Combustor

Abstract

A combustor includes a combustion chamber and an annular dome. The combustion chamber includes an outer liner and an inner liner, and has a combustion zone. An annular dome is coupled to the outer liner and the inner liner. A plurality of mixing assemblies are operable to inject a fuel-air mixture into a combustion zone of the combustion chamber to produce combustion gases. A combustor steam system is in fluid communication with the combustion chamber. The combustor steam system includes a steam path defined by at least one of an outer liner, an inner liner, or an annular dome. The combustor steam system is operable to direct steam from at least one of the outer liner, the inner liner, or the annular dome through the steam path and into the combustion 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 in the core section of the turbine engine. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

[0006] Figure 3 According to the present disclosure Figure 2 Details from 3 locations Figure 2 A schematic cross-sectional view of a portion of an outer liner of a combustor.

[0007] Figure 4 According to the present disclosure Figure 3 Details 4-4 of the interception Figure 3 Schematic cross-sectional plan view of a portion of an outer lining.

[0008] Figure 5 is a schematic cross-sectional plan view of a portion of an outer liner of a combustor according to another embodiment.

[0009] Figure 6 is a schematic cross-sectional bottom view of a portion of an outer liner of a combustor according to another embodiment.

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

[0011] Figure 8 According to the present disclosure Figure 7 The details in 8-8 are taken Figure 7 Schematic cross-sectional bottom view of a portion of an outer liner.

[0012] Fig. 9 is a schematic cross-sectional bottom view of a portion of an outer liner of a combustor according to another embodiment.

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

[0014] Fig.11 According to the present disclosure Fig.10 Details from 11-11 Fig.10 Schematic cross-sectional bottom view of a portion of an outer liner.

[0015] Fig.12 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0016] Fig.13 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0017] Fig.14 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0018] Fig.15 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0019] Fig.16 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0020] Fig.17 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0021] Fig.18 is a schematic cross-sectional view of a portion of an outer liner of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0022] Fig.19 is a schematic cross-sectional view of a portion of an annular dome of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0023] Fig. 20 According to the present disclosure Fig.19 Schematic cross-sectional rear view of a portion of an annular dome.

[0024] Fig.21 is a schematic rear view of a portion of an annular dome of a combustor according to the present disclosure.

[0025] Fig. 22 is a schematic cross-sectional view of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment.

[0026] Fig.23 is a schematic cross-sectional view of a combustor taken along a longitudinal centerline axis of the combustor according to another embodiment. DETAILED DESCRIPTION

[0027] 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.

[0028] 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.

[0029] 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.

[0030] 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.

[0031] 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.

[0032] As used herein, the terms "low," "medium" (or "medium"), and "high," or their respective comparatives (e.g., "lower" and "higher," as applicable), when used with a compressor, combustor, turbine, shaft, fan, or turbine engine component, refer to relative pressures, relative speeds, relative temperatures, or relative power outputs within an engine, unless otherwise specified. For example, a "low power" setting defines an engine or combustor that is configured to operate at a power output lower than a "high power" setting of the engine or combustor, while a "medium power" setting defines an engine or combustor that is configured to operate at a power output higher than the "low power" setting and lower than the "high power" setting. The terms "low," "medium" (or "medium"), or "high" in such above-mentioned terms may additionally or alternatively be understood as relative to a minimum allowable speed, pressure, or temperature, or relative to a minimum or maximum allowable speed, pressure, or temperature for normal, desired, steady-state, etc., operation of an engine or combustor.

[0033] The various power levels of the turbine engines described in detail herein are defined as percentages of the maximum engine rated thrust at sea level static (SLS). Low power operation or conditions include, for example, less than thirty percent (30%) of the SLS maximum engine rated thrust of the turbine engine. Medium power operation or conditions include, for example, thirty percent (30%) to eighty-five percent (85%) of the SLS maximum engine rated thrust of the turbine engine. High power operation or conditions include, for example, greater than eighty-five percent (85%) of the SLS maximum engine rated thrust of the turbine engine. The value of the thrust of each of the low power operation, medium power operation, and high power operation of the turbine engine is exemplary only, and other values ​​of thrust can be used to define low power operation, medium power operation, and high power operation.

[0034] 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.

[0035] The singular forms "a," "an," and "the" include plural references unless the context clearly dictates otherwise.

[0036] 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.

[0037] 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.

[0038] 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.

[0039] 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, burning steam will increase CO emissions and may cause flameout because the steam will block the flame (e.g., reduce oxygen in the combustion chamber). In addition, such turbine engines that inject steam from the fuel nozzles can achieve up to about 5% water-to-air ratio (WAR) in the combustor before flameout occurs. Therefore, such turbine engines are limited in the amount of emissions and SFC reduction that can be achieved through steam injection before flameout.

[0040] Thus, embodiments of the present disclosure provide a system and method for balancing the need for low fuel combustion and low emissions (e.g., NOx The present invention provides a turbine engine having a combustor having a steam system that flows steam in at least one of an outer liner, an inner liner, or an annular dome of the combustor. The steam flows through a channel in the outer liner, the inner liner, or the annular dome to cool the outer liner, the inner liner, or the annular dome. The steam is discharged from the outer liner, the inner liner, or the annular dome or injected into the combustion chamber. At least one of the outer liner or the inner liner includes a dilution hole, and the steam is injected through at least one of the steam cooling holes downstream of the dilution hole or the dilution hole (e.g., axially rearward). The annular dome includes at least one of the flame forming holes or the dome cooling holes through which the steam is injected. The steam passing through the flame forming holes prevents the flame from expanding radially beyond the steam injected through the flame forming holes. Compared with a turbine engine and a combustor without the benefits of the present invention, the steam is injected at a position away from the flame area (e.g., the combustion zone) to avoid flameout, while also ensuring that more steam is injected into the combustion chamber to reduce SFC.

[0041] The steam system of the present disclosure enables greater amounts of steam to be injected into the combustor without sacrificing the operability of the combustor as compared to a combustor without the benefit of the present disclosure. For example, steam is injected into the combustion chamber away from the combustion zone to avoid flame blowout in the combustion zone because the steam is kept away from the flame. This configuration of injecting steam away from the flame enables greater amounts of steam to be injected into the combustor to reduce emissions and reduce SFC while providing flame stability (e.g., avoiding blowout) as compared to a combustor without the benefit of the present disclosure. The present disclosure provides up to 60% WAR as compared to turbine engines and combustors without the benefit of the present disclosure, thereby enabling greater amounts of steam to reduce emissions and reduce SFC while providing flame stability in the combustor (e.g., avoiding blowout). Steam in the liner or annular dome helps increase the life of the liner or annular dome as compared to liners and annular domes without the benefit of the present disclosure.

[0042] 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 .

[0043] The depicted core turbine engine 16 generally includes a casing 18 that is substantially tubular and defines an annular inlet 20. Figure 1As 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.

[0044] 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 .

[0045] 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 case or nacelle 50 that circumferentially surrounds fan 38 and at least a portion of core turbine engine 16. Nacelle 50 is supported relative to core turbine engine 16 by a plurality of outlet guide vanes 52 that are circumferentially spaced about nacelle 50. 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.

[0046] 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.

[0047] 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.

[0048] 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.

[0049] 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 the fuel 67 to the combustion section 26. The fuel system 80 includes a fuel tank (not shown) for storing the fuel therein and one or more fuel injector lines 82 for providing the 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, such as JetA, sustainable aviation fuel (SAF) including biofuels, hydrogen-based fuels (H-based fuels), and hydrogen-based fuels. 2 ) etc. Preferably, the fuel 67 is a hydrogen-based fuel (H 2 ), compared with fossil fuels or other types of fuels used in turbine engines, hydrogen-based fuels (H 2 ) produces a greater amount of water. In this way, a greater amount of steam can be generated from the combustion gases 66 of the hydrogen-based fuel than other types of fuels used in turbine engines.

[0050] Turbine engine 10 includes a steam system 90 in fluid communication with exhaust nozzle section 32. Steam system 90 generates steam 69 from exhaust gas in exhaust nozzle section 32. Steam system 90 includes one or more steam lines 92 to provide steam 69 to combustion section 26, as described in further detail below.

[0051] 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.

[0052] Figure 2 According to the present disclosure, along the turbine engine 10 ( Figure 1 ) of the longitudinal centerline axis 12 ( Figure 1 ) intercepted turbine engine 10 ( Figure 1 ) is a schematic cross-sectional view of a combustor 200. In an exemplary embodiment, the combustion section 26 ( Figure 1) includes a combustor 200 having a combustion chamber 202 defined by an outer liner 204 and an inner liner 206. The combustor 200 is an annular combustor. However, the combustor 200 may include any type of combustor, for example, an annular combustor, a double annular combustor, a can annular combustor, etc.

[0053] 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 outer liner 204. The outer liner 204 defines the radial outer boundary of the combustion chamber 202, and the inner liner 206 defines the radial inner boundary of the combustion chamber 202. The outer liner 204 and the inner liner 206 are radially inwardly spaced from the outer combustor casing 208 and the inner combustor casing 209 extending circumferentially around the outer liner 204 and the inner liner 206, respectively. At least one of the outer liner 204 or the inner liner 206 includes one or more air dilution holes 205, which are operable to guide the compressed air 65 through at least one of the outer liner 204 or the inner liner 206 and into the combustion chamber 202 to cool at least one of the outer liner 204 or the inner liner 206 (for example, by film cooling). The combustor 200 also includes an annular dome 210 coupled to the outer liner 204 and the inner liner 206. The annular dome 210 defines the upstream end or front end of the combustion chamber 202. The combustion chamber 202 extends from the annular dome 210 to a combustion chamber outlet 211 .

[0054] Multiple mixing components 212 ( Figure 2 The plurality of mixing assemblies 212 (only one of which is shown) are spaced circumferentially around the annular dome 210 to deliver a mixture of fuel and air to the combustion chamber 202. For example, the plurality of mixing assemblies 212 deliver a mixture of fuel and air to the combustion zone 203 of the combustion chamber 202, as described in further detail below. Figure 2 In the embodiment, each mixing assembly 212 includes a mixer 214 and a mixing assembly swirler 216. 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 mixer 214 of each of 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.

[0055] The burner 200 includes a steam system 90 ( Figure 1 ) is connected to the combustor steam system 220 in fluid communication with the steam system 90 for receiving the steam 69 from the steam system 90. The combustor steam system 220 includes one or more steam injectors 222 and a steam path 224. The one or more steam injectors 222 are arranged at the outer liner 204 or the inner liner 206 and are connected to the steam line 92 ( Figure 1 ) fluidly connected so that the steam system 90 supplies steam 69 to one or more steam injectors 222. The one or more steam injectors 222 may include discrete steam injectors spaced circumferentially around the combustion chamber 202, or may include a single steam injector annularly around the combustion chamber 202.

[0056] The steam path 224 is defined by the outer liner 204. For example, the steam path 224 is disposed within the outer liner 204. One or more steam injectors 222 supply steam 69 to the steam path 224 for cooling the outer liner 204. Although the steam path 224 is defined by the outer liner 204, the steam path 224 may be defined by the inner liner 206, or may be defined by both the outer liner 206 and the inner liner 206. The steam path 224 is also in fluid communication with the combustion chamber 202, such that the steam path 224 supplies steam 69 into the combustion chamber 202, as described in further detail below.

[0057] In operation, the combustor 200 receives heat from the HP compressor 24 ( Figure 1 ) is discharged from the combustion chamber 202. A portion of the compressed air 65 is directed through a plurality of mixing assemblies 212. For example, the compressed air 65 is directed through a mixing assembly swirler 216 of each of the plurality of mixing assemblies 212, and the mixing assembly swirler 216 causes the compressed air 65 to swirl. At the plurality of mixing assemblies 212, the compressed air 65 is mixed with fuel 67 from a plurality of fuel injectors 218 and discharged into the combustion chamber 202. The plurality of fuel injectors 218 inject the fuel 67 axially rearward into the combustion zone 203 of the combustion chamber 202 to generate a fuel flow 260. At the mixer 214 of each of the plurality of mixing assemblies 212, the fuel flow 260 is mixed with a first compressed air flow 262 to generate a fuel-air mixture. The fuel-air mixture is fuel-rich (e.g., a higher fuel-air ratio in the mixture) or fuel-lean (e.g., a lower fuel-air ratio in the mixture). The fuel-air mixture is ignited by an igniter (for clarity, Figure 2 ) is ignited to generate a flame within the combustion chamber 202 that combusts the fuel-air mixture and provides combustion gases 66 that are directed downstream to the HP turbine 28 ( Figure 1 ) of the first stage turbine nozzle. The flame burns within the combustion zone 203 (eg, adjacent to the mixer 214 and within the region of the annular dome 210) and generates combustion gases 66 within the combustion chamber 202.

[0058] Steam system 90( Figure 1 ) through one or more steam lines 92 ( Figure 1) is operable to supply steam 69 to a combustor steam system 220. For example, the steam system 90 supplies steam 69 to one or more steam injectors 222. The one or more steam injectors 222 are operable to direct the steam 69 into a steam path 224 within the outer liner 204 or the inner liner 206 to cool the outer liner 204 or the inner liner 206. The combustor steam system 220 is then operable to inject the steam 69 from the steam path 224 into the combustion chamber 202 to generate a steam injection flow 270. The combustor steam system 220 is operable to inject steam 69 to generate the steam injection flow 270 downstream of the combustion zone 203. In this way, the steam injection flow 270 does not directly interact with the flame generated by the fuel-gas mixture, thereby reducing the risk of flameout, compared to turbine engines and combustors without the benefit of the present disclosure, while also providing steam 69 into the combustion chamber to reduce the turbine engine 10 ( Figure 1 )’s specific fuel consumption (SFC).

[0059] The combustor 202 is operable to direct the combustion gases 66 from the combustion zone 203 downstream within the combustor 202. The combustion gases 66 from the combustion zone 203 are mixed with the steam injection stream 270 to generate a steam-combustion gas mixture 290 within the combustor 202. The combustor 202 is then operable to direct the steam-combustion gas mixture 290 to exit the combustor 202 through the combustor outlet 211, and the steam-combustion gas mixture 290 is directed downstream to the HP turbine 28 ( Figure 1 )'s first stage turbine nozzle.

[0060] 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, cruise. High power operation includes, for example, takeoff and climb. During low power operation, the burner steam system 220 does not inject steam 69 into the combustion chamber 202. During medium power operation and high power operation, the burner steam system 220 is operable to inject steam 69. During high power operation, the burner steam system 220 is operable to inject a larger amount of steam 69 than during medium power operation.

[0061] Injecting steam 69 downstream of the combustion zone 203 (e.g., downstream of the flame) provides flame stability, and the steam 69 in the combustion chamber 202 reduces the temperature of the combustion gases 66 in the combustion chamber 202. In this way, the flame operates at a higher temperature, and the steam 69 reduces the temperature of the flame. The combustor steam system 220 enables a water-to-air ratio (WAR) of steam 69 to compressed air 65 within the combustion chamber 202 up to 60%. For example, the WAR is 0.0% to 60%, and preferably 5% to 60%. In some embodiments, based on the operating conditions of the turbine engine (e.g., start-up, idle, taxi, take-off, climb, cruise, descent), the WAR is 0.0% to 60%. For example, the WAR in the combustion 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 ), steam 69 is injected into the combustion chamber 202 during any operating condition above idle conditions. Thus, the steam 69 injected into the combustion chamber 202 downstream of the combustion zone 203 enables reduced emissions (NOx emissions, nvPM emissions, CO emissions, noise) and reduced specific fuel capacity (SFC) while avoiding flameout within the combustion zone 203 as compared to turbine engines and combustors without the benefit of the present disclosure.

[0062] Figure 3 According to the present disclosure Figure 2 Detail 3 of FIG. 2 is a schematic cross-sectional view of a portion of the outer liner 204 of the combustor 200 . Figure 4 According to the present disclosure Figure 3 Details 4-4 of the interception Figure 3 A schematic cross-sectional plan view of a portion of the outer liner 204 is shown. Figure 3 As shown, the steam path 224 extends axially within the outer liner 204 and includes a front portion 230 axially forward of the one or more air dilution holes 205 and a rear portion 232 axially rearward of the one or more air dilution holes 205. Figure 4 As shown, the steam path 224 extends circumferentially within the outer liner 204. In this manner, the steam path 224 extends circumferentially about the longitudinal centerline axis 12 ( Figure 1 ) is ring-shaped.

