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. The annular dome is coupled to the outer liner and the inner liner. A plurality of mix assemblies are operable to inject a fuel-air mixture into the 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 the outer liner, the inner liner, or the 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] This disclosure generally relates to burners, such as burners for turbine engines. Background Technology

[0002] A turbine engine typically includes a fan and a core section arranged in a flow communication with each other. A combustor is located in the core section to generate combustion gases for driving the turbine in the core section of the turbine engine. Attached Figure Description

[0003] The above and other features and advantages will become apparent from the following more detailed description of various exemplary embodiments, as illustrated in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar or structurally similar elements.

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

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

[0006] Figure 3 It is based on this disclosure Figure 2 The details were captured in 3 places. Figure 2 A schematic cross-sectional view of a portion of the burner's outer lining.

[0007] Figure 4 It is based on this disclosure Figure 3 Details extracted from point 4-4 Figure 3 A schematic cross-sectional plan view of a portion of the outer lining.

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

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

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

[0011] Figure 8 It is based on this disclosure Figure 7 Details extracted from point 8-8 Figure 7 A schematic bottom cross-sectional view of a portion of the outer lining.

[0012] Figure 9 This is a schematic bottom cross-sectional view of a portion of the outer liner of a burner according to another embodiment.

[0013] Figure 10 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0014] Figure 11 It is based on this disclosure Figure 10 Details captured at point 11-11 Figure 10 A schematic bottom cross-sectional view of a portion of the outer lining.

[0015] Figure 12 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0016] Figure 13 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0017] Figure 14 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0018] Figure 15 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0019] Figure 16 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0020] Figure 17 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0021] Figure 18 This is a schematic cross-sectional view of a portion of the burner liner taken along the longitudinal centerline axis of the burner according to another embodiment.

[0022] Figure 19 This is a schematic cross-sectional view of a portion of the annular dome of the burner, taken along the longitudinal centerline axis of the burner according to another embodiment.

[0023] Figure 20 Based on this disclosure Figure 19 A schematic rear cross-sectional view of a portion of the annular dome.

[0024] Figure 21 This is a schematic rear view of a portion of the annular dome of the burner according to this disclosure.

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

[0026] Figure 23 This is a schematic cross-sectional view of the burner taken along the longitudinal centerline axis of the burner according to another embodiment. Detailed Implementation

[0027] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0028] Various embodiments of this disclosure are discussed in detail below. While specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0029] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0030] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0031] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and specifically to the normal operating posture of the turbine engine or carrier. For example, in the context of a turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0032] As used herein, when used in conjunction with compressors, burners, turbines, shafts, fans, or turbine engine components, the terms “low,” “medium” (or “medium”) and “high,” or their respective comparatives (e.g., “lower” and “higher,” if applicable), refer to relative pressure, relative speed, relative temperature, or relative power output within the engine, unless otherwise specified. For example, a “low power” setting defines an engine or burner configured to operate at a power output lower than the “high power” setting of the engine or burner, while a “medium power” setting defines an engine or burner 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 terms may additionally or alternatively be understood as relative to a minimum permissible speed, pressure, or temperature, or relative to the minimum or maximum permissible speed, pressure, or temperature for normal, desired, steady-state, etc., operation of the engine or burner.

[0033] The various power levels of the turbine engines detailed herein are defined as a percentage of the maximum engine rated thrust at sea level static (SLS). Low-power operation or conditions include, for example, less than 30 percent (30%) of the turbine engine's maximum engine rated thrust at SLS. Medium-power operation or conditions include, for example, from 30 percent (30%) to 85 percent (85%) of the turbine engine's maximum engine rated thrust at SLS. High-power operation or conditions include, for example, greater than 85 percent (85%) of the turbine engine's maximum engine rated thrust at SLS. The thrust values ​​for each of the low-power, medium-power, and high-power operations of the turbine engine are merely exemplary, and other thrust values ​​may be used to define low-power, medium-power, and high-power operations.

[0034] Unless otherwise stated herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features.

[0035] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0036] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the turbine engine.

[0037] Scope limitations are combined and interchanged herein and throughout the specification and claims. Unless the context or language otherwise indicates, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0038] A turbine engine (such as an aircraft turbine engine) uses a combustor to ignite a fuel-air mixture to produce combustion gases, which in turn drive one or more turbines in 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 specify nitrogen oxides (NOx) emissions from turbine engines. x This includes emissions of non-volatile particulate matter (NVPM) and other types of waste gases. NVPM includes, for example, soot and smoke. Typically, NO is formed during the combustion process due to the high flame temperature in the burner. x Design trade-offs are necessary for turbine engines to meet requirements regarding noise, emissions, fuel combustion, cost, weight, and performance. As temperatures rise in the combustor, NO... x NO formation increases due to higher temperatures. In turbine engine design, it is difficult to balance reducing NO... x Improved engine performance is achieved simultaneously in terms of emissions, NVPM emissions, carbon monoxide (CO), and noise. For example, combustor design changes made to achieve lower emissions must not affect the combustion system's ability to meet performance and certification requirements throughout the aircraft's operational lifecycle.

[0039] Besides balancing emissions reduction with improved engine performance, another trade-off is reducing the specific fuel consumption (SFC) of turbocharged engines. Specific fuel consumption is the amount of fuel a turbocharged engine consumes per unit of power output. Therefore, a lower SFC means consuming less fuel to achieve a specific power output from a turbocharged engine. Some turbocharged engines utilize a combustor where steam is injected into the combustion chamber through fuel injectors. Injecting steam into the combustion chamber reduces SFC and also reduces NO. x Emissions. For example, the more steam injected into the combustor, the greater the reduction in SFC (Self-Fueled Combustion). However, steam during combustion increases CO emissions and can lead to flameout because it blocks the flame (e.g., reducing oxygen in the combustion chamber). Furthermore, this type of turbine engine, which injects steam from fuel nozzles, can achieve a water-to-air ratio (WAR) of up to approximately 5% within the combustor before flameout occurs. Therefore, this turbine engine is limited in terms of emissions and SFC reduction achievable through pre-flameout steam injection.

[0040] Therefore, embodiments of this disclosure provide a system and method for balancing the need for low fuel combustion and low emissions (e.g., NO) in turbine engines.x This disclosure addresses the requirements for emissions (NVPM emissions, CO, and noise) while balancing turbine engine performance, reducing SFC (surface fuel cell emissions), and preventing combustor flameout. Embodiments of this disclosure provide a turbine engine with a combustor having a steam system that allows steam to flow within at least one of the combustor's outer liner, inner liner, or annular dome. Steam flows through channels within the outer liner, inner liner, or annular dome to cool the outer liner, inner liner, or annular dome. Steam is discharged from the outer liner, inner liner, or annular dome or injected into the combustion chamber. At least one of the outer liner or inner liner includes a dilution orifice, and steam is injected through at least one of the dilution orifice or a steam cooling orifice downstream of the dilution orifice (e.g., axially rearward). The annular dome includes at least one of the flame-forming orifice through which steam is injected or a dome cooling orifice. Steam through the flame-forming orifice prevents the flame from expanding radially beyond the steam injected through the flame-forming orifice. Compared to turbine engines and combustors without the benefits of this disclosure, steam is injected at a location away from the flame region (e.g., the combustion zone) to avoid flameout, while also ensuring that more steam is injected into the combustion chamber to reduce SFC.

[0041] Compared to burners without the benefits of this disclosure, the steam system of this disclosure can inject a greater amount of steam into the burner without sacrificing burner operability. For example, steam is injected into the combustion chamber away from the combustion zone to prevent flame extinction in the combustion zone, as the steam is kept away from the flame. This configuration of injecting steam away from the flame allows for a greater amount of steam to be injected into the burner to reduce emissions and SFC, while providing flame stability (e.g., preventing flameout), compared to turbine engines and burners without the benefits of this disclosure. This disclosure provides up to 60% WAR, thereby enabling a greater amount of steam to reduce emissions and SFC, while providing flame stability in the burner (e.g., preventing flameout). Compared to bushings and annular domes without the benefits of this disclosure, the steam in the bushing or annular dome helps to increase the life of the bushing or annular dome.

[0042] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 10 taken along the 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 the longitudinal centerline axis 12 provided 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, which is essentially tubular and defines an annular inlet 20. (As...) Figure 1As schematically shown, housing 18 surrounds the following components in a series flow relationship: compressor section 21, which includes a turbocharger or low-pressure (LP) compressor 22, followed downstream by a high-pressure (HP) compressor 24; combustion section 26; turbine section 27, which includes a high-pressure (HP) turbine 28, followed downstream by a low-pressure (LP) turbine 30; and injection nozzle section 32. A high-pressure (HP) shaft 34 or spool drives the HP turbine 28 to the HP compressor 24, causing the HP turbine 28 and HP compressor 24 to rotate in unison. A low-pressure (LP) shaft 36 drives the LP turbine 30 to the LP compressor 22, causing the LP turbine 30 and LP compressor 22 to rotate in unison. Compressor section 21, combustion section 26, turbine section 27, and injection nozzle section 32 together define the core airflow path.

[0044] for Figure 1 In the embodiment depicted, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 extend outward from disk 42 generally in the radial direction R. Each fan blade 40 is operably coupled to an actuation member 44, which is configured to uniformly change the pitch of the fan blades 40 relative to disk 42, via fan blades 40. Fan blades 40, disk 42, and actuation member 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 located in… Figure 1 The diagram is schematically shown. The gearbox assembly 46 includes a plurality of gears for adjusting the rotational speed of the fan shaft 45, and thus adjusting the rotational speed of the fan 38 relative to the LP shaft 36.

[0045] Still referencing Figure 1 In an exemplary embodiment, disk 42 is covered by a rotatable fan hub 48, which is aerodynamically shaped to facilitate airflow through a plurality of fan blades 40. Furthermore, fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 38 and core turbine engine 16. Nacelle 50 is supported relative to core turbine engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced around nacelle 50. Additionally, a downstream section 54 of nacelle 50 extends over the outer portion of core turbine engine 16 to define a bypass airflow passage 56 therebetween.

[0046] During operation of the turbine engine 10, a certain amount of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the fan section 14. As the certain amount 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 airflow 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 commonly referred to as the bypass ratio. The pressure of the second portion of air 64 then increases 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 burned to provide combustion gases 66.

