposed in at least one of the one or more walls, the one or more trapped vortex chamber air holes operable to direct compressed air into the trapped vortex chamber.

7. The burner according to claim 6, characterized in that in, The one or more trapped vortex chamber air holes are operable to direct the compressed air into the trapped vortex chamber to generate a vortex in the trapped vortex chamber.

8. The burner according to claim 1, characterized in that in, The trapped vortex chamber defines a trapped vortex chamber opening such that the trapped vortex chamber is in fluid communication with the main chamber, and the trapped vortex chamber injects the combustion gas into the main chamber through the trapped vortex chamber opening.

9. The burner according to claim 8, characterized in that in, The main chamber mixes the combustion gas with the steam to generate a steam-combustion gas mixture in the main chamber.

10. The burner according to claim 9, characterized in that in, The main chamber generates the steam-combustion gas mixture downstream of the trapped vortex chamber.

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