[0063] The outer liner 204 includes one or more air dilution holes 205 for operably directing compressed air 65 through the outer liner 204 into the combustion chamber 202. The one or more air dilution holes 205 are spaced circumferentially around the outer liner 204. The combustor steam system 220 also includes one or more steam injection holes 226 defined through the outer liner 204 (or the inner liner 206). The one or more steam injection holes 226 provide fluid communication between the steam path 224 and the combustion chamber 202. The one or more steam injection holes 226 are operable to direct steam 69 from the steam path 224 through the outer liner 204 into the combustion chamber 202.

[0064] The one or more steam injection holes 226 are positioned downstream of the one or more air dilution holes 205. For example, the one or more steam injection holes 226 are positioned axially rearward of the one or more air dilution holes 205. In some embodiments, the one or more steam injection holes 226 are positioned at an axial position of at least 20% of the total length of the combustion chamber 202. In this manner, the one or more steam injection holes 226 are positioned downstream (e.g., axially rearward) of the combustion zone 203. The size of each of the one or more steam injection holes 226, the number of the one or more steam injection holes 226, and the circumferential spacing between corresponding steam injection holes in the one or more steam injection holes 226 are based on a desired amount of steam flow desired to generate the steam injection flow 270 within the combustion chamber 202. Additionally, although Figure 4 The one or more steam injection holes 226 are depicted as generally circular openings, but alternatively, other shapes may be implemented for the openings. For example, the one or more steam injection holes 226 may be an elliptical slot, or the like.

[0065] In operation, the combustor 200 and the combustor steam system 220 operate as described above. In particular, the combustor 200 is operable to direct the compressed air 65 through the one or more air dilution holes 205 to generate the second compressed air flow 264 in the combustion chamber 202. The second compressed air flow 264 helps to cool the combustion gases 66 from the combustion zone 203 as the combustion gases 66 are directed downstream through the combustion chamber 202. The combustor steam system 220 is operable to direct the steam 69 from the steam path 224 through the one or more steam injection holes 226 and into the combustion chamber 202 downstream of the combustion zone 203, thereby generating the steam injection flow 270 within the combustion chamber 202. In this manner, the steam injection flow 270 is downstream of the combustion zone 203. The one or more steam injection holes 226 are operable to direct the steam 69 radially into the combustion chamber 202. The steam injection stream 270 is operatively mixed with the combustion gases 66 from the combustion zone 203 to generate a steam combustion gas mixture 290, as described in detail above.

[0066] Figure 5is a schematic cross-sectional plan view of a portion of an outer liner 504 of a combustor 500 according to another embodiment. The combustor 500 is substantially similar to Figure 2 The combustor 200 of the embodiment of the present invention is a combustor 200 of the present invention and includes many components that are the same or similar to the combustor 200. The outer liner 504 includes one or more air dilution holes 505 and a combustor steam system 520. The combustor steam system 520 includes one or more steam injectors 522, a steam path 524 defined by the outer liner 504 (e.g., disposed within the outer liner 504), and one or more steam injection holes 526. The one or more steam injectors 522 are positioned upstream (e.g., axially forward) of the one or more air dilution holes 505. The steam path 524 is different from Figure 2 In particular, the steam path 524 does not extend annularly around the outer liner 504. Instead, the steam path 524 includes one or more discrete steam paths 524, and the one or more discrete steam paths 524 include one or more circumferentially extending portions 525 and one or more axially extending portions 527 fluidly coupled to the one or more circumferentially extending portions 525. In this manner, the steam path 524 defines one or more channels within the outer liner 504, rather than a continuously extending steam path, such as Figure 2 Steam path 224.

[0067] The steam path 524 has a generally zigzag shape extending axially rearward from the one or more steam injectors 522. For example, the one or more circumferentially extending portions 525 and the one or more axially extending portions 527 are fluidly coupled to each other to form a generally zigzag shape of the steam path 524. The steam path 524 extends axially rearward of the one or more air dilution holes 505. In this manner, the steam path 524 includes a front portion 530 axially forward of the one or more air dilution holes 505 and a rear portion 532 axially rearward of the one or more air dilution holes 505. The one or more steam injection holes 526 are in fluid communication with the steam path 524. The one or more steam injection holes 526 are positioned in the outer liner 504 at the rear portion 532 of the steam path 524, so that the one or more steam injection holes 526 are axially rearward of the one or more air dilution holes 505. The one or more steam injection holes 526 are positioned on one or more of the one or more circumferentially extending portions 525 of the steam path 524. One or more steam injection holes 526 may be positioned on one or more of the one or more axially extending portions 527 , or may be positioned on one or more circumferentially extending portions 525 of the steam path 524 and one or more axially extending portions 527 of the steam path 524 .

[0068] The operation of the burner 500 and the burner steam system 520 is substantially similar to Figure 2The burner 200 and the burner steam system 220. In particular, the burner steam system 520 is operable to direct steam 69 into a steam path 524 through one or more steam injectors 522. The steam path 524 is operable to direct steam 69 around the generally zigzag shape of the steam path 524. One or more steam injection holes 526 are operable to direct steam 69 therethrough to generate steam in a combustion chamber (e.g., Figure 2 The generally zigzag shape of the steam path 524 allows the steam 69 to cool various locations of the outer liner 504, rather than, for example, through Figure 2 The steam path 224 cools the entire outer liner. As needed, various shapes of steam paths 524 can be selected to cool the outer liner 504 at various locations.

[0069] Figure 6 FIG. 6 is a schematic cross-sectional plan view of a portion of an outer liner 604 of a combustor 600 according to another embodiment. The combustor 600 is substantially similar to Figure 2 The combustor 200 of the embodiment of the present invention is a combustor 200 of the present invention and includes many components that are the same or similar to the combustor 200. The outer liner 604 includes one or more air dilution holes 605 and a combustor steam system 620. The combustor steam system 620 includes one or more steam injectors 622, a steam path 624 defined by the outer liner 604 (e.g., disposed within the outer liner 604), and one or more steam injection holes 626. The one or more steam injectors 622 are positioned upstream (e.g., axially forward) of the one or more air dilution holes 605. The steam path 624 is different from Figure 2 In particular, the steam path 624 does not extend annularly around the outer liner 604. Instead, the steam path 624 includes one or more discrete steam paths 624, and the one or more discrete steam paths 624 include one or more circumferentially extending portions 625 and one or more axially extending portions 627 fluidly coupled to the one or more circumferentially extending portions 625. In this manner, the steam path 624 defines one or more channels within the outer liner 604, rather than a continuously extending steam path, such as Figure 2 Steam path 224.

[0070] One or more circumferentially extending portions 625 extend circumferentially from the one or more steam injectors 622. One or more axially extending portions 627 are fluidly coupled to the one or more circumferentially extending portions 625. One or more axially extending portions 627 extend axially rearwardly from the one or more circumferentially extending portions 625. One or more axially extending portions 627 extend axially rearwardly of the one or more air dilution holes 605. In this manner, the steam path 624 includes a front portion 630 axially forwardly of the one or more air dilution holes 605 and a rear portion 632 axially rearwardly of the one or more air dilution holes 605. The one or more axially extending portions 627 are spaced circumferentially around the outer liner 604.

[0071] The one or more steam injection holes 626 are in fluid communication with the steam path 624. The one or more steam injection holes 626 are positioned in the outer liner 604 at a rear portion 632 of the steam path 624 such that the one or more steam injection holes 626 are axially rearward of the one or more air dilution holes 605. The one or more steam injection holes 626 are positioned on one or more of the one or more axially extending portions 627 of the steam path 624. For example, each of the one or more axially extending portions 627 includes one or more of the one or more steam injection holes 626.

[0072] The operation of the burner 600 and the burner steam system 620 is substantially similar to Figure 2 The combustor 200 and the combustor steam system 220. In particular, the combustor steam system 620 is operable to direct steam 69 into a steam path 624 through one or more steam injectors 622. The steam path 624 is operable to direct steam 69 through one or more circumferentially extending portions 625 and through one or more axially extending portions 627. One or more steam injection holes 626 are operable to direct steam 69 therethrough to provide a steam source in a combustion chamber (e.g., Figure 2 The steam injection flow is generated in the combustion chamber 202 downstream of the combustion zone. One or more axial extensions 627 allow the steam 69 to cool various locations of the outer liner 604, rather than through Figure 2 The steam path 224 cools the entire outer liner. As needed, various shapes of steam paths 624 can be selected to cool the outer liner 604 at various locations.

[0073] Figure 7 is a schematic cross-sectional view of a portion of an outer liner 704 of a combustor 700 taken along a longitudinal centerline axis of the combustor 700 according to another embodiment. Figure 8 According to the present disclosure Figure 7 A schematic cross-sectional bottom view of a portion of the outer liner 704 taken at detail 8-8 in FIG. The combustor 700 is substantially similar to Figure 2The burner 200 of the embodiment. 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 includes a burner steam system 720. The burner steam system 720 includes one or more steam injectors 722, a steam path 724 defined by the outer liner 704 (e.g., arranged in the outer liner 704), and one or more steam injection holes 726. Figure 7 As shown, the steam path 724 extends axially within the outer liner 704. The steam path 724 may be similar to Figure 2 The steam path 224 may be annular about the longitudinal centerline axis, or may include one or more discrete steam paths similar to steam paths 524, 624. The outer liner 704 does not include one or more air dilution holes.

[0074] The combustor steam system 720 includes a steam manifold 723 and one or more steam dilution holes 728. The steam manifold 723 is radially fluidly coupled between the one or more steam injectors 722 and the steam path 724. The steam manifold 723 allows the pressure of the steam 69 to be reduced before the steam 69 flows to the steam path 724. The steam manifold 723 is sized and shaped to provide a substantially uniform distribution of the steam 69 to the one or more steam injection holes 726 and the one or more steam dilution holes 728. In this manner, the steam manifold 723 ensures a controlled and stable supply of steam 69 to various locations within the combustor steam system 720 at a desired pressure. The steam manifold 723 may include a plurality of discrete steam manifolds spaced circumferentially around the combustion chamber 202, or may include a single steam manifold annularly around the combustion chamber 202.

[0075] One or more steam dilution holes 728 are spaced circumferentially about outer liner 704 and are operable to direct steam 69 therethrough into combustion chamber 202. One or more steam dilution holes 728 are larger than one or more steam injection holes 726. In this manner, one or more steam dilution holes 728 are operable to direct a greater amount of steam 69 into combustion chamber 202 than one or more steam injection holes 726. The size of each of the one or more steam dilution holes 728, the number of the one or more steam dilution holes 728, and the circumferential spacing between respective ones of the one or more steam dilution holes 728 are based on a desired amount of steam flow within combustion chamber 202. Additionally, while Figure 7 and Figure 8 The one or more steam dilution holes 728 are depicted as generally circular openings, but alternatively other shapes may be implemented for the openings. For example, the one or more steam dilution holes 728 may be an elliptical slot, or the like.

[0076] The one or more steam injection holes 726 are positioned downstream of the one or more steam dilution holes 728. For example, the one or more steam injection holes 726 are positioned axially rearward of the one or more steam dilution holes 728. In some embodiments, the one or more steam injection holes 726 are positioned at least 25% of the total length of the combustion chamber 202.

[0077] The steam path 724 includes a front portion 730 located in front of the one or more steam dilution holes 728 and a rear portion 732 behind the one or more steam dilution holes 728. The outer liner 704 includes one or more front steam inlet holes 733 and one or more rear steam inlet holes 735. The one or more front steam inlet holes 733 are positioned in front of the one or more steam dilution holes 728 and provide fluid communication from the steam manifold 723 to the front portion 730 of the steam path 724. The one or more rear steam inlet holes 735 are positioned behind the one or more steam dilution holes 728 and provide fluid communication from the steam manifold 723 to the rear portion 733 of the steam path 724.

[0078] The operation of the burner 700 and the burner steam system 720 is substantially similar to Figure 2 The combustor 200 and the combustor steam system 220 are shown. In particular, the combustor steam system 720 is operable to direct steam 69 through one or more steam injectors 722, through the steam manifold 723, and into the steam path 724 to cool the outer liner 704. For example, the steam 69 flows through one or more front steam inlet holes 733 and enters the front portion 730 of the steam path 724. The steam 69 also flows through one or more rear steam inlet holes 735 and enters the rear portion 733 of the steam path 724. The one or more front steam inlet holes 733 and the one or more rear steam inlet holes 735 can be sized to control the pressure drop between the front portion 730 and the rear portion 733 (e.g., in front of the one or more steam dilution holes 728 and rear of the one or more steam dilution holes 728). In some embodiments, the one or more front steam inlet holes 733 and the one or more rear steam inlet holes 735 include substantially equal sizes so that there is a single pressure drop in front of the one or more steam dilution holes 728 and rear of the one or more steam dilution holes 728. For example, the pressure drop through the one or more front steam inlet holes 733 is substantially equal to the pressure drop through the one or more rear steam inlet holes 735. In some embodiments, the one or more front steam inlet holes 733 are sized differently (e.g., larger or smaller) than the one or more rear steam inlet holes 735, such that the pressure drop in front of the one or more steam dilution holes 728 is different from the pressure drop behind the one or more steam dilution holes 728, such that there are multiple pressure drops across the one or more steam dilution holes 728.

[0079] The one or more steam injection holes 726 are operable to direct steam 69 therethrough to generate a first steam injection stream 770 within the combustion chamber 202. The one or more steam dilution holes 728 are operable to direct steam 69 therethrough to generate a second steam injection stream 772 and enter the combustion chamber 202. The second steam injection stream 772 includes a greater amount of steam 69 than the first steam injection stream 770. For example, the one or more steam dilution holes 728 and the one or more steam injection holes 726 are sized such that the second steam injection stream includes more than 50% of the steam 69 injected into the combustion chamber 202 and the first steam injection stream includes less than 50% of the steam 69 injected into the combustion chamber 220. In some embodiments, the second steam injection stream includes 40% to 100% of the steam 69 and the first steam injection stream includes 0.0% to 60% of the steam 69. The combustion gases 66 from the combustion zone mix with the first steam injection stream 770 and the second steam injection stream 772 to generate a steam combustion gas mixture 790 that is directed downstream and exits the combustion chamber 202.

[0080] Fig. 9 is a schematic cross-sectional bottom view of a portion of an outer liner 904 of a combustor 900 according to another embodiment. The combustor 900 is substantially similar to Figure 2 and Figure 7 The same reference numerals will be used for the components of the burner 900 that are the same as or similar to the components of the above-mentioned burners 200 and 700. The above description of these components also applies to the present embodiment, and the detailed description of these components is omitted here. The burner 900 includes a burner steam system 920, which is substantially similar to the burner steam system 920. Figure 7 The combustor steam system 720 of the embodiment of the present invention. The combustor steam system 920 includes one or more steam injection holes 926 and one or more steam dilution holes 928. The combustor 900 also includes one or more air dilution holes 905. The one or more steam dilution holes 928 and the one or more air dilution holes 905 are spaced and alternated circumferentially around the outer liner 904.

[0081] The operation of the burner 900 and the burner steam system 920 is substantially similar to Figure 2 and Figure 7 The burner 200, 700 and the burner steam system 220, 720. In particular, one or more air dilution holes 905 are operable to dilute the compressed air 65 ( Figure 2 ) is directed to the combustion chamber 202 ( Figure 2 One or more steam injection holes 926 and one or more steam dilution holes 928 are operable to direct steam 69 into the combustion chamber 202, as described above with respect to Figure 7 Detailed.