[0047] Combustion gas 66 is directed into and expands through HP turbine 28, where a portion of the thermal or kinetic energy from the combustion gas 66 is extracted via a successive stage of HP turbine stator blades 68 connected to housing 18 and HP turbine rotor blades 70 connected to HP shaft 34, thus rotating HP shaft 34 to support the operation of HP compressor 24. Combustion gas 66 is then directed into and expands through LP turbine 30. Here, a second portion of thermal or kinetic energy is extracted from the combustion gas 66 via a successive stage of LP turbine stator blades 72 connected to housing 18 and LP turbine rotor blades 74 connected to LP shaft 36, thus rotating LP shaft 36 to support the operation of LP compressor 22 and the rotation of fan 38 via gearbox assembly 46.

[0048] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it is directed through the bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for guiding combustion gas 66 through the core turbine engine 16.

[0049] As detailed above, the second portion of air 64 mixes with fuel 67 in combustion section 26 to produce combustion gases 66. The turbine engine 10 also includes a fuel system 80 for supplying fuel 67 to combustion section 26. Fuel system 80 includes a fuel tank (not shown) for storing fuel therein and one or more fuel injector lines 82 for supplying fuel 67 to combustion section 26, as further detailed below. Fuel system 80 may include one or more valves for controlling the amount of fuel 67 supplied to combustion section 26. Fuel 67 can be any type of fuel used in turbine engines, such as JetA, sustainable aviation fuel (SAF) including biofuels, hydrogen-based fuel (H2), etc. Preferably, fuel 67 is hydrogen-based fuel (H2), which produces a greater amount of water compared to fossil fuels or other types of fuels used in turbine engines. In this way, a greater amount of steam can be generated from the combustion gases 66 of hydrogen-based fuel compared to other types of fuels used in turbine engines.

[0050] The turbine engine 10 includes a steam system 90 in fluid communication with the exhaust nozzle section 32. The steam system 90 generates steam 69 from exhaust gas in the exhaust nozzle section 32. The steam system 90 includes one or more steam lines 92 to supply steam 69 to the combustion section 26, as further detailed below.

[0051] Figure 1 The turbine engine 10 depicted is merely an example. 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. Furthermore, 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 this disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, propeller fan engine, turbojet engine, turboprop engine, and / or turboshaft engine.

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

[0053] Outer liner 204 and inner liner 206 surround the turbine engine 10 ( Figure 1 The longitudinal centerline axis 12 of the combustor 202 is annular. 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 spaced inward from the outer combustor housing 208 and the inner combustor housing 209, which extend 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 orifices 205 operably guiding 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 (e.g., by membrane 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. Combustion chamber 202 extends from annular dome 210 to combustion chamber outlet 211.

[0054] Multiple hybrid components 212 ( Figure 2 (Only one is shown in the diagram) circumferentially spaced around the annular dome 210 to deliver the fuel and air mixture to the combustion chamber 202. For example, multiple mixing assemblies 212 deliver the fuel and air mixture to the combustion zone 203 of the combustion chamber 202, as further detailed below. Figure 2 In this configuration, each mixing assembly 212 includes a mixer 214 and a mixing assembly cyclone separator 216. Multiple fuel injectors 218 ( Figure 2 (Only one is shown) is fluidly connected to a plurality of mixing components 212. A plurality of fuel injectors 218 are circumferentially spaced about an annular dome 210 and extend radially from the outer burner housing 208 to a mixer 214 for each of the plurality of mixing components 212. In some embodiments, the plurality of fuel injectors 218 extend from the inner burner housing 209, or may extend from both the outer burner housing 208 and the inner burner housing 209.

[0055] Burner 200 includes a steam system 90 ( Figure 1 A burner steam system 220 in fluid communication is provided for receiving steam 69 from a steam system 90. The burner steam system 220 includes one or more steam injectors 222 and a steam path 224. One or more steam injectors 222 are located at an outer liner 204 or an inner liner 206 and are connected to the steam line 92 of the steam system 90. Figure 1 The steam system 90 provides fluid communication so that it 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 arranged in annular shape around the combustion chamber 202.

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

[0057] In operation, the burner 200 receives heat from the HP compressor 24 in the diffuser section 250 located upstream of the combustion chamber 202. Figure 1 Compressed air 65 is discharged. 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 swirls the compressed air 65. 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 fuel 67 axially rearward into the combustion zone 203 of the combustion chamber 202 to generate a fuel stream 260. At a mixer 214 of each of the plurality of mixing assemblies 212, the fuel stream 260 is mixed with a first compressed air stream 262 to generate a fuel-air mixture. The fuel-air mixture is either fuel-rich (e.g., a mixture with a higher fuel-air ratio) or fuel-lean (e.g., a mixture with a lower fuel-air ratio). The fuel-air mixture is ignited by an igniter (for clarity, Figure 2 (Not shown) is ignited to generate a flame within the combustion chamber 202, the flame burning the fuel-air mixture and providing combustion gas 66, which is directed downstream to the HP turbine 28 ( Figure 1 The first-stage turbine nozzle. The flame burns in the combustion zone 203 (e.g., adjacent to the mixer 214 and in the region of the annular dome 210) and generates combustion gas 66 in the combustion chamber 202.

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

[0059] Combustion chamber 202 operablely directs combustion gases 66 downstream from combustion zone 203 within combustion chamber 202. The combustion gases 66 from combustion zone 203 are mixed with steam injection stream 270 to generate a steam-combustion mixture 290 within combustion chamber 202. Combustion chamber 202 then operablely directs the steam-combustion mixture 290 out of combustion chamber 202 through combustion chamber outlet 211, and the steam-combustion mixture 290 is directed downstream to HP turbine 28. Figure 1 The first stage turbine nozzle.

[0060] Steam system 90 can be used in turbine engine 10 ( Figure 1 The steam injection into combustion chamber 202 is varied during various operating conditions of the mission cycle. Mission cycles include, for example, low-power operation, medium-power operation, and high-power operation. Low-power operation includes, for example, engine start, idling, taxiing, and approach. Medium-power operation includes, for example, cruise. High-power operation includes, for example, takeoff and climb. During low-power operation, combustor steam system 220 does not inject steam 69 into combustion chamber 202. During medium-power and high-power operation, combustor steam system 220 operably injects steam 69. During high-power operation, combustor steam system 220 operably injects a larger amount of steam 69 than during medium-power operation.

[0061] Injecting steam 69 downstream of combustion zone 203 (e.g., downstream of the flame) provides flame stability, and the steam 69 in combustion chamber 202 lowers the temperature of the combustion gases 66 in combustion chamber 202. In this way, the flame operates at a higher temperature, and the steam 69 lowers the flame temperature. The combustor steam system 220 makes the water-air ratio (WAR) of steam 69 to compressed air 65 in combustion chamber 202 as high as 60%. For example, the WAR is 0.0% to 60%, and preferably 5% to 60%. In some embodiments, the WAR is 0.0% to 60% based on the turbine engine's operating conditions (e.g., start-up, idling, coasting, take-off, climb, cruise, descent). For example, the WAR in combustion chamber 202 is 0% to 30% (0% to 30%) during low-power conditions, 1% to 40% (1% to 40%) during medium-power conditions, and 2% to 60% (2% to 60%) during high-power conditions. In this way, in turbine engine 10 ( Figure 1 During any operating conditions above idle, steam 69 is injected into combustion chamber 202. Therefore, compared to turbine engines and combustors that do not offer the benefits of this disclosure, the steam 69 injected into combustion chamber 202 downstream of combustion zone 203 enables reduced emissions (NOx emissions, NVPM emissions, CO emissions, noise) and a lower specific fuel capacity (SFC), while preventing flameout within combustion zone 203.

[0062] Figure 3 It is based on this disclosure Figure 2 A schematic cross-sectional view of a portion of the outer liner 204 of the burner 200, taken from detail 3. Figure 4 It is based on this disclosure Figure 3 Details extracted from point 4-4 Figure 3 A schematic cross-sectional plan view of a portion of the outer lining 204. (See attached image.) Figure 3 As shown, the steam path 224 extends axially within the liner 204 and includes a front portion 230 axially forward of one or more air dilution orifices 205 and a rear portion 232 axially backward of one or more air dilution orifices 205. Figure 4 As shown, the steam path 224 extends circumferentially within the liner 204. In this way, the steam path 224 is about the longitudinal centerline axis 12 ( Figure 1 It is ring-shaped.

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

[0064] One or more steam injection holes 226 are located downstream of one or more air dilution holes 205. For example, one or more steam injection holes 226 are axially positioned behind one or more air dilution holes 205. In some embodiments, one or more steam injection holes 226 are positioned at at least 20% of the total length of the combustion chamber 202 in an axial location. In this way, one or more steam injection holes 226 are positioned downstream (e.g., axially rearward) of the combustion zone 203. The dimensions of each of the one or more steam injection holes 226, the number of one or more steam injection holes 226, and the circumferential spacing between the respective steam injection holes in the one or more steam injection holes 226 are based on the desired amount of steam flow to generate the steam injection flow 270 within the combustion chamber 202. Additionally, although Figure 4 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, one or more steam injection holes 226 may be elliptical grooves, etc.

[0065] In operation, burner 200 and burner steam system 220 operate as described above. Specifically, burner 200 is operably directed compressed air 65 through one or more air dilution orifices 205 to generate a second compressed air flow 264 in combustion chamber 202. The second compressed air flow 264 helps cool the combustion gas 66 from combustion zone 203 as it is directed downstream through combustion chamber 202. Burner steam system 220 is operably directed steam 69 from steam path 224 through one or more steam injection orifices 226 and into combustion chamber 202 downstream of combustion zone 203, thereby generating a steam injection flow 270 within combustion chamber 202. In this way, steam injection flow 270 is downstream of combustion zone 203. One or more steam injection orifices 226 are operably directed radially into combustion chamber 202. The steam injection stream 270 is operatively mixed with the combustion gas 66 from the combustion zone 203 to generate a steam-combustion gas mixture 290, as detailed above.

[0066] Figure 5This is a schematic cross-sectional plan view of a portion of the outer liner 504 of a burner 500 according to another embodiment. The burner 500 is substantially similar to... Figure 2 The burner 200 includes a number of components identical or similar to those in the burner 200. The liner 504 includes one or more air dilution orifices 505 and a burner steam system 520. The burner steam system 520 includes one or more steam injectors 522, a steam path 524 defined by (e.g., disposed within) the liner 504, and one or more steam injection orifices 526. The one or more steam injectors 522 are positioned upstream (e.g., axially forward) of the one or more air dilution orifices 505. The steam path 524 is different from... Figure 2 The steam path 524. Specifically, the steam path 524 does not extend annularly around the liner 504. Instead, the steam path 524 comprises one or more discrete steam paths 524, each comprising one or more circumferentially extending portions 525 and one or more axially extending portions 527 fluidly connected to the circumferentially extending portions 525. In this way, the steam path 524 defines one or more channels within the liner 504, rather than a continuously extending steam path, such as... Figure 2 Steam path 224.

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

[0068] The operation of burner 500 and burner steam system 520 is basically similar to that of burner 500 and burner steam system 520, respectively. Figure 2The burner 200 and burner steam system 220. Specifically, the burner steam system 520 operably directs steam 69 into a steam path 524 via one or more steam injectors 522. The steam path 524 operably directs steam 69 around a generally zigzag shape. One or more steam injection holes 526 operably direct steam 69 through them to the combustion chamber (e.g., Figure 2 A steam injection flow is generated within the combustion chamber 202. The approximate zigzag shape of the steam path 524 allows the steam 69 to cool various locations of the liner 504, rather than through a channel. Figure 2 The steam path 224 cools the entire liner. Various shapes of steam paths 524 can be selected to cool the liner 504 at various locations as needed.

[0069] Figure 6 This is a schematic cross-sectional plan view of a portion of the outer liner 604 of a burner 600 according to another embodiment. The burner 600 is substantially similar to... Figure 2 The burner 200 includes a number of components identical or similar to those in the burner 200. The liner 604 includes one or more air dilution orifices 605 and a burner steam system 620. The burner steam system 620 includes one or more steam injectors 622, a steam path 624 defined by (e.g., disposed within) the liner 604, and one or more steam injection orifices 626. The one or more steam injectors 622 are positioned upstream (e.g., axially forward) of the one or more air dilution orifices 605. The steam path 624 is different from... Figure 2 The steam path 624. Specifically, the steam path 624 does not extend annularly around the liner 604. Instead, the steam path 624 includes one or more discrete steam paths 624, each including one or more circumferentially extending portions 625 and one or more axially extending portions 627 fluidly connected to the circumferentially extending portions 625. In this way, the steam path 624 defines one or more channels within the liner 604, rather than a continuously extending steam path, for example... Figure 2 Steam path 224.

[0070] One or more circumferential extensions 625 extend circumferentially from one or more steam injectors 622. One or more axial extensions 627 are fluidly coupled to one or more circumferential extensions 625. One or more axial extensions 627 extend axially rearward from one or more circumferential extensions 625. One or more axial extensions 627 extend axially rearward of one or more air dilution orifices 605. In this way, the steam path 624 includes a front portion 630 axially forward of one or more air dilution orifices 605 and a rear portion 632 axially rearward of one or more air dilution orifices 605. One or more axial extensions 627 are circumferentially spaced around the liner 604.

[0071] One or more steam injection holes 626 are in fluid communication with a steam path 624. The one or more steam injection holes 626 are positioned in a 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 one or more air dilution holes 605. The one or more steam injection holes 626 are positioned on one or more of one or more axially extended portions 627 of the steam path 624. For example, each of the one or more axially extended portions 627 includes one or more of the one or more steam injection holes 626.

[0072] The operation of burner 600 and burner steam system 620 is basically similar to that of burner 600 and burner steam system 620, respectively. Figure 2 The burner 200 and burner steam system 220. Specifically, the burner steam system 620 operably directs steam 69 into a steam path 624 via one or more steam injectors 622. The steam path 624 operably directs steam 69 through one or more circumferential extensions 625 and through one or more axial extensions 627. One or more steam injection holes 626 operably direct steam 69 through them to, in the combustion chamber (e.g., Figure 2 The combustion chamber 202) generates a steam injection flow downstream of the combustion zone. One or more axially extending portions 627 allow steam 69 to cool various locations of the liner 604, rather than through... Figure 2 The steam path 224 cools the entire liner. Various shapes of steam paths 624 can be selected to cool the liner 604 at various locations as needed.

[0073] Figure 7 This is a schematic cross-sectional view of a portion of the outer liner 704 of the burner 700, taken along the longitudinal centerline axis of the burner 700 according to another embodiment. Figure 8 It is based on this disclosure Figure 7 A schematic cross-sectional bottom view of a portion of the outer liner 704, taken at detail 8-8. The burner 700 is essentially similar to... Figure 2The burner 200. The same reference numerals will be used for components of the burner 700 that are the same as or similar to those of the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are 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 a liner 704 (e.g., disposed within the liner 704), and one or more steam injection holes 726. Figure 7 As shown, the steam path 724 extends axially within the liner 704. The steam path 724 can be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include one or more discrete steam paths similar to steam paths 524 and 624. The liner 704 does not include one or more air dilution holes.

[0074] The burner steam system 720 includes a steam manifold 723 and one or more steam dilution orifices 728. The steam manifold 723 is radially fluidly connected between one or more steam injectors 722 and a steam path 724. The steam manifold 723 allows for pressure reduction of steam 69 before it flows into the steam path 724. The steam manifold 723 is sized and shaped to provide a substantially uniform distribution of steam 69 to one or more steam injectors 726 and one or more steam dilution orifices 728. In this way, the steam manifold 723 ensures a controlled and stable supply of steam 69 to various locations within the burner steam system 720 at the desired pressure. The steam manifold 723 may comprise a plurality of discrete steam manifolds circumferentially spaced around the combustion chamber 202, or it may comprise a single steam manifold arranged annularly around the combustion chamber 202.

[0075] One or more steam dilution orifices 728 are circumferentially spaced around the liner 704 and operably guide steam 69 through them into the combustion chamber 202. The one or more steam dilution orifices 728 are larger than the one or more steam injection orifices 726. In this way, the one or more steam dilution orifices 728 operably guide a larger amount of steam 69 into the combustion chamber 202 than the one or more steam injection orifices 726. The size of each of the one or more steam dilution orifices 728, the number of the one or more steam dilution orifices 728, and the circumferential spacing between the corresponding steam dilution orifices in the one or more steam dilution orifices 728 are based on the desired amount of steam flow within the combustion chamber 202. Additionally, although... Figure 7 and Figure 8 One or more vapor dilution orifices 728 are depicted as generally circular openings, but alternatively, other shapes may be implemented for the openings. For example, one or more vapor dilution orifices 728 may be elliptical grooves, etc.

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

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

[0078] The operation of burner 700 and burner steam system 720 is basically similar to that of burner 700 and burner steam system 720, respectively. Figure 2 The burner 200 and burner steam system 220. Specifically, the burner steam system 720 operably directs steam 69 through one or more steam injectors 722, through a steam manifold 723, and into a steam path 724 to cool the liner 704. For example, steam 69 flows through one or more front steam inlet holes 733 and into the front portion 730 of the steam path 724. Steam 69 also flows through one or more rear steam inlet holes 735 and into the rear portion 733 of the steam path 724. The dimensions of the one or more front steam inlet holes 733 and the one or more rear steam inlet holes 735 can be set to control the pressure drop between the front portion 730 and the rear portion 733 (e.g., in front of and behind 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 comprise substantially equal dimensions, such that a single pressure drop exists in front of and behind one or more steam dilution holes 728. For example, the pressure drop through one or more front steam inlet holes 733 is substantially equal to the pressure drop through one or more rear steam inlet holes 735. In some embodiments, the size of one or more front steam inlet holes 733 is set to be different from (e.g., larger or smaller than) one or more rear steam inlet holes 735, such that the pressure drop in front of one or more steam dilution holes 728 is different from the pressure drop behind one or more steam dilution holes 728, resulting in multiple pressure drops across one or more steam dilution holes 728.

[0079] One or more steam injection orifices 726 operably guide steam 69 through them to generate a first steam injection stream 770 within the combustion chamber 202. One or more steam dilution orifices 728 operably guide steam 69 through them to generate a second steam injection stream 772 and enter the combustion chamber 202. The second steam injection stream 772 comprises a larger amount of steam 69 than the first steam injection stream 770. For example, the dimensions of one or more steam dilution orifices 728 and one or more steam injection orifices 726 are set such that the second steam injection stream comprises more than 50% of the steam 69 injected into the combustion chamber 202, and the first steam injection stream comprises less than 50% of the steam 69 injected into the combustion chamber 220. In some embodiments, the second steam injection stream comprises 40% to 100% of the steam 69, and the first steam injection stream comprises 0.0% to 60% of the steam 69. Combustion gases 66 from the combustion zone are mixed 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] Figure 9 This is a schematic bottom cross-sectional view of a portion of the outer liner 904 of a burner 900 according to another embodiment. The burner 900 is substantially similar to... Figure 2 and Figure 7 The burners 200 and 700 are described above. The same reference numerals will be used for components of burner 900 that are identical or similar to those of burners 200 and 700 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. Burner 900 includes a burner steam system 920, which is substantially similar to... Figure 7 The burner steam system 720 includes one or more steam injection ports 926 and one or more steam dilution ports 928. The burner 900 also includes one or more air dilution ports 905. The one or more steam dilution ports 928 and the one or more air dilution ports 905 are circumferentially spaced and alternate around the liner 904.

[0081] The operation of burner 900 and burner steam system 920 is basically similar to that of burner 900 and burner steam system 920, respectively. Figure 2 and Figure 7 The burners 200, 700 and the burner steam systems 220, 720. Specifically, one or more air dilution ports 905 operably dilute compressed air 65 ( Figure 2 ) Guided to combustion chamber 202 ( Figure 2 In the combustion chamber 202, one or more steam injection holes 926 and one or more steam dilution holes 928 operably direct steam 69 into the combustion chamber 202, as described above. Figure 7 Detailed explanation.

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

[0083] The burner steam system 1020 also includes one or more steam channels 1029, which are positioned axially rearward of one or more steam dilution orifices 1028 and axially forward of one or more steam injection orifices 1026. The one or more steam channels 1029 are arcuate channels that operatively guide steam 69 through them and into the combustion chamber 202. The dimensions of each of the one or more steam channels 1029, the number of the one or more steam channels 1029, and the circumferential spacing between the respective steam channels in the one or more steam channels 1029 are based on the desired amount of steam flow within the combustion chamber 202. Additionally, although... Figure 10 and Figure 11 One or more steam channels 1029 are depicted as having generally arc-shaped openings, but alternatively, other shapes may be implemented for the openings. For example, one or more steam channels 1029 may be generally straight channels, etc.