[0082] Fig.10 is a schematic cross-sectional view of a portion of an outer liner 1004 of a combustor 1000 taken along a longitudinal centerline axis of the combustor 1000 according to another embodiment. Fig.11 According to the present disclosure Fig.10 A schematic cross-sectional bottom view of a portion of the outer liner 1004 taken at detail 11-11 in FIG. The combustor 1000 is substantially similar to Figure 2 and Figure 7 The burner 200, 700 of the present invention. The same reference numerals will be used for components of the burner 1000 that are the same as or similar to the components of the above-mentioned burners 200, 700. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here. The burner 1000 includes a burner steam system 1020. The burner steam system 1020 includes one or more steam injectors 1022, a steam path 1024 defined by the outer liner 1004 (for example, disposed within the outer liner 1004), a steam manifold 1023, one or more steam injection holes 1026, and one or more steam dilution holes 1028.

[0083] The combustor steam system 1020 also includes one or more steam slots 1029 positioned axially rearward of the one or more steam dilution holes 1028 and axially forward of the one or more steam injection holes 1026. The one or more steam slots 1029 are arcuate slots operable to direct steam 69 therethrough and into the combustion chamber 202. The size of each of the one or more steam slots 1029, the number of the one or more steam slots 1029, and the circumferential spacing between corresponding ones of the one or more steam slots 1029 are based on the desired amount of steam flow within the combustion chamber 202. Additionally, although Fig.10 and Fig.11 The one or more steam slots 1029 are depicted as generally arcuate openings, but alternatively, other shapes may be implemented for the openings. For example, the one or more steam slots 1029 may be generally straight slots, etc.

[0084] The steam path 1024 includes a front portion 1030 in front of the one or more steam dilution holes 1028 and a rear portion 1032 behind the one or more steam dilution holes 1028. The outer liner 1004 includes one or more front steam inlet holes 1033 and one or more rear steam inlet holes 1035. The one or more front steam inlet holes 1033 are positioned in front of the one or more steam dilution holes 1028 and provide fluid communication from the steam manifold 1023 to the front portion 1030 of the steam path 1024. The one or more rear steam inlet holes 1035 are positioned behind the one or more steam dilution holes 1028 and provide fluid communication from the steam manifold 1023 to the rear portion 1033 of the steam path 1024.

[0085] The operation of the burner 1000 and the burner steam system 1020 is substantially similar to Figure 2 and Figure 7 The combustor 200, 700 and the combustor steam system 220, 720 of the embodiment of the present invention are shown in FIG. 1. In particular, the combustor steam system 1020 is operable to direct steam 69 through one or more steam injectors 1022, through a steam manifold 1023, and into a steam path 1024 to cool the outer liner 1004. For example, the steam 69 flows through one or more front steam inlet holes 1033 and enters a front portion 1030 of the steam path 1024. The steam 69 also flows through one or more rear steam inlet holes 1035 and enters a rear portion 1033 of the steam path 1024.

[0086] The one or more steam injection holes 1026 are operable to direct steam 69 therethrough to generate a first steam injection stream 1070 within the combustion chamber 202. The one or more steam dilution holes 1028 are operable to direct steam 69 therethrough to generate a second steam injection stream 1072 and enter the combustion chamber 202. The one or more steam slots 1029 are operable to direct steam 69 therethrough to generate a third steam injection stream 1074 within the combustion chamber 202. The third steam injection stream 1074 helps to suppress the wake or turbulence generated by the second steam injection stream 1072 passing through the one or more steam dilution holes 1028. The combustion gases 66 from the combustion zone mix with the first steam injection stream 1070, the second steam injection stream 1072, and the third steam injection stream 1074 to generate a steam combustion gas mixture 1090 that is directed downstream and exits the combustion chamber 202.

[0087] Fig.12 1 is a schematic cross-sectional view of a portion of an outer liner 1204 of a combustor 1200 taken along a longitudinal centerline axis of the combustor 1200 according to another embodiment. The combustor 1200 is substantially similar to Figure 2 The burner 1200 is a burner 200 and includes many components that are the same or similar to the burner 200. The same reference numerals will be used for components of the burner 1200 that are the same 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 herein. The burner 1200 includes a burner steam system 1220. The burner steam system 1220 includes one or more steam injectors 1222, a steam path 1224 defined by the outer liner 1204 (e.g., disposed within the outer liner 1204), and one or more steam injection holes 1226. As Fig.12 As shown, steam path 1224 extends axially within outer liner 1204. Steam path 1224 may be similar to Figure 2The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6 The steam paths 524, 624 may be one or more discrete steam paths. The steam path 1224 may include a front portion 1230 and a rear portion 1232.

[0088] The outer liner 1204 includes one or more air dilution holes 1205 and one or more air impingement holes 1207. The one or more air dilution holes 1205 are operable to direct the compressed air 65 into the combustion chamber 202. The one or more air impingement holes 1207 are operable to direct the compressed air 65 into the steam path 1224, as further described below. The one or more air impingement holes 1207 are disposed through the radially outer portion of the outer liner 1204 to operably direct the compressed air 65 into the steam path 1224. In some embodiments, the outer liner 1204 does not include the one or more air impingement holes 1207.

[0089] The combustor steam system 1220 includes a steam manifold 1223 fluidly coupled to the one or more steam injectors 1222 downstream of the one or more steam injectors 1222. The combustor steam system 1220 also includes one or more steam injector lines 1240 fluidly coupled to the steam manifold 1223 downstream of the steam manifold 1223. The one or more steam injector lines 1240 are fluidly coupled to the steam path 1224 for operably directing the steam 69 from the steam manifold 1223 to the steam path 1224. For example, the one or more steam injector lines 1240 are disposed at a rear portion 1232 of the steam path 1224. The steam path 1224 is disposed within the outer liner 1204 axially rearward of the one or more air dilution holes 1205. The one or more air impingement holes 1207 are disposed axially forward of the one or more steam injector lines 1240, such that the one or more air impingement holes 1207 are disposed at a front portion 1230 of the steam path 1224.

[0090] The combustor steam system 1220 includes one or more steam cooling holes 1231 disposed through the outer liner 1204, the one or more steam cooling holes 1231 providing fluid communication from the steam path 1224 and the combustion chamber 202. The one or more steam cooling holes 1231 are angled axially rearward relative to the longitudinal centerline axis of the combustor 1200 so that the steam 69 flows axially rearward through the one or more steam cooling holes 1231 to provide film cooling on the outer liner 1204. In this manner, the one or more steam cooling holes 1231 guide the steam 69 axially along the outer liner 1204 to film cool the outer liner 1204. In some embodiments, the one or more steam cooling holes 1231 are angled axially forward so that the steam 69 flows axially forward through the one or more steam cooling holes 1231 into the combustion chamber 202. In some embodiments, the one or more steam cooling holes 1231 include one or more steam cooling holes 1231 angled axially rearward and one or more steam cooling holes 1231 angled axially forward.

[0091] The one or more steam cooling holes 1231 are spaced circumferentially about the outer liner 1204 and spaced axially on the outer liner 1204. The one or more steam cooling holes 1231 include one or more steam cooling holes 1231 disposed axially forward of the one or more steam injection holes 1226. The one or more steam cooling holes 1231 also include one or more steam cooling holes 1231 disposed axially rearward of the one or more steam injection holes 1226. The size of each of the one or more steam cooling holes 1231, the number of the one or more steam cooling holes 1231, and the circumferential spacing between corresponding steam cooling holes in the one or more steam cooling holes 1231 are based on a desired amount of steam flow to film cool the outer liner 1204. Additionally, although Fig.12 The one or more steam cooling holes 1231 are depicted as generally circular openings, but alternatively other shapes may be implemented for the openings. For example, the one or more steam cooling holes 1231 may be an elliptical slot, etc.

[0092] The operation of the burner 1200 and the burner steam system 1220 is substantially similar to Figure 2 The combustor 200 and the combustor steam system 220 are shown. In particular, the combustor 1200 is operable to direct the compressed air 65 into the combustion chamber 202 through one or more air dilution holes 1205 to generate a second compressed air flow 1264 in the combustion chamber 202. The combustor 1200 is operable to direct the compressed air 65 into the steam path 1224 through one or more air impingement holes 1207 to generate an impingement air flow 1265 in the steam path 1224. The impingement air flow 1265 helps to cool the steam 69 in the steam path 1224 because the steam 69 in the steam path 1224 absorbs heat from the outer liner 1204 to cool the outer liner 1204.

[0093] The combustor steam system 1220 is operable to direct steam 69 through one or more steam injectors 1222, through a steam manifold 1223, through one or more steam injector lines 1240, and into a steam path 1224 to cool the outer liner 1204. The steam path 1224 is operable to direct the steam 69 axially forward so that the steam 69 flows within the steam path 1224 in a direction opposite to the combustion gases 66 within the combustion chamber 202. For example, the steam 69 flows from the rear portion 1232 to the front portion 1230. One or more steam injection holes 1226 are operable to direct steam 69 therethrough to generate a steam injection flow 1270 within the combustion chamber 202. One or more steam cooling holes 1231 are operable to direct steam 69 therethrough to generate a steam cooling flow 1276 and into the combustion chamber 202 to film cool the outer liner 1204. Combustion gases 66 from the combustion zone mix with steam injection flow 1270 and steam cooling flow 1276 to generate a steam-combustion gas mixture 1290 that is channeled downstream and out of combustor 202 .

[0094] Fig.13 1 is a schematic cross-sectional view of a portion of an outer liner 1304 of a combustor 1300 taken along a longitudinal centerline axis of the combustor 1300 according to another embodiment. The combustor 1300 is substantially similar to Figure 2 The combustor 1300 is a combustor 200 of the type of embodiment of the present invention and includes many of the same or similar components as the combustor 200. The combustor 1300 includes one or more air dilution holes 1305 operable to direct the compressed air 65 therethrough. The combustor 1300 includes a heat shield 1352 coupled to the outer liner 1304 for protecting the outer liner 1304 from the hot combustion gases 66. The heat shield 1352 is secured to the outer liner 1304 by one or more fasteners (at Fig.13 ) (not shown in the view of ) is connected to the outer liner 1304 by, for example, bolts, etc.

[0095] The combustor 1300 includes a combustor steam system 1320. The combustor steam system 1320 includes one or more steam injectors 1322, a steam path 1324, and one or more steam injection holes 1326. The steam path 1324 is defined by the outer liner 1304 and the heat shield 1352. For example, the steam path 1324 extends axially between the outer liner 1304 and the heat shield 1352. The steam path 1324 can be similar to Figure 2 The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6The steam path 1324 includes a front portion 1330 and a rear portion 1332. The front portion 1330 is axially forward of the one or more air dilution holes 1305, and the rear portion 1332 is axially rearward of the one or more air dilution holes 1305. The front portion 1330 is fluidly separated from the rear portion 1332, thereby preventing steam 69 from flowing from the rear portion 1332 to the front portion 1330.

[0096] The one or more air dilution holes 1305 include a dilution hole insert 1309 disposed within the one or more air dilution holes 1305. The dilution hole insert 1309 prevents the compressed air 65 from flowing into the steam path 1324 and prevents or minimizes the steam 69 from flowing from the steam path 1324 through the one or more air dilution holes 1305.

[0097] The burner steam system 1320 includes a steam manifold 1323 fluidly coupled to the one or more steam injectors 1322 downstream of the one or more steam injectors 1322. The burner steam system 1320 also includes one or more first steam injector lines 1340 fluidly coupled to the steam manifold 1323 downstream of the steam manifold 1323. The one or more first steam injector lines 1340 are fluidly coupled to the rear portion 1332 of the steam path 1324 for operably directing steam 69 from the steam manifold 1323 to the steam path 1324. The burner steam system 1320 includes one or more steam manifold lines 1342 and one or more second steam injector lines 1344. The one or more steam manifold lines 1342 are fluidly coupled to the steam manifold 1323 and the one or more second steam injector lines 1344 for operably directing steam 69 axially forward from the steam manifold 1323 to the one or more second steam injector lines 1344. One or more second steam injector lines 1344 are fluidly coupled to the front portion 1330 of the steam path 1324 for operably directing the steam 69 from the one or more steam manifold lines 1342 to the front portion 1330 of the steam path 1324 .

[0098] The combustor steam system 1320 includes one or more steam injection holes 1326 disposed through the heat shield 1352, the one or more steam injection holes 1326 providing fluid communication from the steam path 1324 to the combustion chamber 202. The one or more steam injection holes 1326 are angled relative to the longitudinal centerline axis of the combustor 1300 to provide film cooling on the heat shield 1352. The one or more steam injection holes 1326 are spaced circumferentially around the heat shield 1352 and axially on the heat shield 1352. The one or more steam injection holes 1326 are disposed at the front 1330 and the rear 1332 of the steam path 1324.

[0099] The operation of the burner 1300 and the burner steam system 1320 is substantially similar to Figure 2 The combustor 200 and the combustor steam system 220. In particular, the combustor 1300 is operable to direct the compressed air 65 into the combustion chamber 202 through one or more air dilution holes 1305 to generate a second compressed air flow 1364 within the combustion chamber 202.

[0100] The combustor steam system 1320 is operable to direct steam 69 through one or more steam injectors 1322, through a steam manifold 1323, through one or more first steam injector lines 1340, and into an aft portion 1332 of a steam path 1324 to cool the outer liner 1304 and the heat shield 1352 at the aft portion 1332. The steam path 1324 is operable to direct the steam 69 axially forward so that the steam 69 flows within the steam path 1324 in a direction opposite to the combustion gases 66 within the combustion chamber 202. The steam manifold 1323 is operable to direct the steam 69 through one or more steam manifold lines 1342, through one or more second steam injector lines 1344, and into a forward portion 1330 of the steam path 1324 to cool the outer liner 1304 and the heat shield 1352 at the forward portion 1330.

[0101] One or more steam injection holes 1326 are operable to direct steam 69 therethrough to generate steam injection streams 1370 within combustion chamber 202 at a front portion 1330 and a rear portion 1332 of steam path 1324. Steam injection stream 1370 from rear portion 1332 includes a greater amount of steam 69 than steam injection stream 1370 from front portion 1330. For example, steam 69 injected from rear portion 1332 includes 50% to 80% of steam 69 from steam path 1324, and steam 69 injected from front portion 1330 includes 20% to 50% of steam 69 from steam path 1324. Combustion gases 66 from the combustion zone mix with steam injection stream 1370 to generate a steam-combustion gas mixture 1390 that is directed downstream and exits combustion chamber 202.

[0102] Fig.14 1 is a schematic cross-sectional view of a portion of an outer liner 1404 of a combustor 1400 taken along a longitudinal centerline axis of the combustor 1400 according to another embodiment. The combustor 1400 is substantially similar to Figure 2The combustor 200 of the embodiment of the present invention is a combustor 200 of the present invention, and includes many components that are the same or similar to the combustor 200. The same reference numerals will be used for components of the combustor 1400 that are the same or similar to the components of the combustor 200 described above. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted herein. The combustor 1400 includes one or more air dilution holes 1405 that are operable to guide the compressed air 65 therethrough. The combustor 1400 includes a heat shield 1452 coupled to the outer liner 1404 for protecting the outer liner 1402 from the hot combustion gases 66. The one or more air dilution holes 1405 include a dilution hole insert 1409 disposed within the one or more air dilution holes 1405. The one or more air dilution holes 1405 also include a dilution hole support 1413 that extends axially through the one or more air dilution holes 1405 to absorb thermal expansion between the heat shield 1452 and the outer liner 1404. In this manner, the dilution hole supports 1413 help prevent one or more of the air dilution holes 1405 from closing due to thermal expansion of the outer liner 1404 or the heat shield 1452. The dilution hole supports 1413 also help prevent or minimize mixing of the steam 69 from the steam path 1424 and the compressed air 65 from the air path 1415 of the combustor 1400.

[0103] The air path 1415 is defined by the outer liner 1404 and the heat shield 1452. For example, the air path 1415 is defined between the outer liner 1404 and the heat shield 1452 axially forward of the one or more air dilution holes 1405. The combustor 1400 includes one or more air impingement holes 1407 disposed through the outer liner 1404 and in fluid communication with the air path 1415. The one or more air impingement holes 1407 are disposed axially forward of the one or more air dilution holes 1405. The combustor 1400 includes one or more air injection holes 1408 disposed through the heat shield 1452 for providing fluid communication between the air path 1415 and the combustion chamber 202 upstream of the one or more air dilution holes 1405. The one or more air injection holes 1408 are angled axially rearward relative to the longitudinal centerline axis of the combustor 1400 so that the compressed air 65 flows axially rearward through the one or more air injection holes 1408 to provide air film cooling on the heat shield 1452. In this manner, the one or more air injection holes 1408 direct the compressed air 65 axially along the heat shield 1452 to film cool the heat shield 1452. In some embodiments, the one or more air injection holes 1408 are angled axially forward so that the compressed air 65 flows axially forward through the one or more air injection holes 1408 into the combustion chamber 202. In some embodiments, the one or more air injection holes 1408 include one or more air injection holes 1408 angled axially backward and one or more air injection holes 1408 angled axially forward.