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

[0085] The operation of burner 1000 and burner steam system 1020 is basically similar to that of burner 1000 and burner steam system 1020, respectively. Figure 2 and Figure 7 The burners 200 and 700 and the burner steam systems 220 and 720. Specifically, the burner steam system 1020 operably directs steam 69 through one or more steam injectors 1022, through a steam manifold 1023, and into a steam path 1024 to cool the liner 1004. For example, steam 69 flows through one or more front steam inlet ports 1033 and into the front portion 1030 of the steam path 1024. Steam 69 also flows through one or more rear steam inlet ports 1035 and into the rear portion 1033 of the steam path 1024.

[0086] One or more steam injection holes 1026 operably guide steam 69 through them to generate a first steam injection stream 1070 within the combustion chamber 202. One or more steam dilution holes 1028 operably guide steam 69 through them to generate a second steam injection stream 1072 and enter the combustion chamber 202. One or more steam channels 1029 operably guide steam 69 through them 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 through the one or more steam dilution holes 1028. Combustion gases 66 from the combustion zone are mixed 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] Figure 12 This is a schematic cross-sectional view of a portion of the outer liner 1204 of the burner 1200, taken along the longitudinal centerline axis of the burner 1200 according to another embodiment. The burner 1200 is substantially similar to... Figure 2 The burner 200 includes a number of components that are the same as or similar to those of the burner 200. The same reference numerals will be used for components of the burner 1200 that are the same as or similar to those of the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. 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 a liner 1204 (e.g., disposed within the liner 1204), and one or more steam injection holes 1226. Figure 12 As shown, the steam path 1224 extends axially within the liner 1204. The steam path 1224 can be similar to... Figure 2The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6 One or more discrete steam paths 524 and 624. Steam path 1224 includes a front section 1230 and a rear section 1232.

[0088] The liner 1204 includes one or more air dilution orifices 1205 and one or more air impingement orifices 1207. The one or more air dilution orifices 1205 are operable to direct compressed air 65 into the combustion chamber 202. The one or more air impingement orifices 1207 are operable to direct compressed air 65 into the steam path 1224, as further detailed below. The one or more air impingement orifices 1207 are configured to extend radially outward from the liner 1204 to operablely direct compressed air 65 into the steam path 1224. In some embodiments, the liner 1204 does not include one or more air impingement orifices 1207.

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

[0090] The burner steam system 1220 includes one or more steam cooling holes 1231 configured to pass through a liner 1204, providing fluid communication from a steam path 1224 and a combustion chamber 202. The one or more steam cooling holes 1231 are axially angled rearward relative to the longitudinal centerline of the burner 1200, such that steam 69 flows axially rearward through the one or more steam cooling holes 1231 to provide film cooling on the liner 1204. In this way, the one or more steam cooling holes 1231 axially guide steam 69 along the liner 1204 to film cool the liner 1204. In some embodiments, the one or more steam cooling holes 1231 are axially angled forward, such that 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 rearward and one or more steam cooling holes 1231 angled forward.

[0091] One or more steam cooling holes 1231 are circumferentially spaced around the liner 1204 and axially spaced on the liner 1204. The one or more steam cooling holes 1231 include one or more steam cooling holes 1231 disposed axially forward of 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 one or more steam injection holes 1226. The dimensions 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 the respective steam cooling holes in the one or more steam cooling holes 1231 are based on the desired amount of steam flow for film cooling of the liner 1204. Additionally, although... Figure 12 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, one or more steam cooling holes 1231 may be elliptical slots, etc.

[0092] The operation of burner 1200 and burner steam system 1220 is basically similar to that of burner 1200 and burner steam system 1220, respectively. Figure 2 The burner 200 and burner steam system 220. Specifically, the burner 1200 is operably directed to direct compressed air 65 through one or more air dilution orifices 1205 into the combustion chamber 202 to generate a second compressed air flow 1264 within the combustion chamber 202. The burner 1200 is also operably directed to direct compressed air 65 through one or more air impingement orifices 1207 into the steam path 1224 to generate an impingement air flow 1265 within the steam path 1224. The impingement air flow 1265 helps to cool the steam 69 within the steam path 1224 because the steam 69 within the steam path 1224 absorbs heat from the liner 1204 to cool the liner 1204.

[0093] The burner steam system 1220 operably directs 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 liner 1204. The steam path 1224 operably directs the steam 69 axially forward such that the steam 69 flows within the steam path 1224 in the opposite direction to the combustion gases 66 within the combustion chamber 202. For example, the steam 69 flows from the rear 1232 to the front 1230. One or more steam injection holes 1226 operably direct steam 69 through them to generate a steam injection flow 1270 within the combustion chamber 202. One or more steam cooling holes 1231 operably direct steam 69 through them to generate a steam cooling flow 1276 and enter the combustion chamber 202 to film-cool the liner 1204. Combustion gas 66 from the combustion zone is mixed with steam injection stream 1270 and steam cooling stream 1276 to generate a steam-combustion gas mixture 1290 that is directed downstream and leaves the combustion chamber 202.

[0094] Figure 13 This is a schematic cross-sectional view of a portion of the outer liner 1304 of the burner 1300, taken along the longitudinal centerline axis of the burner 1300 according to another embodiment. The burner 1300 is substantially similar to... Figure 2 The burner 200 includes a number of components identical or similar to those in the burner 200. The burner 1300 includes one or more air dilution orifices 1305 operably guiding compressed air 65 through it. The burner 1300 includes a heat shield 1352 coupled to an outer liner 1304 for protecting the outer liner 1304 from hot combustion gases 66. The heat shield 1352 is secured by one or more fasteners (in... Figure 13 (Not shown in the view) (e.g., bolts, etc.) are attached to the outer liner 1304.

[0095] Burner 1300 includes a burner steam system 1320. The burner steam system 1320 includes one or more steam injectors 1322, a steam path 1324, and one or more steam injection ports 1326. The steam path 1324 is defined by a liner 1304 and a heat shield 1352. For example, the steam path 1324 extends axially between the liner 1304 and the heat shield 1352. The steam path 1324 may be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6One or more discrete steam paths 524, 624. Steam path 1324 includes a front portion 1330 and a rear portion 1332. The front portion 1330 is axially ahead of one or more air dilution orifices 1305, and the rear portion 1332 is axially behind one or more air dilution orifices 1305. The front portion 1330 and the rear portion 1332 are fluidly separated, thereby preventing steam 69 from flowing from the rear portion 1332 to the front portion 1330.

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

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

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

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

[0100] The burner steam system 1320 operably directs 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 the rear portion 1332 of the steam path 1324 to cool the liner 1304 and the heat shield 1352 at the rear portion 1332. The steam path 1324 operably directs steam 69 axially forward such that steam 69 flows within the steam path 1324 in the opposite direction to the combustion gas 66 within the combustion chamber 202. The steam manifold 1323 operably directs steam 69 through one or more steam manifold lines 1342, through one or more second steam injector lines 1344, and into the front portion 1330 of the steam path 1324 to cool the liner 1304 and the heat shield 1352 at the front portion 1330.

[0101] One or more steam injection orifices 1326 operatively guide steam 69 through them to generate a steam injection stream 1370 within the combustion chamber 202 at the front 1330 and rear 1332 of the steam path 1324. The steam injection stream 1370 from the rear 1332 comprises a larger amount of steam 69 than the steam injection stream 1370 from the front 1330. For example, the steam 69 injected from the rear 1332 comprises 50% to 80% of the steam 69 from the steam path 1324, and the steam 69 injected from the front 1330 comprises 20% to 50% of the steam 69 from the steam path 1324. Combustion gases 66 from the combustion zone are mixed with the steam injection stream 1370 to generate a steam-combustion gas mixture 1390 that is directed downstream and exits the combustion chamber 202.

[0102] Figure 14 This is a schematic cross-sectional view of a portion of the outer liner 1404 of the burner 1400, taken along the longitudinal centerline axis of the burner 1400 according to another embodiment. The burner 1400 is substantially similar to... Figure 2The burner 200 includes a number of components identical or similar to those of the burner 200. The same reference numerals will be used for components of the burner 1400 that are identical or similar to those of the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. The burner 1400 includes one or more air dilution orifices 1405 operably guiding compressed air 65 through them. The burner 1400 includes a heat shield 1452 coupled to a liner 1404 for protecting the liner 1402 from the effects of hot combustion gases 66. The one or more air dilution orifices 1405 include dilution orifice inserts 1409 disposed within the one or more air dilution orifices 1405. The one or more air dilution orifices 1405 also include dilution orifice supports 1413 extending axially through the one or more air dilution orifices 1405 to absorb thermal expansion between the heat shield 1452 and the liner 1404. In this way, the dilution orifice support 1413 helps prevent one or more air dilution orifices 1405 from closing due to thermal expansion of the liner 1404 or the heat shield 1452. The dilution orifice support 1413 also helps prevent or minimize the mixing of steam 69 from steam path 1424 and compressed air 65 from air path 1415 of burner 1400.

[0103] Air path 1415 is defined by liner 1404 and heat shield 1452. For example, air path 1415 is defined between liner 1404 and heat shield 1452 axially forward of one or more air dilution orifices 1405. Combustor 1400 includes one or more air impingement orifices 1407 configured to communicate fluidly through liner 1404 and air path 1415. The one or more air impingement orifices 1407 are configured axially forward of the one or more air dilution orifices 1405. Combustor 1400 includes one or more air injection orifices 1408 configured to communicate fluidly through heat shield 1452 between air path 1415 and combustion chamber 202 upstream of the one or more air dilution orifices 1405. The one or more air injection orifices 1408 are axially rearwardly angled relative to longitudinal centerline axis of combustor 1400, such that compressed air 65 flows axially rearward through the one or more air injection orifices 1408 to provide air film cooling on heat shield 1452. In this manner, one or more air injection holes 1408 axially guide compressed air 65 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 forward such that compressed air 65 flows 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 rearward and one or more air injection holes 1408 angled forward.

[0104] Burner 1400 includes a burner steam system 1420. The burner steam system 1420 includes one or more steam injectors 1422, a steam path 1424 disposed between the liner 1404 and the heat shield 1452, and one or more steam injection ports 1426. Figure 14 As shown, the steam path 1424 extends axially between the outer liner 1404 and the heat shield 1452. The steam path 1424 can be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6 One or more discrete steam paths 524, 624. Steam path 1424 is located axially rear of one or more air dilution orifices 1405. Steam path 1424 is fluidly separated from air path 1415, thereby preventing steam 69 from flowing from steam path 1424 to air path 1415.

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

[0106] The operation of burner 1400 and burner steam system 1420 is basically similar to that of burner 1400 and burner steam system 1420, respectively. Figure 2 The combustor 200 and combustor steam system 220. Specifically, the combustor 1400 is operable to direct compressed air 65 into the combustion chamber 202 through one or more air dilution orifices 1405 to generate a second compressed air flow 1464 within the combustion chamber 202. The combustor 1400 is operable to direct compressed air 65 into the air path 1415 through one or more air impingement orifices 1407 to generate an impingement air flow 1465 within the air path 1415. One or more air injection orifices 1408 are operable to direct compressed air 65 (e.g., impingement air flow 1465) from the air path 1415 into the combustion chamber 202 to generate an air injection flow 1466, thereby cooling the heat shield 1452 by membrane cooling.

[0107] The burner steam system 1420 operably directs 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 liner 1404 and heat shield 1452 axially rearward of one or more air dilution orifices 1405. The steam path 1424 operably directs steam 69 axially forward such that steam 69 flows within the steam path 1424 in the opposite direction to the combustion gas 66 within the combustion chamber 202. One or more steam injection orifices 1426 operably direct steam 69 through them to generate a steam injection stream 1470 downstream of one or more air dilution orifices 1405 within the combustion chamber 202. The combustion gas 66 from the combustion zone mixes with a second compressed air stream 1464, the air injection stream 1466, and the steam injection stream 1470 to generate an air-steam-combustion gas mixture 1490 that is directed downstream and exits the combustion chamber 202.

[0108] Figure 15 This is a schematic cross-sectional view of a portion of the outer liner 1504 of the burner 1500, taken along the longitudinal centerline axis of the burner 1500 according to another embodiment. The burner 1500 is substantially similar to... Figure 2 and Figure 14 The burners 200 and 1400 include a number of components that are the same as or similar to those in burners 200 and 1400. The same reference numerals will be used for components in burner 1500 that are the same as or similar to those in burners 200 and 1400. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. Burner 1500 includes a heat shield 1552 coupled to an outer liner 1504 for protecting the outer liner 1504 from the effects of hot combustion gases 66.

[0109] Burner 1500 includes burner steam system 1520. Burner steam system 1520 includes one or more steam injectors 1522, a steam path 1524 defined by liner 1504 and heat shield 1552 (e.g., disposed between liner 1504 and heat shield 1552), and one or more steam injection ports 1526. Figure 15 As shown, the steam path 1524 extends axially between the outer liner 1504 and the heat shield 1552. The steam path 1524 can be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6One or more discrete steam paths 524, 624. Steam path 1524 is located axially rear of one or more air dilution orifices 1405. Steam path 1524 is fluidly separated from air path 1415, thereby preventing steam 69 from flowing from steam path 1524 to 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 a steam path 1524. The steam manifold wall 1556 includes one or more steam impingement holes 1558 configured to operatively guide steam 69 from the steam manifold 1523 to the steam path 1524, as further detailed below.

[0111] The operation of burner 1500 and burner steam system 1520 is basically similar to that of the other two. Figure 2 and Figure 14 The combustors 200 and 1400 and the combustor steam systems 220 and 1420. Specifically, the combustor steam system 1520 operably directs steam 69 through one or more steam injectors 1522, through a steam manifold 1523, and through one or more steam impingement orifices 1558 to generate a steam impingement flow 1575 within a steam path 1524. In this way, the steam impingement flow 1575 impinges on a heat shield 1552 within the steam path 1524 to cool the heat shield 1552. One or more steam injection orifices 1526 operably direct steam 69 through them to generate a steam injection flow 1570 downstream of one or more air dilution orifices 1405 within a combustion chamber 202. Combustion gases 66 from the combustion zone mix 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] Figure 16 This is a schematic cross-sectional view of a portion of the outer liner 1604 of the burner 1600, taken along the longitudinal centerline axis of the burner 1600 according to another embodiment. The burner 1600 is substantially similar to... Figure 2 , Figure 14 and Figure 15The burners 200, 1400, and 1500 include a number of components that are the same as or similar to those in burners 200, 1400, and 1500. The same reference numerals will be used for components in burner 1600 that are the same as or similar to those in burners 200, 1400, and 1500 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. Burner 1600 includes a heat shield 1652 coupled to an outer liner 1604 for protecting the outer liner 1604 from the hot combustion gases 66. However, burner 1600 does not include components similar to... Figure 14 The air path of 1415.

[0113] Burner 1600 includes a burner steam system 1620. The burner steam system 1620 includes one or more steam injectors 1622, a steam path 1624 defined by a liner 1604 and a heat shield 1652 (e.g., disposed between the liner 1604 and the heat shield 1652), and one or more steam injection ports 1626. Figure 16 As shown, the steam path 1624 extends axially between the outer liner 1604 and the heat shield 1652. The steam path 1624 can be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6 One or more discrete steam paths 524 and 624. Steam path 1624 includes a front portion 1630 axially forward of one or more air dilution orifices 1405 and a rear portion 1632 axially rearward of one or more air dilution orifices 1405. The rear portion 1632 is fluidly connected to the front portion 1630 such that steam 69 flows from the rear portion 1632 to the front portion 1630, as further detailed below. Burner steam system 1620 includes a steam manifold 1623 extending in the front portion 1630 and the rear portion 1632. 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 configured therethrough, which operatively guide steam 69 from the steam manifold 1623 to the front 1630 and rear 1632 of the steam path 1624, as further detailed below.

[0114] The operation of burner 1600 and burner steam system 1620 is basically similar to that of burner 1600 and burner steam system 1620, respectively. Figure 2 , Figure 14 and Figure 15The burners 200, 1400, 1500 and burner steam systems 220, 1420, 1520. Specifically, burner steam system 1620 operably directs steam 69 through one or more steam injectors 1622, through a steam manifold 1623 and through one or more steam impingement orifices 1658 to generate a steam impingement flow 1675 within the rear portion 1632 of steam path 1624. Steam manifold 1623 operably directs steam 69 from the rear portion 1632 to the front portion 1630. For example, although in Figure 16 Not shown in the view, but the front portion 1630 and the rear portion 1632 are fluidly connected around one or more air dilution holes 1405, such that 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 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 way, the steam impingement flow 1675 impinges on the heat shield 1652 within the steam path 1624 to cool the heat shield 1652. One or more steam injection holes 1626 operatively guide steam 69 through them to generate a steam injection flow 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 larger quantity of steam 69 than the steam injection flow 1670 from the front portion 1630. For example, the steam 69 injected from the rear 1632 comprises 50% to 80% of the steam 69 from the steam path 1624, and the steam 69 injected from the front 1630 comprises 20% to 50% of the steam 69 from the steam path 1624. The combustion gases 66 from the combustion zone are mixed with the steam injection stream 1670 to generate an air-steam-combustion gas mixture 1690 that is directed downstream and exits the combustion chamber 202.

[0115] Figure 17 This is a schematic cross-sectional view of a portion of the outer liner 1704 of the burner 1700, taken along the longitudinal centerline axis of the burner 1700 according to another embodiment. The burner 1700 is substantially similar to... Figure 2 and Figure 16 The burners 200 and 1600 include a number of components that are the same as or similar to those in burners 200 and 1600. The same reference numerals will be used for components in burner 1700 that are the same as or similar to those in burners 200 and 1600 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0116] Burner 1700 includes burner steam system 1720. Burner steam system 1720 is essentially similar to... Figure 16The burner steam system 1620 includes one or more steam injectors 1722, each including a first steam injector 1722a and a second steam injector 1722b disposed at the liner 1704. The first steam injector 1722a is in fluid communication with the front section 1630. The second steam injector 1722b is in fluid communication with the rear section 1632. The operation of the burner 1700 and the burner steam system 1720 is substantially similar to that of the burner 1600 and the burner steam system 1620, respectively. Specifically, the burner steam system 1720 is operatively directed to conduct steam 69 through the first steam injector 1722a and into the front section 1630. The burner steam system 1720 is operatively directed to conduct steam 69 through the second steam injector 1722b and into the rear section 1632.

[0117] Figure 18 This is a schematic cross-sectional view of a portion of the outer liner 1804 of the burner 1800, taken along the longitudinal centerline axis of the burner 1800 according to another embodiment. The burner 1800 is substantially similar to... Figure 2 The burner 200 includes a number of components that are the same as or similar to those in the burner 200. The same reference numerals will be used for components in the burner 1800 that are the same as or similar to those in the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. The burner 1800 includes one or more air dilution orifices 1805 operably guiding compressed air 65 through it. Each air dilution orifice 1805 includes a dilution orifice insert 1809 and a dilution orifice support 1813. The burner 1800 includes a heat shield 1852 coupled to an outer liner 1804 for protecting the outer liner 1804 from the effects of hot combustion gases 66.

[0118] The burner 1800 includes a plurality of mixing assemblies 1812, each including a mixer 1814 and a fuel injector 1818 disposed through an annular dome 210. The fuel injector 1818 includes a fuel supply line 1819 and a fuel path 1821. The fuel supply line 1819 is positioned axially rearward of one or more air dilution orifices 1805 and extends radially to a liner 1804. The fuel path 1821 is disposed within the liner 1804 and is in fluid communication with the fuel supply line 1819 and the fuel injector 1818. The fuel path 1821 extends substantially axially from the fuel supply line 1819 to the fuel injector 1818 through the liner 1804. For example, although in Figure 18 Not shown in the view, but the fuel path 1821 is fluidly connected around one or more air dilution holes 1805, such that fuel 67 flows within the fuel path 1821 around one or more air dilution holes 1805.