[0104] The combustor 1400 includes a combustor steam system 1420. The combustor steam system 1420 includes one or more steam injectors 1422, a steam path 1424 disposed between the outer liner 1404 and the heat shield 1452, and one or more steam injection holes 1426. Fig.14 As shown, the steam path 1424 extends axially between the outer liner 1404 and the thermal shield 1452. The steam path 1424 may be similar to Figure 2 The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6 The steam paths 524, 624 are one or more discrete steam paths. The steam path 1424 is disposed axially rearward of the one or more air dilution holes 1405. The steam path 1424 is fluidly separated from the air path 1415, thereby preventing the steam 69 from flowing from the steam path 1424 to the air path 1415.

[0105] The combustor steam system 1420 includes a steam manifold 1423 and one or more steam injector lines 1440. The one or more steam injector lines 1440 are fluidly coupled to the steam path 1424 for operably directing steam 69 from the steam manifold 1423 to the steam path 1424. The combustor steam system 1420 includes one or more steam injection holes 1426 disposed through the heat shield 1452, the one or more steam injection holes 1426 providing fluid communication from the steam path 1424 to the combustion chamber 202 axially rearward of the one or more air dilution holes 1405. The one or more steam injection holes 1426 are angled axially rearward relative to the longitudinal centerline axis of the combustor 1400 to provide steam film cooling on the heat shield 1452. In some embodiments, the one or more steam injection holes 1426 are angled axially forward, or include one or more steam injection holes 1426 angled axially rearward and one or more steam injection holes 1426 angled axially forward.

[0106] The operation of the burner 1400 and the burner steam system 1420 is substantially similar to Figure 2 The combustor 200 and the combustor steam system 220 are shown in FIG. 1 . In particular, the combustor 1400 is operable to direct the compressed air 65 into the combustion chamber 202 through the one or more air dilution holes 1405 to generate a second compressed air flow 1464 within the combustion chamber 202. The combustor 1400 is operable to direct the compressed air 65 into the air path 1415 through the one or more air impingement holes 1407 to generate an impingement air flow 1465 within the air path 1415. The one or more air injection holes 1408 are operable to direct the compressed air 65 (e.g., the impingement air flow 1465) from the air path 1415 into the combustion chamber 202 to generate an air injection flow 1466 to cool the heat shield 1452 through film cooling.

[0107] The combustor steam system 1420 is operable to direct steam 69 through one or more steam injectors 1422, through a steam manifold 1423, through one or more steam injector lines 1440, and into a steam path 1424 to cool the outer liner 1404 and the heat shield 1452 axially rearward of the one or more air dilution holes 1405. The steam path 1424 is operable to direct the steam 69 axially forward so that the steam 69 flows within the steam path 1424 in a direction opposite to the combustion gases 66 within the combustion chamber 202. The one or more steam injection holes 1426 are operable to direct steam 69 therethrough to generate a steam injection flow 1470 within the combustion chamber 202 downstream of the one or more air dilution holes 1405. The combustion gases 66 from the combustion zone are mixed with the second compressed air flow 1464, the air injection flow 1466, and the steam injection flow 1470 to generate an air-steam-combustion gas mixture 1490 that is directed downstream and exits the combustion chamber 202.

[0108] Fig.15 is a schematic cross-sectional view of a portion of an outer liner 1504 of a combustor 1500 taken along a longitudinal centerline axis of the combustor 1500 according to another embodiment. The combustor 1500 is substantially similar to Figure 2 and Fig.14 The combustor 1500 is a combustor 200, 1400 of the present invention and includes many components that are the same or similar to the combustor 200, 1400. The same reference numerals will be used for components of the combustor 1500 that are the same or similar to the components of the combustor 200, 1400 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 combustor 1500 includes a heat shield 1552 coupled to the outer liner 1504 for protecting the outer liner 1504 from the hot combustion gases 66.

[0109] The combustor 1500 includes a combustor steam system 1520. The combustor steam system 1520 includes one or more steam injectors 1522, a steam path 1524 defined by the outer liner 1504 and the heat shield 1552 (e.g., disposed between the outer liner 1504 and the heat shield 1552), and one or more steam injection holes 1526. Fig.15 As shown, steam path 1524 extends axially between outer liner 1504 and thermal shield 1552. Steam path 1524 may be similar to Figure 2 The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6The steam paths 524, 624 are one or more discrete steam paths. The steam path 1524 is disposed axially rearward of the one or more air dilution holes 1405. The steam path 1524 is fluidly separated from the air path 1415, thereby preventing the steam 69 from flowing from the steam path 1524 to the air path 1415.

[0110] The burner steam system 1520 includes a steam manifold 1523. The steam manifold 1523 includes a steam manifold wall 1556 radially disposed between the steam manifold 1523 and the steam path 1524. The steam manifold wall 1556 includes one or more steam impingement holes 1558 disposed therethrough, the one or more steam impingement holes 1558 operable to direct steam 69 from the steam manifold 1523 to the steam path 1524, as described in further detail below.

[0111] The operation of the burner 1500 and the burner steam system 1520 is substantially similar to Figure 2 and Fig.14 200, 1400 and the combustor steam system 220, 1420. In particular, the combustor steam system 1520 is operable to direct steam 69 through one or more steam injectors 1522, through the steam manifold 1523, and through one or more steam impingement holes 1558 to generate a steam impingement flow 1575 within the steam path 1524. In this manner, the steam impingement flow 1575 impinges on the heat shield 1552 within the steam path 1524 to cool the heat shield 1552. One or more steam injection holes 1526 are operable to direct steam 69 therethrough to generate a steam injection flow 1570 downstream of one or more air dilution holes 1405 within the combustion chamber 202. The combustion gases 66 from the combustion zone are mixed with the air injection flow 1466 and the steam injection flow 1570 to generate an air-steam-combustion gas mixture 1590 that is directed downstream and exits the combustion chamber 202.

[0112] Fig.16 1 is a schematic cross-sectional view of a portion of an outer liner 1604 of a combustor 1600 taken along a longitudinal centerline axis of the combustor 1600 according to another embodiment. The combustor 1600 is substantially similar to Figure 2 , Fig.14 and Fig.15The burner 1600 is a burner 200, 1400, 1500 of the embodiment of the present invention and includes many components that are the same or similar to the burners 200, 1400, 1500. The same reference numerals will be used for components of the burner 1600 that are the same or similar to the components of the burners 200, 1400, 1500 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 1600 includes a heat shield 1652 coupled to the outer liner 1604 for protecting the outer liner 1604 from the hot combustion gases 66. However, the burner 1600 does not include a heat shield 1652 similar to the heat shield 1652 of the burner 1600. Fig.14 The air path 1415 is an air path.

[0113] The combustor 1600 includes a combustor steam system 1620. The combustor steam system 1620 includes one or more steam injectors 1622, a steam path 1624 defined by the outer liner 1604 and the heat shield 1652 (e.g., disposed between the outer liner 1604 and the heat shield 1652), and one or more steam injection holes 1626. Fig.16 As shown, the steam path 1624 extends axially between the outer liner 1604 and the thermal shield 1652. The steam path 1624 may be similar to Figure 2 The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6 The combustor steam system 1620 includes one or more discrete steam paths of the steam paths 524, 624. The steam path 1624 includes a front portion 1630 axially forward of the one or more air dilution holes 1405 and a rear portion 1632 axially rearward of the one or more air dilution holes 1405. The rear portion 1632 is fluidly coupled to the front portion 1630 so that the steam 69 flows from the rear portion 1632 to the front portion 1630, as further described below. The combustor steam system 1620 includes a steam manifold 1623 extending in the front portion 1630 and the rear portion 1632. The steam manifold 1623 includes a steam manifold wall 1656 radially disposed between the steam manifold 1623 and the steam path 1624. The steam manifold wall 1656 includes one or more steam impingement holes 1658 disposed therethrough that are operable to direct steam 69 from the steam manifold 1623 to the front portion 1630 and the rear portion 1632 of the steam path 1624, as described in further detail below.

[0114] The operation of the burner 1600 and the burner steam system 1620 is substantially similar to Figure 2 , Fig.14 and Fig.15The burners 200, 1400, 1500 and the burner steam systems 220, 1420, 1520 of the present invention are shown in FIG. 1. In particular, the burner steam system 1620 is operable to direct steam 69 through one or more steam injectors 1622, through a steam manifold 1623, and through one or more steam impingement holes 1658 to generate a steam impingement flow 1675 within a rear portion 1632 of a steam path 1624. The steam manifold 1623 is operable to direct steam 69 from the rear portion 1632 to the front portion 1630. For example, although in Fig.16 1405, the front portion 1630 and the rear portion 1632 are fluidly coupled around the one or more air dilution holes 1405 so that the steam 69 flows from the rear portion 1632 to the front portion 1630 around the one or more air dilution holes 1405. The steam 69 then flows through the one or more steam impingement holes 1658 to generate a steam impingement flow 1675 within the front portion 1630 of the steam path 1624. In this manner, the steam impingement flow 1675 impinges on the heat shield 1652 within the steam path 1624 to cool the heat shield 1652. The one or more steam injection holes 1626 are operable to direct the steam 69 therethrough to generate steam injection flows 1670 from the front portion 1630 and the rear portion 1632 upstream and downstream of the one or more air dilution holes 1405 within the combustion chamber 202. The steam injection flow 1670 from the rear portion 1632 includes a greater amount of steam 69 than the steam injection flow 1670 from the front portion 1630. For example, steam 69 injected from rear portion 1632 comprises 50% to 80% of steam 69 from steam path 1624, and steam 69 injected from front portion 1630 comprises 20% to 50% of steam 69 from steam path 1624. Combustion gases 66 from the combustion zone mix with steam injection stream 1670 to generate an air-steam-combustion gas mixture 1690 that is directed downstream and out of combustor 202.

[0115] Fig.17 1700 is a schematic cross-sectional view of a portion of an outer liner 1704 of a combustor 1700 taken along a longitudinal centerline axis of the combustor 1700 according to another embodiment. The combustor 1700 is substantially similar to Figure 2 and Fig.16 The burner 200, 1600 of the embodiment is described above and includes many components that are the same or similar to the burners 200, 1600. The same reference numerals will be used for components of the burner 1700 that are the same or similar to the components of the above-mentioned burners 200, 1600. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here.

[0116] Burner 1700 includes a burner steam system 1720. Burner steam system 1720 is substantially similar to Fig.16The burner steam system 1720 of the embodiment of the present invention is a burner steam system 1620. The burner steam system 1720 includes one or more steam injectors 1722, including a first steam injector 1722a and a second steam injector 1722b disposed at the outer liner 1704. The first steam injector 1722a is in fluid communication with the front portion 1630. The second steam injector 1722b is in fluid communication with the rear portion 1632. The operation of the burner 1700 and the burner steam system 1720 is substantially similar to the burner 1600 and the burner steam system 1620, respectively. In particular, the burner steam system 1720 is operable to direct steam 69 through the first steam injector 1722a and into the front portion 1630. The burner steam system 1720 is operable to direct steam 69 through the second steam injector 1722b and into the rear portion 1632.

[0117] Fig.18 1 is a schematic cross-sectional view of a portion of an outer liner 1804 of a combustor 1800 taken along a longitudinal centerline axis of the combustor 1800 according to another embodiment. The combustor 1800 is substantially similar to Figure 2 The burner 1800 is a burner 200 of the embodiment of the present invention and includes many components that are the same or similar to the burner 200. The same reference numerals will be used for components of the burner 1800 that are the same 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 herein. The burner 1800 includes one or more air dilution holes 1805 that are operable to direct the compressed air 65 therethrough. The one or more air dilution holes 1805 include a dilution hole insert 1809 and a dilution hole support 1813. The burner 1800 includes a heat shield 1852 coupled to the outer liner 1804 for protecting the outer liner 1802 from the hot combustion gases 66.

[0118] The combustor 1800 includes a plurality of mixing assemblies 1812 including mixers 1814 and fuel injectors 1818 disposed through the annular dome 210. The fuel injectors 1818 include a fuel supply line 1819 and a fuel path 1821. The fuel supply line 1819 is positioned axially rearward of the one or more air dilution holes 1805 and extends radially to the outer liner 1804. The fuel path 1821 is disposed within the outer liner 1804 and is in fluid communication with the fuel supply line 1819 and the fuel injectors 1818. The fuel path 1821 extends substantially axially through the outer liner 1804 from the fuel supply line 1819 to the fuel injectors 1818. For example, although in Fig.18 , but the fuel path 1821 is fluidly coupled around the one or more air dilution holes 1805 such that the fuel 67 flows within the fuel path 1821 around the one or more air dilution holes 1805 .

[0119] The combustor 1800 includes a combustor steam system 1820. The combustor steam system 1820 includes one or more steam injectors 1822, a steam path 1824 defined by the outer liner 1804 and the heat shield 1852 (e.g., disposed between the outer liner 1804 and the heat shield 1852), and one or more steam injection holes 1826. Fig.18 As shown, steam path 1824 extends axially between outer liner 1804 and thermal shield 1852. Steam path 1824 may be similar to Figure 2 The steam path 224 is annular about the longitudinal centerline axis, or may include similar Figure 5 and Figure 6 The steam path 1824 includes one or more discrete steam paths of the steam paths 524, 624. The steam path 1824 includes a front portion 1830 and a rear portion 1832. The front portion 1830 is fluidly coupled to the rear portion 1832 so that the steam 69 flows from the rear portion 1832 to the front portion 1830. For example, although in Fig.18 1805, the front portion 1830 and the rear portion 1832 of the steam path 1824 are fluidly coupled around the one or more air dilution holes 1805 so that the steam 69 flows from the rear portion 1832 to the front portion 1830 around the one or more air dilution holes 1805. The combustor steam system 1820 includes one or more steam injection holes 1826 disposed through the heat shield 1852, the one or more steam injection holes 1826 providing fluid communication from the steam path 1824 to the combustion chamber 202. The one or more steam injection holes 1826 are angled relative to the longitudinal centerline axis of the combustor 1800 to provide film cooling on the heat shield 1852.

[0120] The operation of the burner 1800 and the burner steam system 1820 is substantially similar to Figure 2 200 and a combustor steam system 220. In particular, the combustor 1800 is operable to direct the compressed air 65 through the annular dome 210 to generate a first compressed air flow 1862 within the combustion zone 203 of the combustion chamber 202. The combustor 1800 is operable to direct the compressed air 65 into the combustion chamber 202 through one or more air dilution holes 1805 to generate a second compressed air flow 1864 within the combustion chamber 202. The fuel supply line 1819 is operable to direct the fuel 67 into the fuel path 1821 and then into the fuel injector 1818. The fuel 67 flows axially forward in the fuel path 1821 in a direction opposite to the combustion gases 66 within the combustion chamber 202. The fuel injector 1818 is operable to inject the fuel 67 to generate the fuel flow 1860 within the combustion zone 203 of the combustion chamber 202.

[0121] The combustor steam system 1820 is operable to direct steam 69 through one or more steam injectors 1822 and into a steam path 1824 to cool the outer liner 1804 and the heat shield 1852 at the aft portion 1832. The steam path 1824 is operable to direct the steam 69 axially forward so that the steam 69 flows within the steam path 1824 in a direction opposite to the combustion gases 66 within the combustion chamber 202. The steam path 1824 is operable to direct the steam 69 from the aft portion 1832 to the forward portion 1830. As the steam 69 flows from the aft portion 1832 to the forward portion 1830, the steam 69 absorbs heat from the outer liner 1804 to cool the outer liner 1804. At the same time, the fuel 67 in the fuel path 1821 absorbs heat from the steam 69 in the steam path 1824 so that the temperature of the fuel 67 increases as the fuel 67 flows through the fuel path 1821. Increasing the temperature of the fuel 67 allows for more efficient combustion within the combustion zone 203 compared to a combustor without the benefit of the present disclosure.