[0119] Burner 1800 includes a burner steam system 1820. The burner steam system 1820 includes one or more steam injectors 1822, a steam path 1824 defined by a liner 1804 and a heat shield 1852 (e.g., disposed between the liner 1804 and the heat shield 1852), and one or more steam injection ports 1826. Figure 18 As shown, the steam path 1824 extends axially between the outer liner 1804 and the heat shield 1852. The steam path 1824 can be similar to... Figure 2 The steam path 224 is circular around the longitudinal centerline axis, or may include paths similar to... Figure 5 and Figure 6 One or more discrete steam paths 524, 624. Steam path 1824 includes a front section 1830 and a rear section 1832. The front section 1830 is fluidly connected to the rear section 1832, such that steam 69 flows from the rear section 1832 to the front section 1830. For example, although in Figure 18 Not shown in the view, but the front 1830 and rear 1832 of the steam path 1824 are fluidly connected around one or more air dilution orifices 1805, such that steam 69 flows from the rear 1832 to the front 1830 around the one or more air dilution orifices 1805. The burner steam system 1820 includes one or more steam injection orifices 1826 configured to pass through a heat shield 1852, providing fluid communication from the steam path 1824 to the combustion chamber 202. The one or more steam injection orifices 1826 are angled relative to the longitudinal centerline axis of the burner 1800 to provide film cooling on the heat shield 1852.

[0120] The operation of burner 1800 and burner steam system 1820 is basically similar to that of burner 1800 and burner steam system 1820, respectively. Figure 2 The combustor 200 and combustor steam system 220 are included. Specifically, the combustor 1800 operatively directs compressed air 65 through an annular dome 210 to generate a first compressed air flow 1862 within the combustion zone 203 of the combustion chamber 202. The combustor 1800 operatively directs compressed air 65 into the combustion chamber 202 through one or more air dilution orifices 1805 to generate a second compressed air flow 1864 within the combustion chamber 202. A fuel supply line 1819 operatively directs fuel 67 into a fuel path 1821 and then into a fuel injector 1818. 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 operatively injects fuel 67 to generate a fuel flow 1860 within the combustion zone 203 of the combustion chamber 202.

[0121] The burner steam system 1820 operably directs steam 69 through one or more steam injectors 1822 and into a steam path 1824 to cool the liner 1804 and heat shield 1852 at the rear section 1832. The steam path 1824 operably directs the steam 69 axially forward, such that the steam 69 flows within the steam path 1824 in the opposite direction to the combustion gases 66 within the combustion chamber 202. The steam path 1824 operably directs the steam 69 from the rear section 1832 to the front section 1830. As the steam 69 flows from the rear section 1832 to the front section 1830, the steam 69 absorbs heat from the liner 1804 to cool the liner 1804. Simultaneously, fuel 67 in the fuel path 1821 absorbs heat from the steam 69 in the steam path 1824, causing the temperature of the fuel 67 to increase as it flows through the fuel path 1821. Compared to burners that do not offer the benefits of this disclosure, increasing the temperature of fuel 67 allows for more efficient combustion within combustion zone 203.

[0122] One or more steam injection orifices 1826 operatively guide steam 69 through them to generate steam injection streams 1870 at the front 1830 and rear 1832 of steam path 1824 within combustion chamber 202. The steam injection stream 1870 from the rear 1832 comprises a larger amount of steam 69 than the steam injection stream 1870 from the front 1830. For example, the steam 69 injected from the rear 1832 comprises 50% to 80% of the steam 69 from steam path 1824, and the steam 69 injected from the front 1830 comprises 20% to 50% of the steam 69 from steam path 1824. Combustion gases 66 from the combustion zone are mixed with the steam injection stream 1870 to generate a steam-combustion gas mixture 1890 that is directed downstream and exits combustion chamber 202.

[0123] Figure 19 This is a schematic cross-sectional view of a portion of the annular dome 1910 of the burner 1900, taken along the longitudinal centerline axis of the burner 1900 according to another embodiment. Figure 20 Based on this disclosure Figure 19 A schematic rear cross-sectional view of a portion of the annular dome of the 1910. The burner of the 1900 was essentially similar. Figure 2The burner 200 includes a number of components that are the same as or similar to those of the burner 200. The same reference numerals will be used for components of the burner 1900 that are the same as or similar to those of the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted here. The annular dome 1910 includes one or more mixing assembly holes 1980 for receiving respective mixing assemblies (e.g., a plurality of mixing assemblies 212). The burner 1900 includes a burner steam system 1920. The burner steam system 1920 includes a steam path 1982 defined by (e.g., disposed within) the annular dome 1910. For example, the steam path 1982 extends substantially radially within the annular dome 1910.

[0124] The burner steam system 1920 includes one or more steam injection holes 1984 and one or more flame-forming holes 1986 disposed through an annular dome 1910. The one or more steam injection holes 1984 and the one or more flame-forming holes 1986 provide fluid communication from a steam path 1982 to a combustion chamber 202. The one or more steam injection holes 1984 are substantially located on the radially outer or 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 an axial direction A to provide film cooling on the annular dome 1910. In this way, the one or more steam injection holes 1984 may be steam cooling holes. The one or more flame-forming holes 1986 are radially positioned between one or more mixing assembly holes 1980 and the one or more steam injection holes 1984. The one or more flame-forming holes 1986 are angled toward the one or more mixing assembly holes 1980.

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

[0126] Figure 21 This is a schematic cross-sectional rear view of a portion of the annular dome 2110 of the burner 2100 according to this disclosure. The burner 2100 is substantially similar to... Figure 2 and Figure 19 The burners 200 and 1900 include a number of components identical or similar to those in the burners 200 and 1900. Burner 2100 includes a burner steam system 2120, which includes a steam path 2182 defined by an annular dome 2110 (e.g., within the annular dome 2110) and one or more steam injection holes 2184. The steam path 2182 has discrete flow paths within the annular dome 2110. Specifically, the steam path 2182 defines a generally swirling shape around the annular dome 2110 for cooling specific areas of the annular dome 2110. 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... Figure 2 and Figure 19 The burner steam system 220, 1920. Specifically, steam path 2182 operably guides steam 69 around steam path 2180 to cool the annular dome 2110. One or more steam injection holes 2184 operably guide steam 69 through them and into the combustion chamber.

[0127] Figure 22 This is a schematic cross-sectional view of the burner 2200 taken along the longitudinal centerline axis of the burner 2200 according to another embodiment. The burner 2200 is substantially similar to... Figure 2 The burner 200 includes a number of components that are the same as or similar to those of the burner 200. The same reference numerals will be used for components of the burner 2200 that are the same as or similar to those of the burner 200 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are 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 component holes 2280 for receiving corresponding mixing components (e.g., ...). Figure 2 The corresponding mixing component 212). The outer liner 2204, the inner liner 2206, and the annular dome 2210 form a single component. The burner 2200 includes one or more air dilution holes 2205 defined for passage through at least one of the outer liner 2204 or the inner liner 2206.

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

[0129] The operation of burner 2200 and burner steam system 2220 is basically similar to that of burner 2200 and burner steam system 2220, respectively. Figure 2The combustor 2200 and combustor steam system 220. Specifically, the combustor 2200 is operable to direct compressed air 65 through one or more air dilution orifices 2205 to generate a second compressed air flow 2264 within the combustion chamber 2202. A bushing steam path 2224 is operable to direct steam 69 around an outer liner 2204 and an inner liner 2206 to cool the outer liner 2204 and the inner liner 2206. The bushing steam path 2224 is operable to direct steam 69 to a dome steam path 2282, and the dome steam path 2282 is operable to direct steam 69 within an annular dome 2210 to cool the annular dome 2210. A bushing steam injection orifice 2226 is operable to direct steam 69 into the combustion chamber 2202 to generate a bushing steam injection flow 2270 downstream of one or more air dilution orifices 2205. One or more dome steam injection orifices 2284 operably direct steam 69 from dome steam path 2282 into combustion chamber 2202 to generate a dome steam injection stream 2285 within the region of annular dome 2210 in combustion chamber 2202. A bushing steam injection stream 2270 comprises a larger amount of steam 69 than the dome steam injection stream 2285. For example, the bushing steam injection stream 2270 comprises 70% to 90% of the steam 69 from steam paths 2224, 2282, while the dome steam injection stream 2285 comprises 10% to 30% of the steam 69 from steam paths 2224, 2282. One or more flame forming orifices 2286 operably direct steam 69 into combustion chamber 2202 to generate a steam flame forming stream 2287, thereby forming a flame within combustion zone 203. Combustion gas 66 from combustion zone 203 is mixed with dome steam injection stream 2285, steam flame forming stream 2287 and bushing steam injection stream 2270 to generate a steam-combustion gas mixture 2290 within combustion chamber 2202 that is directed downstream and exits combustion chamber 2202.

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

[0131] Burner 2300 includes burner steam system 2320. Burner steam system 2320 includes steam paths 2324 and 2282 defined (e.g., within at least one of outer liner 2304, inner liner 2306, or annular dome 2210). Steam paths 2324 and 2282 include a bushing steam path 2324 defined (e.g., within outer liner 2304 and inner liner 2306) and a dome steam path 2282 defined (e.g., within annular dome 2210). Bushing steam path 2324 includes a front portion 2330 and a rear portion 2332. The burner steam system 2320 includes one or more steam injection ports 2326, 2284 defined through at least one of an outer liner 2304, an inner liner 2306, or an annular dome 2210. The one or more steam injection ports 2326, 2284 include one or more bushing steam injection ports 2326 and one or more dome steam injection ports 2284. The burner steam system 2320 also includes one or more steam dilution ports 2328 defined in the outer liner 2304 or the inner liner 2306. The one or more bushing steam injection ports 2326 are located axially rearward of the one or more steam dilution ports 2328. For example, the one or more bushing steam injection ports 2326 are located at the rear portion 2332 of the bushing 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 with a dilution hole length L dilution Positioned on outer liner 2304 or inner liner 2306, the dilution hole length L dilutionThe length L is measured from the downstream surface of the annular dome 2110 to the axial center of one or more vapor dilution orifices 2328. dilution In the total combustion chamber length L combustor The range is from 10% to 90%. In this way, steam 69 is within the total combustion chamber length L. combustor Between 10% and 90% of the material is injected through the outer liner 2304 or the inner liner 2306.

[0133] The operation of burner 2300 and burner steam system 2320 is basically similar to that of burner 2300 and burner steam system 2320, respectively. Figure 2 and Figure 22 The combustors 200 and 2200 and the combustor steam systems 220 and 2220. Specifically, one or more bushing steam injection holes 2326 operatively direct steam 69 from steam path 2324 to generate a first steam injection flow 2370 through outer liner 2304 and inner liner 2306 downstream of one or more steam dilution holes 2328 within combustion chamber 2302. One or more steam dilution holes 2328 operatively direct steam 69 from steam path 2324 to generate a second steam injection flow 2372 from outer liner 2304 and inner liner 2306 within combustion chamber 2302. Combustion gases 66 from combustion zone 203 are mixed with dome steam injection flow 2285, steam flame shaping flow 2287, first bushing steam injection flow 2370, and second bushing steam injection flow 2372 to generate a steam-combustion gas mixture 2390 within combustion chamber 2302 that is directed downstream and exits combustion chamber 2302.

[0134] Therefore, the embodiments of this disclosure, detailed herein, provide a flame in the combustion zone within the combustion chamber and inject steam into the combustion chamber remotely from the combustion zone. Compared to burners without the benefits of this disclosure, the steam system detailed herein is able to inject a greater volume of steam into the burner without sacrificing burner operability. For example, a large volume of steam injected into a burner typically causes flameout, but this disclosure provides steam injected into the combustion chamber remotely from the combustion zone (e.g., downstream of the combustion zone) to avoid flameout in the combustion zone. This configuration of injecting steam remotely from the flame allows for the injection of a greater volume of steam into the burner compared to burners without the benefits of this disclosure. For example, injecting steam downstream of the combustion zone prevents steam from flowing near the flame within the combustion zone. In this way, this disclosure allows for the injection of a greater volume of steam into the burner compared to burners without the benefits of this disclosure, while preventing steam from blocking the flame, thereby reducing emissions (e.g., NO). xIt reduces emissions (nvPM emissions, CO and noise) and SFCs while providing flame stability (e.g., preventing flameout). This configuration, which allows steam to flow 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 outer liners, inner liners and annular domes that do not have the benefits of this disclosure.

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

[0136] A burner includes: a combustion chamber including an outer liner and an inner liner and having a combustion zone; an annular dome connected at a front end of the combustion chamber to the outer liner and the inner liner; a plurality of mixing components operable to inject a fuel-air mixture into the combustion zone of the combustion chamber to generate combustion gases; and a burner steam system in fluid communication with the combustion chamber, the burner steam system including a steam path defined by at least one of the outer liner, the inner liner, or the annular dome, the burner steam system operable to guide 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.

[0137] According to the burner described in the foregoing clause, the burner steam system is operatively directed away from the combustion zone to guide the steam.

[0138] According to any of the preceding clauses, the water-to-air ratio of the steam to compressed air in the combustion chamber is 0.0% to 60%.

[0139] The burner according to any of the foregoing clauses further 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, wherein the burner steam system is operable to inject at least a portion of the steam into the combustion chamber axially rearward of at least one of the one or more air dilution holes or the one or more steam injection holes.

[0140] According to any of the preceding clauses, the burner steam system includes one or more steam cooling holes of at least one of the outer liner, the inner liner, or the annular dome, the one or more steam cooling holes being operable to guide steam through them to cool at least one of the outer liner, the inner liner, or the annular dome.

[0141] According to any of the preceding clauses, 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 operatively capable of injecting steam into the steam path.

[0142] According to any of the preceding clauses, the one or more steam injectors are arranged in annular shape around the combustion chamber.

[0143] According to any of the preceding clauses, the burner steam system includes one or more steam injection holes of 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 guide the steam from the steam path into the combustion chamber.

[0144] According to any of the preceding clauses, the one or more steam injection holes are located on the outer liner or the inner liner, at least 25% of the total combustion chamber length of the combustion chamber.

[0145] According to any of the preceding clauses, the one or more steam injection holes are located on the outer liner or the inner liner, within 10% to 90% of the total combustion chamber length of the combustion chamber.

[0146] The burner according to any of the foregoing clauses further includes a steam system operable to supply the steam to the burner steam system.

[0147] According to any of the preceding clauses, the steam system includes one or more steam lines that supply the steam to the burner steam system.

[0148] According to the burner described in the foregoing clause, the one or more steam lines supply the steam to the one or more steam injectors.

[0149] According to any of the preceding clauses, the steam system generates steam from the exhaust gas of the turbine engine.

[0150] According to any of the preceding clauses, the plurality of mixing components include a plurality of fuel injectors for supplying fuel to the plurality of mixing components.

[0151] According to the burner described in the foregoing clause, the plurality of mixing components include a mixer that mixes compressed air with the fuel from the plurality of fuel injectors.

[0152] According to any of the preceding clauses of the burner, the one or more dilution orifices are one or more air dilution orifices operably directing the compressed air into the combustion chamber.

[0153] According to any of the preceding clauses, the steam path includes a front portion and a rear portion behind the front portion, wherein the one or more steam injection holes are located at the front portion.

[0154] According to any of the preceding clauses, the steam path is annular around at least one of the outer liner, the inner liner, or the annular dome.

[0155] According to any of the preceding clauses, the steam path includes one or more discrete steam paths within at least one of the outer liner, the inner liner, or the annular dome.

[0156] According to any of the preceding clauses, the steam path includes one or more circumferential extensions and one or more axial extensions, the one or more axial extensions being fluidly connected to the one or more circumferential extensions.

[0157] According to any of the preceding clauses, the steam path has a generally zigzag shape.

[0158] According to the burner described in the foregoing clause, the one or more circumferential extensions and the one or more axial extensions are fluidly connected to form the generally zigzag shape.

[0159] According to any of the preceding clauses, the steam path extends axially rearward behind the one or more dilution orifices of the burner.

[0160] According to any of the preceding clauses, the one or more steam injectors are positioned axially in front of the one or more dilution orifices.

[0161] According to any of the preceding clauses, the one or more steam injectors are positioned axially rearward of the one or more dilution orifices.

[0162] According to any of the preceding clauses of the burner, the one or more steam injection holes are located on the one or more circumferential extensions of the steam path.

[0163] According to any of the preceding clauses, the one or more circumferential extensions extend circumferentially from the one or more steam injectors, and the one or more axial extensions extend axially rearward from the one or more circumferential extensions.

[0164] According to any of the preceding clauses, the one or more axially extending portions include one or more discrete axially extending portions that are circumferentially spaced around at least one of the outer liner, the inner liner, or the annular dome.

[0165] According to any of the preceding clauses, the one or more axially extending portions extend axially rearward of the one or more dilution orifices.

[0166] According to any of the preceding clauses, the steam path is in the outer liner or the inner liner of the burner.

[0167] According to any of the preceding clauses of the burner, the one or more dilution orifices include one or more steam dilution orifices in fluid communication with the steam path, the one or more steam dilution orifices being operable to guide the steam from the steam path into the combustion chamber.

[0168] According to any of the preceding clauses, the one or more dilution orifices include one or more air dilution orifices and one or more steam dilution orifices that alternate circumferentially around the outer liner or the inner liner.

[0169] According to any of the preceding clauses, the burner steam system further includes one or more steam channels configured to operatively direct the steam into the combustion chamber via the outer liner or the inner liner.

[0170] According to the burner described in the foregoing clause, the one or more steam troughs are positioned axially rearward of the one or more dilution orifices.

[0171] According to any of the preceding clauses, the one or more steam troughs are positioned axially in front of the one or more steam injection holes.

[0172] According to any of the preceding clauses, the one or more steam channels are generally arc-shaped channels.

[0173] According to any of the preceding clauses, the burner steam system further includes a steam manifold fluidly connected between the one or more steam injectors and the steam path.

[0174] According to any of the preceding clauses, the steam manifold includes one or more discrete steam manifolds.

[0175] According to any of the preceding clauses, the steam manifold is annular around the combustion chamber.

[0176] The burner according to any of the foregoing clauses further includes a heat shield connected to at least one of the outer liner, the inner liner, or the annular dome.

[0177] According to any of the preceding clauses, the steam path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0178] The burner according to any of the foregoing clauses further includes one or more air impingement holes configured to operatively direct the compressed air into the steam path to impinge on the heat shield through at least one of the outer liner, the inner liner, or the annular dome.

[0179] According to any of the preceding clauses, the burner steam system further includes one or more steam cooling holes configured to guide steam from the steam path into the combustion chamber to cool the heat shield.

[0180] According to any of the preceding clauses, the one or more steam cooling holes are angled rearward relative to the longitudinal centerline axis of the burner.

[0181] According to any of the preceding clauses, the burner steam system further includes one or more steam injector lines fluidly connected between the steam manifold and the steam path for operatively directing the steam from the steam manifold to the steam path.

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

[0183] According to any of the foregoing clauses, the front portion is fluidly connected to the rear portion of the burner.

[0184] According to any of the preceding clauses, the burner steam system further includes one or more front steam inlet ports located in front of the one or more steam dilution ports and providing fluid communication from the steam manifold to the front of the steam path.

[0185] According to any of the preceding clauses, the burner steam system further includes one or more rear steam inlet ports located downstream of the one or more steam dilution ports and providing fluid communication from the steam manifold to the rear portion of the steam path.

[0186] According to any of the preceding clauses, the one or more front steam inlet ports and the one or more rear steam inlet ports comprise substantially equal dimensions, such that the pressure drop through the one or more front steam inlet ports is substantially equal to the pressure drop through the one or more rear steam inlet ports.

[0187] According to any of the preceding clauses of the burner, the size of the one or more front steam inlet holes is set differently from the one or more rear steam inlet holes, such 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.

[0188] According to any of the preceding clauses of the burner, the dimensions of the one or more steam dilution orifices and the one or more steam injection orifices are set such that the one or more steam dilution orifices are operable to direct more than 50% of the steam into the combustion chamber, and the one or more steam injection orifices are operable to direct less than 50% of the steam into the combustion chamber.

[0189] According to any of the preceding clauses of the burner, the dimensions of the one or more steam dilution orifices and the one or more steam injection orifices are set such that the one or more steam dilution orifices are operable to direct 40% to 100% of the steam into the combustion chamber, and the one or more steam injection orifices are operable to direct 0.0% to 60% of the steam into the combustion chamber.

[0190] According to any of the preceding clauses, the one or more steam injectors are positioned to direct the steam to the rear of the steam path.

[0191] According to any of the preceding clauses of the burner, the steam path operatively directs the steam from the rear to the front.

[0192] According to any of the foregoing clauses, the front section and the rear section are fluid-separated.

[0193] According to any of the preceding clauses, the burner steam system includes one or more first steam injector lines in fluid communication with the rear section and one or more second steam injector lines in fluid communication with the front section.

[0194] According to any of the preceding clauses of the burner, the one or more steam injection ports are located at the front portion such that steam is injected from the front portion, and the one or more steam injection ports are located at the rear portion such that steam is injected from the rear portion.

[0195] According to any of the preceding clauses, the steam injected from the rear portion comprises a larger amount of steam than the steam injected from the front portion.