[0122] One or more steam injection holes 1826 are operable to direct steam 69 therethrough to generate steam injection streams 1870 at a front portion 1830 and a rear portion 1832 of a steam path 1824 within the combustion chamber 202. The steam injection stream 1870 from the rear portion 1832 includes a greater amount of steam 69 than the steam injection stream 1870 from the front portion 1830. For example, the steam 69 injected from the rear portion 1832 includes 50% to 80% of the steam 69 from the steam path 1824, and the steam 69 injected from the front portion 1830 includes 20% to 50% of the steam 69 from the steam path 1824. The combustion gases 66 from the combustion zone mix with the steam injection stream 1870 to generate a steam-combustion gas mixture 1890 that is directed downstream and exits the combustion chamber 202.

[0123] Fig.19 is a schematic cross-sectional view of a portion of annular dome 1910 of combustor 1900 taken along a longitudinal centerline axis of combustor 1900 according to another embodiment. Fig. 20 According to the present disclosure Fig.19 A schematic cross-sectional rear view of a portion of an annular dome 1910 of FIG. 1900 is substantially similar to Figure 2200 of the burner 1900, and includes many components that are the same or similar to the burner 200. The same reference numerals will be used for components of the burner 1900 that are the same 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 annular dome 1910 includes one or more mixing assembly holes 1980 that receive corresponding mixing assemblies (e.g., multiple mixing assemblies 212). The burner 1900 includes a burner steam system 1920. The burner steam system 1920 includes a steam path 1982 defined by the annular dome 1910 (e.g., disposed within the annular dome 1910). For example, the steam path 1982 extends substantially radially within the annular dome 1910.

[0124] The combustor steam system 1920 includes one or more steam injection holes 1984 and one or more flame shaping holes 1986 disposed through the annular dome 1910. The one or more steam injection holes 1984 and the one or more flame shaping holes 1986 provide fluid communication from the steam path 1982 to the combustion chamber 202. The one or more steam injection holes 1984 are substantially positioned at the radially outer periphery or the radially inner periphery of the annular dome 1910 and extend substantially axially through the annular dome 1910. In some embodiments, the one or more steam injection holes 1984 are angled relative to the axial direction A to provide film cooling on the annular dome 1910. In this manner, the one or more steam injection holes 1984 can be steam cooling holes. The one or more flame shaping holes 1986 are radially positioned between the one or more mixing assembly holes 1980 and the one or more steam injection holes 1984. The one or more flame shaping holes 1986 are angled toward the one or more mixing assembly holes 1980.

[0125] The operation of the burner 1900 and the burner steam system 1920 is substantially similar to the burner 1900 and the burner steam system 1920, respectively. In particular, the burner steam system 1920 is operable to direct steam 69 within the steam path 1982 to cool the annular dome 1910. One or more steam injection holes 1984 are operable to inject steam 69 from the steam path 1982 into the combustion chamber 202 to generate a steam injection flow 1985 in the area of ​​the combustion zone 203 of the combustion chamber 202. One or more flame shaping holes 1986 are operable to direct steam 69 into the combustion chamber 202 to generate a steam flame shaping flow 1987 within the combustion zone 203 of the combustion chamber 202. The steam flame shaping flow 1987 is angled toward the flame generated in the combustion zone 203 so that the steam flame shaping flow 1987 maintains the flame within the radial center of a portion of the annular dome 1910. In this manner, the steam flame shaping stream 1987 prevents the flame from undesirably expanding radially beyond the steam flame shaping stream 1987 .

[0126] Fig.21 is a schematic cross-sectional rear view of a portion of an annular dome 2110 of a burner 2100 according to the present disclosure. The burner 2100 is substantially similar to Figure 2 and Fig.19 The burner 200, 1900 is similar to the burner 200, 1900 and includes many components that are the same or similar to the burners 200, 1900. The burner 2100 includes a burner steam system 2120, and the burner steam system 2120 includes a steam path 2182 defined by the annular dome 2110 (for example, within the annular dome 2110) and one or more steam injection holes 2184. The steam path 2182 has a discrete flow path within the annular dome 2110. In particular, the steam path 2182 defines a generally swirling shape around the annular dome 2110 for cooling specific areas of the annular dome 2110. The one or more steam injection holes 2184 are spaced apart along the steam path 2182. The operation of the burner steam system 2120 is substantially similar to that of the burner steam system 2120, respectively. Figure 2 and Fig.19 The combustor steam system 220, 1920. In particular, the steam path 2182 is operable to direct the steam 69 around the steam path 2180 to cool the annular dome 2110. One or more steam injection holes 2184 are operable to direct the steam 69 therethrough and into the combustion chamber.

[0127] Fig. 22 is a schematic cross-sectional view of a combustor 2200 taken along a longitudinal centerline axis of the combustor 2200 according to another embodiment. The combustor 2200 is substantially similar to Figure 2 The burner 2200 is a burner 200 of the present invention and includes many components that are the same or similar to the burner 200. The same reference numerals will be used for components of the burner 2200 that are the same 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 herein. The burner 2200 includes a combustion chamber 2202 defined by an outer liner 2204, an inner liner 2206, and an annular dome 2210. The combustion chamber 2202 extends to a combustion chamber outlet 2211. The annular dome 2210 includes one or more mixing assembly holes 2280 for receiving corresponding mixing assemblies (e.g., Figure 2 The combustor 2200 includes one or more air dilution holes 2205 defined through at least one of the outer liner 2204 or the inner liner 2206.

[0128] The combustor 2200 includes a combustor steam system 2220. The combustor steam system 2220 includes steam paths 2224, 2282 defined by at least one of the outer liner 2204, the inner liner 2206, or the annular dome 2210 (e.g., within at least one of the outer liner 2204, the inner liner 2206, or the annular dome 2210). The steam paths 2224, 2282 include a liner steam path 2222 defined by the outer liner 2204 and the inner liner 2206 (e.g., disposed within the outer liner 2204 and the inner liner 2206), and a dome steam path 2282 defined by the annular dome 2210 (e.g., within the annular dome 2210). The liner steam path 2224 and the dome steam path 2282 can be any steam path detailed herein, respectively. The liner steam path 2224 is fluidly coupled to the dome steam path 2282. The liner steam path 2224 includes a front portion 2230 and a rear portion 2232. The combustor steam system 2220 includes one or more steam injection holes 2226, 2284 defined through at least one of the outer liner 2204, the inner liner 2206, or the annular dome 2210. The one or more steam injection holes 2226, 2284 include one or more liner steam injection holes 2226 and one or more dome steam injection holes 2284. The one or more liner steam injection holes 2226 are positioned axially rearward of the one or more air dilution holes 2205. The one or more dome steam injection holes 2284 are disposed through the annular dome 2210. The combustor steam system 2220 also includes one or more flame shaping holes 2286 disposed through the annular dome 2210.

[0129] The operation of the burner 2200 and the burner steam system 2220 is substantially similar to Figure 2The combustor 200 and the combustor steam system 220 are shown in FIG. 1 . In particular, the combustor 2200 is operable to direct the compressed air 65 through the one or more air dilution holes 2205 to generate a second compressed air flow 2264 within the combustion chamber 2202. The liner steam path 2224 is operable to direct the steam 69 around the outer liner 2204 and the inner liner 2206 to cool the outer liner 2204 and the inner liner 2206. The liner steam path 2224 is operable to direct the steam 69 to the dome steam path 2282, and the dome steam path 2282 is operable to direct the steam 69 within the annular dome 2210 to cool the annular dome 2210. The liner steam injection hole 2226 is operable to direct the steam 69 into the combustion chamber 2202 to generate a liner steam injection flow 2270 downstream of the one or more air dilution holes 2205. One or more dome steam injection holes 2284 are operable to direct steam 69 from the dome steam path 2282 into the combustion chamber 2202 to generate a dome steam injection flow 2285 in the region of the annular dome 2210 within the combustion chamber 2202. The liner steam injection flow 2270 includes a greater amount of steam 69 than the dome steam injection flow 2285. For example, the liner steam injection flow 2270 includes 70% to 90% of the steam 69 from the steam paths 2224, 2282, while the dome steam injection flow 2285 includes 10% to 30% of the steam 69 from the steam paths 2224, 2282. One or more flame shaping holes 2286 are operable to direct steam 69 into the combustion chamber 2202 to generate a steam flame shaping flow 2287 to shape a flame within the combustion zone 203. The combustion gases 66 from the combustion zone 203 mix with the dome steam injection flow 2285 , the steam flame forming flow 2287 , and the liner steam injection flow 2270 to generate a steam-combustion gas mixture 2290 within the combustion chamber 2202 that is directed downstream and out of the combustion chamber 2202 .

[0130] Fig.23 is a schematic cross-sectional view of a combustor 2300 taken along a longitudinal centerline axis 12 of the combustor 2300 according to another embodiment. The combustor 2300 is substantially similar to Figure 2 and Fig. 22The burner 200, 2200 of the present invention is a burner 200, 2200, and includes many components that are the same or similar to the burners 200, 2200, respectively. The same reference numerals will be used for components of the burner 2300 that are the same or similar to the components of the above-mentioned burners 200, 2200. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here. The burner 2300 includes a combustion chamber 2302 defined by an outer liner 2304, an inner liner 2306 and an annular dome 2210. The combustion chamber 2202 extends to a combustion chamber outlet 2311. The outer liner 2304 and the inner liner 2306 extend from the annular dome 2210 to the combustion chamber outlet 2311. The outer liner 2304 and the inner liner 2306 are angled with the annular dome 2210 toward the longitudinal centerline axis 12, so that the combustion chamber 2302 defines a converging nozzle that accelerates the combustion gas 66 through the combustion chamber outlet 2311.

[0131] The combustor 2300 includes a combustor steam system 2320. The combustor steam system 2320 includes steam paths 2324, 2282 defined by (e.g., within) at least one of the outer liner 2304, the inner liner 2306, or the annular dome 2210. The steam paths 2324, 2282 include a liner steam path 2324 defined by (e.g., within) the outer liner 2304 and the inner liner 2306, and a dome steam path 2282 defined by (e.g., within) the annular dome 2210. The liner steam path 2324 includes a front portion 2330 and an aft portion 2332. The combustor steam system 2320 includes one or more steam injection holes 2326, 2284 defined through at least one of the outer liner 2304, the inner liner 2306, or the annular dome 2210. The one or more steam injection holes 2326, 2284 include one or more liner steam injection holes 2326 and one or more dome steam injection holes 2284. The combustor steam system 2320 also includes one or more steam dilution holes 2328 defined in the outer liner 2304 or the inner liner 2306. The one or more liner steam injection holes 2326 are positioned axially rearward of the one or more steam dilution holes 2328. For example, the one or more liner steam injection holes 2326 are positioned at the rear 2332 of the liner steam path 2324.

[0132] Combustion chamber 2302 includes a total combustion chamber length L defined axially from the downstream surface of annular dome 2110 to combustion chamber outlet 2311. combustor One or more steam dilution holes 2328 have a dilution hole length L dilution Positioned on the outer liner 2304 or the inner liner 2306, the dilution hole length L dilutionIt is measured from the downstream surface of the annular dome 2110 to the axial center of the one or more steam dilution holes 2328. Dilution hole length L dilution The total combustion chamber length L combustor In this way, the steam 69 is within the total combustion chamber length L combustor A range of 10% to 90% is injected through the outer liner 2304 or the inner liner 2306.

[0133] The operation of the burner 2300 and the burner steam system 2320 is substantially similar to Figure 2 and Fig. 22 The combustor 200, 2200 and the combustor steam system 220, 2220 of the embodiment of the present invention are shown in Figure 2. In particular, one or more liner steam injection holes 2326 are operable to direct steam 69 from the steam path 2324 to generate a first steam injection flow 2370 through the outer liner 2304 and the inner liner 2306 downstream of one or more steam dilution holes 2328 in the combustion chamber 2302. One or more steam dilution holes 2328 are operable to direct steam 69 from the steam path 2324 to generate a second steam injection flow 2372 from the outer liner 2304 and the inner liner 2306 in the combustion chamber 2302. The combustion gases 66 from the combustion zone 203 are mixed with the dome steam injection flow 2285, the steam flame forming flow 2287, the first liner steam injection flow 2370, and the second liner steam injection flow 2372 to generate a steam-combustion gas mixture 2390 in the combustion chamber 2302 that is directed downstream and exits the combustion chamber 2302.

[0134] Thus, embodiments of the present disclosure detailed herein provide a flame in a combustion zone within a combustion chamber and inject steam into the combustion chamber away from the combustion zone. The steam system detailed herein enables greater amounts of steam to be injected into the burner without sacrificing the operability of the burner, as compared to a burner without the benefit of the present disclosure. For example, large amounts of steam typically injected into a burner cause the flame to flame out, but the present disclosure provides steam injected into the combustion chamber away from the combustion zone (e.g., downstream of the combustion zone) to avoid flame flame out in the combustion zone. This configuration of injecting steam away from the flame enables greater amounts of steam to be injected into the burner, as compared to a burner without the benefit of the present disclosure. For example, injecting steam downstream of the combustion zone prevents steam from flowing near the flame within the combustion zone. In this way, the present disclosure allows greater amounts of steam to be injected into the burner while preventing steam from blocking the flame, thereby reducing emissions (e.g., NO xEmissions, nvPM emissions, CO, and noise) and reduce SFC while providing flame stability (e.g., avoiding flameout). This configuration of flowing steam through a steam path defined by at least one of the outer liner, inner liner, or annular dome also increases the life of the outer liner, inner liner, or annular dome compared to an outer liner, inner liner, and annular dome without the benefit of the present disclosure.

[0135] Further aspects of the disclosure are provided by the subject matter of the following clauses.

[0136] A combustor comprises: a combustion chamber, the combustion chamber comprising an outer liner and an inner liner and having a combustion zone; an annular dome, the annular dome being connected to the outer liner and the inner liner at a front end of the combustion chamber; a plurality of mixing assemblies, the plurality of mixing assemblies being operable to inject a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases; and a combustor steam system, the combustor steam system being fluidly connected to the combustion chamber, the combustor steam system comprising a steam path defined by at least one of the outer liner, the inner liner or the annular dome, the combustor steam system being operable to guide steam from the outer liner, the inner liner or the annular dome through the steam path and into the combustion chamber.

[0137] A burner as recited in the preceding clause, wherein said burner steam system is operable to direct said steam away from said combustion zone.

[0138] A burner as claimed in any preceding clause, wherein the water-to-air ratio of the steam to compressed air in the combustion chamber is between 0.0% and 60%.

[0139] The combustor according to any preceding clause, further comprising at least one of one or more air dilution holes or one or more steam dilution holes in the outer liner or the inner liner, the combustor steam system being operable to inject at least a portion of the steam into the combustion chamber axially rearward of the at least one of the one or more air dilution holes or the one or more steam injection holes.

[0140] According to the combustor described in any preceding item, the combustor steam system includes one or more steam cooling holes in at least one of the outer liner, the inner liner or the annular dome, and the one or more steam cooling holes are operable to guide the steam therethrough to cool the at least one of the outer liner, the inner liner or the annular dome.

[0141] A burner as described in any preceding clause, the burner steam system comprising one or more steam injectors in fluid communication with the steam path, and the one or more steam injectors are operable to inject the steam into the steam path.

[0142] A burner as claimed in any preceding clause, wherein said one or more steam injectors are annularly arranged around said combustion chamber.

[0143] According to the combustor described in any of the preceding items, the combustor steam system includes one or more steam injection holes in at least one of the outer liner, the inner liner or the annular dome, and the one or more steam injection holes are operable to direct the steam from the steam path into the combustion chamber.

[0144] A combustor as in any preceding clause, wherein said one or more steam injection holes are positioned on said outer liner or said inner liner at least 25% of a total combustor length of said combustor.

[0145] The combustor of any preceding clause, wherein the one or more steam injection holes are positioned on the outer liner or the inner liner within a range of 10% to 90% of a total combustion chamber length of the combustion chamber.

[0146] A burner as claimed in any preceding clause, further comprising a steam system operable to supply said steam to said burner steam system.

[0147] A burner as claimed in any preceding clause, wherein the steam system comprises one or more steam lines providing the steam to the burner steam system.

[0148] The burner according to the preceding clause, wherein said one or more steam lines provide said steam to said one or more steam injectors.

[0149] A combustor as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0150] A combustor as claimed in any preceding clause, wherein the plurality of mixing assemblies comprises a plurality of fuel injectors for supplying fuel to the plurality of mixing assemblies.

[0151] The combustor of the preceding clause, said plurality of mixing assemblies comprising mixers that mix compressed air with said fuel from said plurality of fuel injectors.

[0152] A combustor as claimed in any preceding clause, wherein the one or more dilution holes are one or more air dilution holes operable to direct the compressed air into the combustion chamber.

[0153] A burner as claimed in any preceding clause, wherein the steam path comprises a front portion and a rear portion rearward of the front portion, the one or more steam injection holes being located at the front portion.

[0154] The combustor of any preceding clause, said steam path being annular about said at least one of said outer liner, said inner liner or said annular dome.

[0155] The combustor of any preceding clause, said steam path comprising one or more discrete steam paths within said at least one of said outer liner, said inner liner, or said annular dome.

[0156] The combustor of any preceding clause, the steam path comprising one or more circumferentially extending portions and one or more axially extending portions, the one or more axially extending portions being fluidly coupled to the one or more circumferentially extending portions.

[0157] A burner as claimed in any preceding clause, wherein the steam path has a generally zigzag shape.

[0158] The combustor according to the preceding clause, said one or more circumferentially extending portions and said one or more axially extending portions being fluidly coupled to form said generally zigzag shape.

[0159] A combustor as claimed in any preceding clause, wherein the steam path extends axially rearwardly of the one or more dilution holes.

[0160] A combustor as claimed in any preceding clause, wherein said one or more steam injectors are positioned axially forward of said one or more dilution holes.

[0161] A combustor as claimed in any preceding clause, wherein the one or more steam injectors are positioned axially rearward of the one or more dilution holes.

[0162] A burner as claimed in any preceding clause, wherein said one or more steam injection holes are positioned on said one or more circumferentially extending portions of said steam path.

[0163] A combustor as claimed in any preceding clause, wherein said one or more circumferentially extending portions extend circumferentially from said one or more steam injectors and said one or more axially extending portions extend axially rearwardly from said one or more circumferentially extending portions.

[0164] A combustor as described in any preceding clause, wherein the one or more axially extending portions include one or more discrete axially extending portions, the one or more discrete axially extending portions being circumferentially spaced about the at least one of the outer liner, the inner liner, or the annular dome.

[0165] A combustor as claimed in any preceding clause, wherein said one or more axially extending portions extend axially rearwardly of said one or more dilution holes.

[0166] A combustor as described in any preceding clause, wherein the steam path is in the outer liner or the inner liner.

[0167] A burner as described in any preceding clause, wherein the one or more dilution holes include one or more steam dilution holes in fluid communication with the steam path, the one or more steam dilution holes being operable to direct the steam from the steam path into the combustion chamber.

[0168] The combustor of any preceding clause, wherein the one or more dilution holes include one or more air dilution holes and one or more steam dilution holes alternating circumferentially around the outer liner or the inner liner.

[0169] The combustor of any preceding clause, the combustor steam system further comprising one or more steam slots disposed through the outer liner or the inner liner, the one or more steam slots operable to direct the steam into the combustion chamber.

[0170] The combustor according to the preceding clause, wherein the one or more steam slots are positioned axially rearward of the one or more dilution holes.

[0171] A burner as claimed in any preceding clause, wherein said one or more steam slots are positioned axially forward of said one or more steam injection holes.

[0172] A burner according to any preceding clause, wherein said one or more steam slots are substantially arcuate slots.

[0173] The combustor of any preceding clause, the combustor steam system further comprising a steam manifold fluidly coupled between the one or more steam injectors and the steam path.

[0174] A burner as claimed in any preceding clause, wherein the steam manifold comprises one or more discrete steam manifolds.

[0175] A burner as claimed in any preceding clause, wherein the steam manifold is annular about the combustion chamber.

[0176] The combustor of any preceding clause, further comprising a heat shield coupled to said at least one of the outer liner, the inner liner, or the annular dome.

[0177] The combustor of any preceding clause, the steam path defined between the heat shield and the at least one of the outer liner, the inner liner, or the annular dome.

[0178] The combustor of any preceding clause, further comprising one or more air impingement holes disposed through said at least one of said outer liner, said inner liner, or said annular dome, said one or more air impingement holes operable to direct said compressed air into said steam path to impinge said heat shield.

[0179] A combustor according to any preceding clause, the combustor steam system further comprising one or more steam cooling holes arranged through the heat shield, the one or more steam cooling holes being operable to direct the steam from the steam path into the combustion chamber to cool the heat shield.

[0180] A combustor as claimed in any preceding clause, wherein said one or more steam cooling holes are angled rearwardly relative to said longitudinal centreline axis of said combustor.

[0181] The burner of any preceding clause, the burner steam system further comprising one or more steam injector lines fluidly coupled between the steam manifold and the steam path for operatively directing the steam from the steam manifold to the steam path.

[0182] According to the burner of any preceding clause, the steam path includes a front portion located in front of at least one of the one or more air dilution holes or the one or more steam dilution holes, and a rear portion located behind at least one of the one or more air dilution holes or the one or more steam dilution holes.

[0183] A burner as claimed in any preceding clause, wherein the front portion is fluidly coupled to the rear portion.

[0184] A burner according to any preceding clause, the burner steam system further comprising one or more front steam inlet holes, the one or more front steam inlet holes being positioned forward of the one or more steam dilution holes and providing fluid communication from the steam manifold to the front portion of the steam path.

[0185] According to the burner described in any preceding clause, the burner steam system further includes one or more rear steam inlet holes, which are positioned rearward of the one or more steam dilution holes and provide fluid communication from the steam manifold to the rear of the steam path.

[0186] A burner according to any preceding clause, wherein the one or more front steam inlet holes and the one or more rear steam inlet holes comprise substantially equal sizes such that a pressure drop through the one or more front steam inlet holes is substantially equal to a pressure drop through the one or more rear steam inlet holes.

[0187] A burner according to any preceding clause, wherein the one or more front steam inlet holes are sized differently from the one or more rear steam inlet holes such that a pressure drop across the one or more front steam inlet holes is different from a pressure drop across the one or more rear steam inlet holes.

[0188] According to the burner described in any preceding clause, the sizes of the one or more steam dilution holes and the one or more steam injection holes are set so that the one or more steam dilution holes are operable to guide more than 50% of the steam into the combustion chamber, and the one or more steam injection holes are operable to guide less than 50% of the steam into the combustion chamber.

[0189] According to the burner described in any preceding item, the sizes of the one or more steam dilution holes and the one or more steam injection holes are set so that the one or more steam dilution holes are operable to direct 40% to 100% of the steam into the combustion chamber, and the one or more steam injection holes are operable to direct 0.0% to 60% of the steam into the combustion chamber.

[0190] A burner as claimed in any preceding clause, said one or more steam injectors being positioned to direct said steam to said rear portion of said steam path.

[0191] A burner as claimed in any preceding clause, wherein said steam path is operable to direct said steam from said rear portion to said front portion.

[0192] A burner as claimed in any preceding clause, wherein the front portion is fluidly separated from the rear portion.

[0193] A burner as in any preceding clause, the burner steam system comprising one or more first steam injector lines in fluid communication with the rear portion, and one or more second steam injector lines in fluid communication with the front portion.

[0194] A burner according to any preceding clause, wherein the one or more steam injection holes are located at the front portion such that the steam is injected from the front portion, and the one or more steam injection holes are located at the rear portion such that the steam is injected from the rear portion.

[0195] A burner as claimed in any preceding clause, wherein said steam injected from said rear portion comprises a greater amount of said steam than said steam injected from said front portion.

[0196] A burner as described in any preceding clause, wherein the steam injected from the rear portion comprises 50% to 80% of the steam injected into the combustion chamber, and the steam injected from the front portion comprises 20% to 50% of the steam injected into the combustion chamber.

[0197] A burner according to any preceding clause, the burner steam system further comprising one or more steam manifold lines fluidly coupled between the steam manifold and the one or more second steam injector lines to operably direct the steam to the one or more second steam injector lines.

[0198] A combustor as in any preceding clause, the one or more air dilution holes comprising a dilution hole insert disposed within the one or more air dilution holes.

[0199] A combustor according to any preceding clause, wherein the one or more air dilution holes include dilution hole supports disposed within the one or more air dilution holes for preventing closure of the one or more air dilution holes during thermal expansion of the heat shield and the at least one of the outer liner, the inner liner or the annular dome.

[0200] A combustor as in any preceding clause, further comprising an air path positioned axially forward of the one or more dilution holes.

[0201] The combustor of any preceding clause, said air path being defined between said heat shield and said at least one of said outer liner, said inner liner or said annular dome.

[0202] A combustor as claimed in any preceding clause, said one or more air impingement holes being operable to direct said compressed air into said air path to impinge upon said heat shield.

[0203] A combustor as described in any preceding clause, further comprising one or more air injection holes disposed through the heat shield, the one or more air injection holes being operable to direct the compressed air from the air path to the combustion chamber to cool the heat shield.

[0204] A combustor as claimed in any preceding clause, wherein the steam path is positioned axially rearward of the one or more dilution holes.

[0205] The combustor of any preceding clause, the steam manifold comprising one or more steam impingement holes disposed therein, the one or more steam impingement holes operable to direct the steam from the steam manifold into the steam path to impinge on the heat shield.

[0206] The combustor of any preceding clause, the steam manifold comprising a front portion located axially forward of the one or more dilution holes and a rear portion located axially rearward of the one or more dilution holes.

[0207] A burner as claimed in any preceding clause, wherein said steam manifold is operable to direct said steam from said rear portion to said front portion.

[0208] The burner of any preceding clause, said one or more steam injectors comprising one or more first steam injectors operable to direct said steam into said rear portion, and one or more second steam injectors operable to direct said steam into said front portion.

[0209] The combustor of any preceding clause, the plurality of fuel injectors comprising a fuel supply line positioned axially rearward of the one or more dilution holes, the fuel supply line operable to direct the fuel to the plurality of fuel injectors.

[0210] The combustor of any preceding clause, further comprising a fuel path disposed within the outer liner or the inner liner, the fuel path providing fluid communication from the fuel supply line to the plurality of fuel injectors.

[0211] A combustor as in any preceding clause, said fuel path extending substantially axially from said fuel supply line to said plurality of fuel injectors.

[0212] A burner as claimed in any preceding clause, wherein the fuel path is operable to direct the fuel from the fuel supply line to the fuel injector.

[0213] A burner according to any preceding clause, wherein the fuel in the fuel path absorbs heat from the steam in the steam path as the fuel flows through the fuel path.

[0214] A burner as claimed in any preceding clause, wherein the steam flows through the steam path in a direction opposite to the direction of flow of the combustion gases.

[0215] A burner as claimed in any preceding clause, wherein the fuel flows through the fuel path in a direction opposite to the flow direction of the combustion gases.

[0216] A combustor as described in any preceding clause, wherein the steam path is provided in the outer liner or the inner liner.

[0217] The combustor of any preceding clause, wherein the one or more steam injection holes are provided in the outer liner or the inner liner.

[0218] A burner as claimed in any preceding clause, wherein said steam path is provided in said annular dome.

[0219] A burner as claimed in any preceding clause, wherein said one or more steam injection holes are provided in said annular dome.

[0220] According to the burner described in any of the preceding items, the burner steam system further includes one or more flame forming holes arranged through the annular dome, and the one or more flame forming holes are operable to guide the steam through the annular dome and into the combustion chamber to prevent the flame from radially expanding beyond the steam from the one or more flame forming holes.

[0221] A burner as claimed in any preceding clause, wherein the one or more flame-shaping holes are angled towards the flame.

[0222] The burner of any preceding clause, wherein the annular dome comprises one or more mixing assembly holes for receiving the plurality of mixing assemblies, the one or more flame shaping holes being radially positioned between the one or more mixing assembly holes and the one or more steam injection holes.

[0223] A burner as claimed in any preceding clause, wherein the one or more flame shaping holes are larger than the one or more steam injection holes.

[0224] A burner as claimed in any preceding clause, wherein the steam path has a generally swirl shape.

[0225] A combustor as claimed in any preceding clause, wherein said outer liner, said inner liner and said annular dome form a single unitary component.

[0226] A combustor as described in any preceding clause, wherein the steam path includes a liner steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0227] The combustor of any preceding clause, the liner steam path being fluidly coupled to the dome steam path.

[0228] The combustor according to any preceding clause, wherein the steam injected from the outer liner or the inner liner is 70% to 90% of the steam injected into the combustion chamber, and the steam injected from the annular dome is 10% to 30% of the steam injected into the combustion chamber.

[0229] The combustor of any preceding clause, said outer liner and said inner liner being angled toward said longitudinal centerline axis to define a converging nozzle that accelerates said combustion gases through a combustor outlet of said combustion chamber.

[0230] A combustor as in any preceding clause, said combustion chamber comprising a total combustion chamber length defined axially from a downstream surface of said annular dome to said combustion chamber outlet.

[0231] The combustor of any preceding clause, wherein the one or more dilution holes are positioned on the outer liner or the inner liner with a dilution hole length measured from the downstream surface of the annular dome to an axial center of the one or more dilution holes.

[0232] A burner as claimed in any preceding clause, wherein the dilution hole length is in the range of 10% to 90% of the total combustion chamber length.

[0233] A turbine engine includes a fan and a core turbine engine, the core turbine engine including a compressor section, a combustion section, and a turbine section. The combustion section includes a combustor, the combustor including: a combustion chamber, the combustion chamber including an outer liner and an inner liner and having a combustion zone; an annular dome, the annular dome coupled to the outer liner and the inner liner at a front end of the combustion chamber; a plurality of mixing assemblies, the plurality of mixing assemblies operable to inject a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases; and a combustor steam system, the combustor steam system being in fluid communication with the combustion chamber, the combustor steam system including a steam path defined by at least one of the outer liner, the inner liner, or the annular dome, the combustor steam system operable to direct steam from the outer liner, the inner liner, or the annular dome through the steam path, and into the combustion chamber.

[0234] According to the turbine engine of the preceding clause, the combustor steam system is operable to direct the steam away from the combustion zone.

[0235] A turbine engine as claimed in any preceding clause, wherein the water-to-air ratio of the steam to compressed air in the combustion chamber is between 0.0% and 60%.

[0236] The turbine engine according to any preceding clause, further comprising at least one of one or more air dilution holes or one or more steam dilution holes in the outer liner or the inner liner, the combustor steam system being operable to inject at least a portion of the steam into the combustion chamber axially rearward of the at least one of the one or more air dilution holes or the one or more steam injection holes.

[0237] According to a turbine engine described in any preceding clause, the combustor steam system includes one or more steam cooling holes in at least one of the outer liner, the inner liner or the annular dome, and the one or more steam cooling holes are operable to guide the steam therethrough to cool the at least one of the outer liner, the inner liner or the annular dome.

[0238] A turbine engine as described in any preceding clause, wherein the combustor steam system comprises one or more steam injectors in fluid communication with the steam path and wherein the one or more steam injectors are operable to inject the steam into the steam path.

[0239] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors are annularly arranged around said combustion chamber.

[0240] According to a turbine engine described in any of the preceding items, the combustor steam system includes one or more steam injection holes in at least one of the outer liner, the inner liner or the annular dome, and the one or more steam injection holes are operable to direct the steam from the steam path into the combustion chamber.

[0241] A turbine engine as claimed in any preceding clause, wherein said one or more steam injection holes are located on said outer liner or said inner liner at least 25% of a total combustion chamber length of said combustion chamber.

[0242] A turbine engine according to any preceding clause, wherein said one or more steam injection holes are positioned on said outer liner or said inner liner within a range of 10% to 90% of a total combustion chamber length of said combustion chamber.

[0243] A turbine engine as described in any preceding clause, further comprising a steam system operable to supply said steam to said combustor steam system.

[0244] A turbine engine as described in any preceding clause, wherein the steam system comprises one or more steam lines providing the steam to the combustor steam system.

[0245] The turbine engine according to the preceding clause, wherein said one or more steam lines provide said steam to said one or more steam injectors.

[0246] A turbine engine as claimed in any preceding clause, wherein the steam system generates steam from exhaust gas of the turbine engine.

[0247] A turbine engine as described in any preceding clause, the plurality of mixing assemblies comprising a plurality of fuel injectors for supplying fuel to the plurality of mixing assemblies.

[0248] The turbine engine according to the preceding clause, said plurality of mixing assemblies comprising mixers that mix compressed air with said fuel from said plurality of fuel injectors.

[0249] A turbine engine as claimed in any preceding clause, wherein said one or more dilution holes are one or more air dilution holes operable to direct said compressed air into said combustion chamber.

[0250] A turbine engine as claimed in any preceding clause, wherein the steam path comprises a front portion and a rear portion rearward of the front portion, the one or more steam injection holes being located at the front portion.

[0251] A turbine engine as described in any preceding clause, wherein said steam path is annular about said at least one of said outer liner, said inner liner or said annular dome.

[0252] A turbine engine as in any preceding clause, said steam path comprising one or more discrete steam paths within said at least one of said outer liner, said inner liner, or said annular dome.

[0253] A turbine engine as described in any preceding clause, wherein the steam path comprises one or more circumferentially extending portions and one or more axially extending portions, the one or more axially extending portions being fluidly coupled to the one or more circumferentially extending portions.

[0254] A turbine engine as claimed in any preceding clause, wherein said steam path has a generally zigzag shape.

[0255] The turbine engine according to the preceding clause, said one or more circumferentially extending portions and said one or more axially extending portions being fluidly coupled to form said generally zigzag shape.

[0256] A turbine engine as claimed in any preceding clause, wherein the steam path extends axially rearwardly of the one or more dilution holes.

[0257] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors are positioned axially forward of said one or more dilution holes.

[0258] A turbine engine as claimed in any preceding clause, wherein said one or more steam injectors are positioned axially rearward of said one or more dilution holes.

[0259] A turbine engine as claimed in any preceding clause, wherein said one or more steam injection holes are positioned on said one or more circumferentially extending portions of said steam path.

[0260] A turbine engine as described in any preceding clause, wherein said one or more circumferentially extending portions extend circumferentially from said one or more steam injectors, and wherein said one or more axially extending portions extend axially aft from said one or more circumferentially extending portions.

[0261] A turbine engine according to any preceding clause, wherein said one or more axially extending portions comprise one or more discrete axially extending portions spaced circumferentially about said at least one of said outer liner, said inner liner or said annular dome.

[0262] A turbine engine as claimed in any preceding clause, wherein said one or more axially extending portions extend axially rearwardly of said one or more dilution holes.

[0263] A turbine engine as described in any preceding clause, wherein the steam path is in the outer liner or the inner liner.

[0264] A turbine engine as described in any preceding clause, wherein the one or more dilution holes include one or more steam dilution holes in fluid communication with the steam path, the one or more steam dilution holes being operable to direct the steam from the steam path into the combustion chamber.

[0265] A turbine engine as described in any preceding clause, wherein the one or more dilution holes include one or more air dilution holes and one or more steam dilution holes alternating circumferentially around the outer liner or the inner liner.

[0266] A turbine engine as described in any preceding clause, the combustor steam system further comprising one or more steam slots disposed through the outer liner or the inner liner, the one or more steam slots operable to direct the steam into the combustion chamber.

[0267] The turbine engine according to the preceding clause, wherein said one or more steam slots are positioned axially rearward of said one or more dilution holes.

[0268] A turbine engine as described in any preceding clause, wherein said one or more steam slots are positioned axially forward of said one or more steam injection holes.

[0269] A turbine engine as described in any preceding clause, wherein said one or more steam slots are generally arcuate slots.

[0270] A turbine engine as in any preceding clause, said combustor steam system further comprising a steam manifold fluidly coupled between said one or more steam injectors and said steam path.

[0271] A turbine engine as described in any preceding clause, wherein the steam manifold comprises one or more discrete steam manifolds.

[0272] A turbine engine as described in any preceding clause, wherein the steam manifold is annular about the combustion chamber.

[0273] A turbine engine as recited in any preceding clause, further comprising a heat shield coupled to said at least one of said outer liner, said inner liner, or said annular dome.

[0274] A turbine engine as recited in any preceding clause, said steam path being defined between said heat shield and said at least one of said outer liner, said inner liner or said annular dome.

[0275] A turbine engine according to any preceding clause, further comprising one or more air impingement holes disposed through said at least one of said outer liner, said inner liner or said annular dome, said one or more air impingement holes operable to direct said compressed air into said steam path to impinge said heat shield.

[0276] According to the turbine engine of any preceding clause, the combustor steam system further includes one or more steam cooling holes arranged through the heat shield, the one or more steam cooling holes being operable to direct the steam from the steam path into the combustion chamber to cool the heat shield.

[0277] A turbine engine as described in any preceding clause, wherein said one or more steam cooling holes are angled rearwardly relative to said longitudinal centerline axis of said combustor.

[0278] A turbine engine as recited in any preceding clause, said combustor steam system further comprising one or more steam injector lines fluidly coupled between said steam manifold and said steam path for operatively directing said steam from said steam manifold to said steam path.

[0279] A turbine engine according to any preceding clause, wherein the steam path includes a forward portion located forward of at least one of the one or more air dilution holes or the one or more steam dilution holes, and a rearward portion located rearward of at least one of the one or more air dilution holes or the one or more steam dilution holes.

[0280] A turbine engine as claimed in any preceding clause, wherein the front portion is fluidly coupled to the rear portion.

[0281] According to the turbine engine of any preceding clause, the combustor steam system further includes one or more forward steam inlet holes, which are positioned forward of the one or more steam dilution holes and provide fluid communication from the steam manifold to the front of the steam path.

[0282] According to a turbine engine as described in any preceding clause, the combustor steam system further includes one or more rear steam inlet holes, which are positioned rearward of the one or more steam dilution holes and provide fluid communication from the steam manifold to the rear portion of the steam path.

[0283] According to a turbine engine as described in any preceding clause, the one or more front steam inlet holes and the one or more rear steam inlet holes include substantially equal sizes, so that the pressure drop through the one or more front steam inlet holes is substantially equal to the pressure drop through the one or more rear steam inlet holes.

[0284] According to a turbine engine as described in any preceding clause, the one or more front steam inlet holes are sized differently from the one or more rear steam inlet holes so that the pressure drop through the one or more front steam inlet holes is different from the pressure drop through the one or more rear steam inlet holes.

[0285] According to the turbine engine described in any preceding clause, the sizes of the one or more steam dilution holes and the one or more steam injection holes are set so that the one or more steam dilution holes are operable to direct more than 50% of the steam into the combustion chamber, and the one or more steam injection holes are operable to direct less than 50% of the steam into the combustion chamber.

[0286] According to the turbine engine described in any preceding clause, the one or more steam dilution holes and the one or more steam injection holes are sized so that the one or more steam dilution holes are operable to direct 40% to 100% of the steam into the combustion chamber, and the one or more steam injection holes are operable to direct 0.0% to 60% of the steam into the combustion chamber.

[0287] A turbine engine as described in any preceding clause, wherein said one or more steam injectors are positioned to direct said steam to said rear portion of said steam path.

[0288] A turbine engine as claimed in any preceding clause, wherein said steam path is operable to direct said steam from said rear portion to said front portion.

[0289] A turbine engine as claimed in any preceding clause, wherein said front portion is fluidly separated from said rear portion.

[0290] A turbine engine as described in any preceding clause, the combustor steam system comprising one or more first steam injector lines in fluid communication with the aft portion, and one or more second steam injector lines in fluid communication with the forward portion.

[0291] A turbine engine according to any preceding clause, wherein said one or more steam injection holes are located at said front portion such that said steam is injected from said front portion, and wherein said one or more steam injection holes are located at said rear portion such that said steam is injected from said rear portion.

[0292] A turbine engine as claimed in any preceding clause, wherein said steam injected from said rear portion comprises a greater amount of said steam than said steam injected from said front portion.

[0293] A turbine engine according to any preceding clause, wherein said steam injected from said rear portion comprises 50% to 80% of said steam injected into said combustion chamber and said steam injected from said front portion comprises 20% to 50% of said steam injected into said combustion chamber.

[0294] According to the turbine engine of any preceding clause, the combustor steam system further includes one or more steam manifold lines fluidly connected between the steam manifold and the one or more second steam injector lines to operably direct the steam to the one or more second steam injector lines.

[0295] A turbine engine as described in any preceding clause, wherein the one or more air dilution holes include a dilution hole insert disposed within the one or more air dilution holes.

[0296] A turbine engine according to any preceding clause, wherein the one or more air dilution holes include a dilution hole support disposed within the one or more air dilution holes for preventing closure of the one or more air dilution holes during thermal expansion of the heat shield and the at least one of the outer liner, the inner liner or the annular dome.

[0297] A turbine engine as described in any preceding clause, the combustor further comprising an air path positioned axially forward of the one or more dilution holes.

[0298] A turbine engine as recited in any preceding clause, said air path being defined between said heat shield and said at least one of said outer liner, said inner liner or said annular dome.

[0299] A turbine engine as recited in any preceding clause, said one or more air impingement holes operable to direct said compressed air into said air path to impinge upon said heat shield.

[0300] According to any preceding clause of the turbine engine, the combustor further comprises one or more air injection holes arranged through the heat shield, the one or more air injection holes being operable to direct the compressed air from the air path to the combustion chamber to cool the heat shield.

[0301] A turbine engine as claimed in any preceding clause, wherein the steam path is located axially rearward of the one or more dilution holes.

[0302] A turbine engine as recited in any preceding clause, the steam manifold comprising one or more steam impingement holes disposed therein, the one or more steam impingement holes operable to direct the steam from the steam manifold into the steam path to impinge upon the heat shield.

[0303] A turbine engine according to any preceding clause, wherein the steam manifold comprises a front portion located axially forward of the one or more dilution holes and a rear portion located axially rearward of the one or more dilution holes.

[0304] A turbine engine as described in any preceding clause, wherein said steam manifold is operable to direct said steam from said rear portion to said front portion.

[0305] A turbine engine as described in any preceding clause, wherein the one or more steam injectors include one or more first steam injectors operable to direct the steam into the aft portion, and one or more second steam injectors operable to direct the steam into the forward portion.

[0306] A turbine engine as recited in any preceding clause, said plurality of fuel injectors comprising a fuel supply line positioned axially rearward of said one or more dilution holes, said fuel supply line operable to direct said fuel to said plurality of fuel injectors.

[0307] A turbine engine as recited in any preceding clause, further comprising a fuel path disposed within said outer liner or said inner liner, said fuel path providing fluid communication from said fuel supply line to said plurality of fuel injectors.

[0308] A turbine engine as claimed in any preceding clause, wherein the fuel path extends substantially axially from the fuel supply line to the plurality of fuel injectors.

[0309] A turbine engine as described in any preceding clause, wherein the fuel path is operable to direct the fuel from the fuel supply line to the fuel injector.

[0310] A turbine engine as described in any preceding clause, wherein the fuel in the fuel path absorbs heat from the steam in the steam path as the fuel flows through the fuel path.

[0311] A turbine engine as claimed in any preceding clause, wherein said steam flows through said steam path in a direction opposite to a direction of flow of said combustion gases.

[0312] A turbine engine as described in any preceding clause, wherein the fuel flows through the fuel path in a direction opposite to the flow direction of the combustion gases.

[0313] A turbine engine as described in any preceding clause, wherein the steam path is provided in the outer liner or the inner liner.

[0314] A turbine engine as claimed in any preceding clause, wherein said one or more steam injection holes are provided in said outer liner or said inner liner.

[0315] A turbine engine as described in any preceding clause, wherein said steam path is provided in said annular dome.

[0316] A turbine engine as described in any preceding clause, wherein said one or more steam injection holes are provided in said annular dome.

[0317] According to a turbine engine described in any of the preceding items, the combustor steam system further includes one or more flame forming holes arranged through the annular dome, and the one or more flame forming holes are operable to guide the steam through the annular dome and into the combustion chamber to prevent the flame from radially expanding beyond the steam from the one or more flame forming holes.

[0318] A turbine engine as claimed in any preceding clause, wherein said one or more flame-shaping holes are angled towards said flame.

[0319] A turbine engine according to any preceding clause, wherein the annular dome comprises one or more mixing assembly holes for receiving the plurality of mixing assemblies, the one or more flame-forming holes being radially positioned between the one or more mixing assembly holes and the one or more steam injection holes.

[0320] A turbine engine as claimed in any preceding clause, wherein said one or more flame shaping holes are larger than said one or more steam injection holes.

[0321] A turbine engine as claimed in any preceding clause, wherein the steam path has a generally swirl shape.

[0322] A turbine engine as claimed in any preceding clause, wherein said outer liner, said inner liner and said annular dome form a single unitary component.

[0323] A turbine engine as described in any preceding clause, wherein the steam path includes a liner steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0324] A turbine engine as described in any preceding clause, wherein the liner steam path is fluidly coupled to the dome steam path.

[0325] A turbine engine according to any preceding clause, wherein the steam injected from the outer liner or the inner liner is 70% to 90% of the steam injected into the combustion chamber, and the steam injected from the annular dome is 10% to 30% of the steam injected into the combustion chamber.

[0326] A turbine engine as described in any preceding clause, wherein said outer liner and said inner liner are angled toward said longitudinal centerline axis to define a converging nozzle that accelerates said combustion gases through a combustor outlet of said combustor.

[0327] A turbine engine as claimed in any preceding clause, wherein said combustion chamber comprises a total combustion chamber length defined axially from a downstream surface of said annular dome to said combustion chamber outlet.

[0328] A turbine engine according to any preceding clause, wherein the one or more dilution holes are positioned on the outer liner or the inner liner with a dilution hole length measured from the downstream surface of the annular dome to an axial center of the one or more dilution holes.

[0329] A turbine engine as claimed in any preceding clause, wherein the dilution hole length is in the range of 10% to 90% of the total combustion chamber length.

[0330] A method of operating a turbine engine 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 combustion zone of the combustion chamber to generate a flame in the combustion zone that produces the combustion gases; directing the steam into the steam path defined by at least one of the outer liner, the inner liner, or the annular dome using the combustor steam system; and directing the steam from the steam path and into the combustion chamber.

[0331] A method as in any preceding clause, further comprising directing the steam away from the combustion zone.

[0332] The method of any preceding clause, further comprising injecting the steam utilizing the combustor steam system during medium power operation of the turbine engine and during high power operation of the turbine engine.

[0333] A method as in any preceding clause, further comprising directing the steam into the combustion chamber such that a water-to-air ratio of the steam to compressed air in the combustion chamber is between 0.0% and 60%.

[0334] A method according to any preceding clause, wherein the combustor includes at least one of one or more air dilution holes or one or more steam dilution holes in the outer liner or the inner liner, and the method further includes directing at least a portion of the steam into the combustion chamber axially rearward of the at least one of the one or more air dilution holes or the one or more steam dilution holes.

[0335] A method according to any preceding clause, wherein the combustor steam system includes one or more steam cooling holes in at least one of the outer liner, the inner liner, or the annular dome, and the method further includes operably directing the steam through the one or more steam cooling holes to cool the at least one of the outer liner, the inner liner, or the annular dome.

[0336] The method of any preceding clause, wherein the burner steam system comprises one or more steam injectors in fluid communication with the steam path, and the method further comprises directing the steam through the one or more steam injectors and into the steam path.

[0337] A method according to any preceding clause, wherein the combustor steam system includes one or more steam injection holes in at least one of the outer liner, the inner liner, or the annular dome, and the method further includes directing the steam from the steam path through the one or more steam injection holes and into the combustion chamber.

[0338] The method of any preceding clause, further comprising directing the steam from the steam path through the one or more steam injection holes and into the combustion chamber at a location at least 25% of a total combustion chamber length of the combustion chamber.

[0339] A method as in any preceding clause, further comprising directing the steam from the steam path through the one or more steam injection holes and into the combustion chamber at a location in the range of 10% to 90% of a total combustion chamber length of the combustion chamber.

[0340] A method as in any preceding clause, further comprising supplying the steam to the burner steam system using a steam system.

[0341] A method as defined in any preceding clause, further comprising providing the steam to the burner steam system via one or more steam lines.

[0342] A method as described in the preceding clause, further comprising providing said steam to said one or more steam injectors.

[0343] A method as in any preceding clause, further comprising generating steam from exhaust gas of the turbine engine using the steam system.

[0344] A method as in any preceding clause, the plurality of mixing assemblies comprising a plurality of fuel injectors, the method comprising supplying fuel to the plurality of mixing assemblies via the plurality of fuel injectors.

[0345] A method as in the preceding clause, wherein the plurality of mixing assemblies include mixers, the method comprising mixing the compressed air with the fuel from the plurality of fuel injectors.

[0346] A method as defined in any preceding clause, further comprising directing the compressed air into the combustion chamber through the one or more air dilution holes.

[0347] A method as in any preceding clause, the steam path comprising a front portion and a rear portion rearward of the front portion, the one or more steam injection holes being located at the front portion.

[0348] A method as in any preceding clause, wherein the steam path is annular about the at least one of the outer liner, the inner liner, or the annular dome.

[0349] The method of any preceding clause, the steam path comprising one or more discrete steam paths within the at least one of the outer liner, the inner liner, or the annular dome.

[0350] A method as in any preceding clause, the steam path comprising one or more circumferentially extending portions and one or more axially extending portions, the one or more axially extending portions being fluidly coupled to the one or more circumferentially extending portions.

[0351] A method as in any preceding clause, wherein the steam path has a generally zigzag shape.

[0352] A method as recited in the preceding clause, wherein said one or more circumferentially extending portions and said one or more axially extending portions are fluidly coupled to form said generally zigzag shape.

[0353] A method as in any preceding clause, wherein the steam path extends axially rearwardly of the one or more dilution holes.

[0354] A method as in any preceding clause, wherein the one or more steam injectors are positioned axially forward of the one or more dilution holes.

[0355] A method as in any preceding clause, wherein the one or more steam injectors are positioned axially rearward of the one or more dilution holes.

[0356] A method as in any preceding clause, wherein the one or more steam injection holes are positioned on the one or more circumferentially extending portions of the steam path.

[0357] A method as in any preceding clause, wherein the one or more circumferentially extending portions extend circumferentially from the one or more steam injectors and the one or more axially extending portions extend axially rearwardly from the one or more circumferentially extending portions.

[0358] A method as in any preceding clause, wherein the one or more axially extending portions comprise one or more discrete axially extending portions spaced circumferentially about the at least one of the outer liner, the inner liner, or the annular dome.

[0359] A method as in any preceding clause, wherein the one or more axially extending portions extend axially rearwardly of the one or more dilution holes.

[0360] A method as in any preceding clause, wherein the steam path is in the outer liner or the inner liner.

[0361] A method as described in any preceding clause, wherein the one or more dilution holes include one or more steam dilution holes in fluid communication with the steam path, the method comprising directing the steam from the steam path into the combustion chamber through the one or more steam dilution holes.

[0362] A method as in any preceding clause, wherein the one or more dilution holes comprise one or more air dilution holes in fluid communication with the combustion chamber, the method comprising directing the compressed air into the combustion chamber through the one or more air dilution holes.

[0363] A method as in any preceding clause, wherein the one or more air dilution holes and the one or more steam dilution holes alternate circumferentially around the outer liner or the inner liner.

[0364] The method of any preceding clause, the combustor steam system further comprising one or more steam slots disposed through the outer liner or the inner liner, the method further comprising directing the steam into the combustion chamber through the one or more steam slots.

[0365] A method as recited in the preceding clause, wherein said one or more steam slots are positioned axially rearward of said one or more dilution holes.

[0366] A method as in any preceding clause, wherein the one or more steam slots are positioned axially forward of the one or more steam injection holes.

[0367] A method as in any preceding clause, wherein the one or more steam slots are generally arcuate slots.

[0368] The method of any preceding clause, the combustor steam system further comprising a steam manifold fluidly coupled between the one or more steam injectors and the steam path.

[0369] A method as in any preceding clause, the steam manifold comprising one or more discrete steam manifolds.

[0370] A method as in any preceding clause, wherein the steam manifold is annular about the combustion chamber.

[0371] The method of any preceding clause, further comprising a thermal shield coupled to said at least one of the outer liner, the inner liner, or the annular dome.

[0372] The method of any preceding clause, the steam path being defined between the thermal shield and the at least one of the outer liner, the inner liner, or the annular dome.

[0373] The method of any preceding clause, further comprising one or more air impingement holes disposed through said at least one of said outer liner, said inner liner or said annular dome, said method further comprising directing said compressed air into said steam path through said one or more air impingement holes to impinge said thermal shield.

[0374] According to the method of any preceding clause, the combustor steam system further includes one or more steam cooling holes arranged through the heat shield, and the method further includes directing the steam from the steam path through the one or more steam cooling holes and into the combustion chamber to cool the heat shield.

[0375] A method as in any preceding clause, wherein the one or more steam cooling holes are angled relative to the longitudinal centerline axis of the combustor.

[0376] According to the method of any preceding clause, the burner steam system further includes one or more steam injector pipelines fluidly connected between the steam manifold and the steam path, and the method further includes directing the steam from the steam manifold to the steam path through the one or more steam injector pipelines.

[0377] A method as described in any preceding clause, wherein the steam path includes a front portion located forward of at least one of the one or more air dilution holes or the one or more steam dilution holes, and a rear portion located rearward of the at least one of the one or more air dilution holes or the one or more steam dilution holes.

[0378] A method as in any preceding clause, the front portion being fluidly coupled to the rear portion.

[0379] A method according to any preceding clause, the burner steam system further comprising one or more front steam inlet holes positioned forward of the one or more steam dilution holes, and the method further comprising directing the steam from the steam manifold to the front portion of the steam path through the one or more front steam inlet holes.

[0380] A method according to any preceding clause, the burner steam system further comprising one or more rear steam inlet holes positioned rearward of the one or more steam dilution holes, and the method further comprising directing the steam from the steam manifold to the rear portion of the steam path through the one or more rear steam inlet holes.

[0381] A method according to any preceding clause, wherein the one or more front steam inlet holes and the one or more rear steam inlet holes comprise substantially equal sizes such that a pressure drop through the one or more front steam inlet holes is substantially equal to a pressure drop through the one or more rear steam inlet holes.

[0382] A method according to any preceding clause, wherein the one or more front steam inlet holes are sized differently than the one or more rear steam inlet holes such that a pressure drop across the one or more front steam inlet holes is different than a pressure drop across the one or more rear steam inlet holes.

[0383] The method of any preceding clause, further comprising directing greater than 50% of the steam into the combustion chamber through the one or more steam dilution holes and directing less than 50% of the steam into the combustion chamber through the one or more steam injection holes.

[0384] The method of any preceding clause, further comprising directing 40% to 100% of the steam into the combustion chamber through the one or more steam dilution holes, and directing 0.0% to 60% of the steam into the combustion chamber through the one or more steam injection holes.

[0385] A method as in any preceding clause, further comprising directing the steam to the rear portion of the steam path via the one or more steam injectors.

[0386] A method as in any preceding clause, further comprising directing the steam from the rear portion to the front portion.

[0387] A method as in any preceding clause, wherein the front portion is fluidly separated from the rear portion.

[0388] A method as in any preceding clause, the combustor steam system comprising one or more first steam injector lines in fluid communication with the rear portion, and one or more second steam injector lines in fluid communication with the front portion.

[0389] A method as claimed in any preceding clause, wherein the one or more steam injection holes are located at the front such that the steam is injected from the front, and the one or more steam injection holes are located at the rear such that the steam is injected from the rear.

[0390] A method as in any preceding clause, further comprising injecting a greater amount of said steam from said rear portion than from said front portion.

[0391] A method as in any preceding clause, wherein the steam injected from the rear comprises 50% to 80% of the steam injected into the combustion chamber and the steam injected from the front comprises 20% to 50% of the steam injected into the combustion chamber.

[0392] The method according to any preceding clause, the burner steam system further comprising one or more steam manifold lines fluidly coupled between the steam manifold and the one or more second steam injector lines, the method further comprising directing the steam to the one or more second steam injector lines.

[0393] A method as in any preceding clause, the one or more air dilution holes comprising a dilution hole insert disposed within the one or more air dilution holes.

[0394] The method of any preceding clause, wherein the one or more air dilution holes include a dilution hole support disposed within the one or more air dilution holes for preventing closure of the one or more air dilution holes during thermal expansion of the heat shield and the at least one of the outer liner, the inner liner, or the annular dome.

[0395] A method as in any preceding clause, the combustor further comprising an air path positioned axially forward of the one or more dilution holes.

[0396] A method as in any preceding clause, the air path being defined between the thermal shield and the at least one of the outer liner, the inner liner, or the annular dome.

[0397] A method as in any preceding clause, further comprising directing the compressed air into the air path through the one or more air impingement holes to impinge the heat shield.

[0398] A method according to any preceding clause, wherein the combustor further comprises one or more air injection holes arranged through the heat shield, the method further comprising directing the compressed air from the air path to the combustion chamber through the one or more air injection holes to cool the heat shield.

[0399] A method as in any preceding clause, wherein the steam path is positioned axially rearward of the one or more dilution holes.

[0400] A method according to any preceding clause, wherein the steam manifold comprises one or more steam impingement holes disposed therein, the method further comprising directing the steam from the steam manifold into the steam path through the one or more steam impingement holes to impinge the heat shield.

[0401] A method as in any preceding clause, the steam manifold comprising a front portion located axially forward of the one or more dilution holes and a rear portion located axially rearward of the one or more dilution holes.

[0402] A method as in any preceding clause, further comprising directing the steam from the rear portion to the front portion.

[0403] A method as in any preceding clause, the one or more steam injectors comprising one or more first steam injectors, the method further comprising directing the steam into the rear portion using the one or more first steam injectors.

[0404] A method as in any preceding clause, the one or more steam injectors comprising one or more second steam injectors, the method further comprising directing the steam into the front portion using the one or more second steam injectors.

[0405] The method of any preceding clause, the plurality of fuel injectors comprising a fuel supply line positioned axially rearward of the one or more dilution holes, the method further comprising directing the fuel to the plurality of fuel injectors through the fuel supply line.

[0406] The method of any preceding clause, further comprising a fuel path disposed within the outer liner or the inner liner, the fuel path providing fluid communication from the fuel supply line to the plurality of fuel injectors.

[0407] A method as in any preceding clause, the fuel path extending substantially axially from the fuel supply line to the plurality of fuel injectors.

[0408] A method as in any preceding clause, further comprising directing the fuel from the fuel supply line to the fuel injector through the fuel path.

[0409] A method as defined in any preceding clause, further comprising absorbing heat from the fuel from the steam in the steam path as the fuel flows through the fuel path.

[0410] A method as in any preceding clause, further comprising directing the steam in the steam path in a direction opposite to the direction of the combustion gases.

[0411] A method as in any preceding clause, further comprising directing the fuel through the fuel path in a direction opposite to the direction of the combustion gases.

[0412] A method as in any preceding clause, wherein the steam path is provided in the outer liner or the inner liner.

[0413] A method as in any preceding clause, wherein the one or more steam injection holes are provided in the outer liner or the inner liner.

[0414] A method as in any preceding clause, wherein the steam path is provided in the annular dome.

[0415] A method as in any preceding clause, wherein the one or more steam injection holes are provided in the annular dome.

[0416] According to the method of any preceding clause, the burner steam system further includes one or more flame forming holes arranged through the annular dome, and the method further includes guiding the steam through the annular dome and into the combustion chamber through the one or more flame forming holes to prevent the flame from radially expanding beyond the steam from the one or more flame forming holes.

[0417] A method as in any preceding clause, wherein the one or more flame-shaping holes are angled towards the flame.

[0418] The method of any preceding clause, wherein the annular dome comprises one or more mixing assembly holes for receiving the plurality of mixing assemblies, the one or more flame-forming holes being positioned radially between the one or more mixing assembly holes and the one or more steam injection holes.

[0419] A method as in any preceding clause, wherein the one or more flame-forming holes are larger than the one or more steam injection holes.

[0420] A method as in any preceding clause, the steam path having a generally swirl shape.

[0421] A method as in any preceding clause, wherein the outer liner, the inner liner and the annular dome form a single unitary component.

[0422] A method as in any preceding clause, wherein the steam path comprises a liner steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0423] A method as in any preceding clause, the liner steam path being fluidly coupled to the dome steam path.

[0424] A method as in any preceding clause, wherein the steam injected from the outer liner or the inner liner is 70% to 90% of the steam injected into the combustion chamber, and the steam injected from the annular dome is 10% to 30% of the steam injected into the combustion chamber.

[0425] The method of any preceding clause, wherein the outer liner and the inner liner are angled toward the longitudinal centerline axis to define a converging nozzle that accelerates the combustion gases through a combustor outlet of the combustor.

[0426] A method as in any preceding clause, the combustion chamber comprising a total combustion chamber length defined axially from a downstream surface of the annular dome to the combustion chamber outlet.

[0427] A method as in any preceding clause, wherein the one or more dilution holes are positioned on the outer liner or the inner liner with a dilution hole length measured from the downstream surface of the annular dome to an axial center of the one or more dilution holes.

[0428] A method as in any preceding clause, wherein the dilution hole length is in the range of 10% to 90% of the total combustion chamber length.

[0429] Although the foregoing description is directed to the preferred embodiments of the present disclosure, other changes and modifications are apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, the features described in conjunction with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A burner, characterized in that: include: a combustion chamber including an outer liner and an inner liner and having a combustion zone; an annular dome coupled to the outer liner and the inner liner at a forward end of the combustion chamber; a plurality of mixing assemblies operable to inject a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases; as well as and a combustor steam system in fluid communication with the combustion chamber, the combustor steam system comprising a steam path defined by at least one of the outer liner, the inner liner, or the annular dome, wherein the combustor steam system is operable to direct steam from the at least one of the outer liner, the inner liner, or the annular dome through the steam path and into the combustion chamber.

2. The burner according to claim 1, characterized in that in, The burner steam system is operable to direct the steam away from the combustion zone.

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

4. The burner according to claim 1, characterized in that Further comprising at least one of one or more air dilution holes or one or more steam dilution holes in the outer liner or the inner liner, wherein the combustor steam system is operable to inject at least a portion of the steam into the combustion chamber axially rearward of the at least one of the one or more air dilution holes or the one or more steam dilution holes.

5. The burner according to claim 1, characterized in that in, The combustor steam system includes one or more steam cooling holes in at least one of the outer liner, the inner liner, or the annular dome, the one or more steam cooling holes operable to direct the steam therethrough to cool the at least one of the outer liner, the inner liner, or the annular dome.

6. The burner according to claim 1, characterized in that in, The burner steam system includes one or more steam injectors in fluid communication with the steam path, and the one or more steam injectors are operable to inject the steam into the steam path.

7. The burner according to claim 6, characterized in that in, The one or more steam injectors are arranged in an annular manner around the combustion chamber.

8. The burner according to claim 1, characterized in that in, The combustor steam system includes one or more steam injection holes in the at least one of the outer liner, the inner liner, or the annular dome, and the one or more steam injection holes are operable to direct the steam from the steam path into the combustion chamber.

9. The burner according to claim 8, characterized in that in, The one or more steam injection holes are positioned on the outer liner or the inner liner at least 25% of a total combustor length of the combustor.

10. The burner according to claim 8, characterized in that in, The one or more steam injection holes are positioned on the outer liner or the inner liner within a range of 10% to 90% of a total combustion chamber length of the combustion chamber.

Images