[0196] According to any of the preceding clauses, 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] According to any of the preceding clauses, the burner 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 operatively direct the steam to the one or more second steam injector lines.

[0198] According to any of the preceding clauses, the one or more air dilution orifices include a dilution orifice insert disposed within the one or more air dilution orifices.

[0199] According to any of the preceding clauses of the burner, the one or more air dilution orifices include a dilution orifice support disposed within the one or more air dilution orifices for preventing the one or more air dilution orifices from closing during thermal expansion of at least one of the heat shield and the outer liner, the inner liner or the annular dome.

[0200] According to any of the preceding clauses, the burner further includes an air path positioned axially forward of the one or more dilution orifices.

[0201] According to any of the preceding clauses of the burner, the air path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0202] According to any of the preceding clauses of the burner, the one or more air impingement holes are operable to direct the compressed air into the air path to impinge on the heat shield.

[0203] According to any of the preceding clauses, the burner further includes one or more air injection ports configured to guide compressed air from the air path to the combustion chamber through the heat shield to cool the heat shield.

[0204] According to any of the preceding clauses of the burner, the steam path is located axially rearward of the one or more dilution orifices.

[0205] According to any of the preceding clauses, the steam manifold includes one or more steam impingement holes disposed in the steam manifold, the one or more steam impingement holes being operable to guide the steam from the steam manifold into the steam path to impinge on the heat shield.

[0206] According to any of the preceding clauses, the steam manifold includes a front portion located axially forward of the one or more dilution orifices and a rear portion located axially backward of the one or more dilution orifices.

[0207] According to any of the preceding clauses of the burner, the steam manifold is operable to direct the steam from the rear to the front.

[0208] According to any of the preceding clauses, the one or more steam injectors include one or more first steam injectors operably directing the steam to the rear portion, and one or more second steam injectors operably directing the steam to the front portion.

[0209] According to any of the preceding clauses, the plurality of fuel injectors includes a fuel supply line positioned axially rearward of the one or more dilution orifices, the fuel supply line being operable to direct the fuel to the plurality of fuel injectors.

[0210] The burner according to any of the foregoing clauses further includes 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] According to any of the preceding clauses, the fuel path extends substantially axially from the fuel supply line to the plurality of fuel injectors.

[0212] According to any of the preceding clauses of the burner, the fuel path operatively directs the fuel from the fuel supply line to the fuel injector.

[0213] According to any of the preceding clauses of the burner, when the fuel flows through the fuel path, the fuel in the fuel path absorbs heat from the steam in the steam path.

[0214] According to any of the preceding clauses of the burner, the steam flows through the steam path in a direction opposite to the flow direction of the combustion gas.

[0215] According to any of the preceding clauses of the burner, the fuel flows through the fuel path in a direction opposite to the flow direction of the combustion gases.

[0216] According to any of the preceding clauses, the steam path is provided in the outer liner or the inner liner.

[0217] According to any of the preceding clauses, the one or more steam injection holes are provided in the outer liner or the inner liner.

[0218] According to any of the preceding clauses, the steam path is arranged in the annular dome.

[0219] According to any of the preceding clauses, the one or more steam injection holes are disposed in the annular dome.

[0220] According to any of the preceding clauses, the burner steam system further includes one or more flame-forming orifices configured to pass through the annular dome, the one or more flame-forming orifices operatively guiding 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 orifices.

[0221] According to any of the preceding clauses, the one or more flame-forming holes are angled toward the flame.

[0222] According to any of the preceding clauses, the annular dome includes one or more mixing component holes for receiving the plurality of mixing components, the one or more flame-forming holes being radially positioned between the one or more mixing component holes and the one or more steam injection holes.

[0223] According to any of the preceding clauses, the one or more flame forming orifices are larger than the one or more steam injection orifices.

[0224] According to any of the preceding clauses, the steam path has a generally swirling shape.

[0225] According to any of the preceding clauses, the outer liner, the inner liner, and the annular dome form a single, single component in the burner.

[0226] According to any of the preceding clauses, the steam path includes a bushing steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0227] According to any of the preceding clauses, the bushing steam path is fluidly connected to the dome steam path of the burner.

[0228] According to any of the foregoing clauses, 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] According to any of the preceding clauses, 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 the combustion chamber outlet of the combustion chamber.

[0230] According to any of the preceding clauses, the combustion chamber includes a total combustion chamber length axially defined from the downstream surface of the annular dome to the combustion chamber outlet.

[0231] According to any of the preceding clauses of the burner, the one or more dilution holes are positioned on the outer or inner liner by a dilution hole length measured from the downstream surface of the annular dome to the axial center of the one or more dilution holes.

[0232] According to any of the preceding clauses, the length of the dilution orifice 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 comprising: a combustion chamber including an outer liner and an inner liner and having a combustion zone; an annular dome connected at a front end of the combustion chamber to the outer liner and the inner liner; a plurality of mixing components operable to inject a fuel-air mixture into the combustion zone of the combustion chamber to produce combustion gases; and a combustor steam system 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 guide 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.

[0234] According to the turbine engine described in the foregoing clause, the combustor steam system is operatively directed away from the combustion zone to guide the steam.

[0235] According to any of the foregoing clauses of the turbine engine, the water-to-air ratio of the steam to compressed air in the combustion chamber is 0.0% to 60%.

[0236] The turbine engine according to any of the foregoing clauses further 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, wherein the burner steam system is operable to inject at least a portion of the steam into the combustion chamber axially rearward of at least one of the one or more air dilution holes or the one or more steam injection holes.

[0237] According to any of the preceding clauses, the turbine engine's combustor steam system includes one or more steam cooling holes of at least one of the outer liner, the inner liner, or the annular dome, the one or more steam cooling holes being operable to guide steam through them to cool at least one of the outer liner, the inner liner, or the annular dome.

[0238] According to any of the preceding clauses, the combustor steam system of the turbine engine 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.

[0239] According to any of the preceding clauses, the one or more steam injectors are annular around the combustion chamber.

[0240] According to any of the preceding clauses, the turbine engine's combustor steam system includes one or more steam injection ports of at least one of the outer liner, the inner liner, or the annular dome, and the one or more steam injection ports are operable to guide steam from the steam path into the combustion chamber.

[0241] According to any of the preceding clauses of the turbine engine, the one or more steam injection holes are located on the outer liner or the inner liner, at least 25% of the total combustion chamber length of the combustion chamber.

[0242] According to any of the preceding clauses of the turbine engine, the one or more steam injection holes are located on the outer liner or the inner liner, within 10% to 90% of the total combustion chamber length of the combustion chamber.

[0243] The turbine engine according to any of the foregoing clauses further includes a steam system operable to supply the steam to the burner steam system.

[0244] According to any of the preceding clauses, the steam system of the turbine engine includes one or more steam lines that supply steam to the burner steam system.

[0245] According to the turbine engine described in the foregoing clause, the one or more steam lines supply the steam to the one or more steam injectors.

[0246] According to any of the foregoing clauses, the steam system generates steam from the exhaust gas of the turbine engine.

[0247] According to any of the preceding clauses, the plurality of mixing components include a plurality of fuel injectors for supplying fuel to the plurality of mixing components.

[0248] According to the turbine engine described in the foregoing clause, the plurality of mixing components include a mixer that mixes compressed air with the fuel from the plurality of fuel injectors.

[0249] According to any of the preceding clauses of the turbine engine, the one or more dilution orifices are one or more air dilution orifices that operatively direct the compressed air into the combustion chamber.

[0250] According to any of the preceding clauses of the turbine engine, the steam path includes a front portion and a rear portion behind the front portion, wherein the one or more steam injection holes are located at the front portion.

[0251] According to any of the preceding clauses of the turbine engine, the steam path is annular around at least one of the outer liner, the inner liner, or the annular dome.

[0252] According to any of the preceding clauses, the steam path of the turbine engine includes one or more discrete steam paths within at least one of the outer liner, the inner liner, or the annular dome.

[0253] According to any of the preceding clauses, the steam path includes one or more circumferential extensions and one or more axial extensions, the one or more axial extensions being fluidly connected to the one or more circumferential extensions.

[0254] According to any of the preceding clauses, the steam path of the turbine engine has a generally zigzag shape.

[0255] According to the turbine engine described in the foregoing clause, the one or more circumferential extensions and the one or more axial extensions are fluidly connected to form the generally zigzag shape.

[0256] According to any of the preceding clauses of the turbine engine, the steam path extends axially rearward behind the one or more dilution orifices.

[0257] According to any of the preceding clauses of the turbine engine, the one or more steam injectors are positioned axially forward of the one or more dilution orifices.

[0258] According to any of the preceding clauses of the turbine engine, the one or more steam injectors are positioned axially rearward of the one or more dilution orifices.

[0259] According to any of the preceding clauses of the turbine engine, the one or more steam injection holes are located on the one or more circumferential extensions of the steam path.

[0260] According to any of the foregoing clauses, the one or more circumferential extensions extend circumferentially from the one or more steam injectors, and the one or more axial extensions extend axially rearward from the one or more circumferential extensions.

[0261] According to any of the preceding clauses, the one or more axial extension portions include one or more discrete axial extension portions that are circumferentially spaced around at least one of the outer liner, the inner liner, or the annular dome.

[0262] According to any of the foregoing clauses, the one or more axially extending portions extend axially rearward of the one or more dilution orifices.

[0263] According to any of the preceding clauses, the steam path is in the outer liner or the inner liner of the turbine engine.

[0264] According to any of the preceding clauses of the turbine engine, the one or more dilution orifices include one or more steam dilution orifices in fluid communication with the steam path, the one or more steam dilution orifices being operable to guide the steam from the steam path into the combustion chamber.

[0265] According to any of the preceding clauses, the one or more dilution holes include one or more air dilution holes and one or more steam dilution holes that alternate circumferentially around the outer liner or the inner liner.

[0266] According to any of the preceding clauses of the turbine engine, the combustor steam system further includes one or more steam channels configured to operatively direct the steam into the combustion chamber via the outer liner or the inner liner.

[0267] According to the turbine engine described in the foregoing clause, the one or more steam tanks are located axially rearward of the one or more dilution orifices.

[0268] According to any of the preceding clauses of the turbine engine, the one or more steam troughs are positioned axially forward of the one or more steam injection holes.

[0269] According to any of the preceding clauses, the one or more steam troughs are generally arc-shaped troughs.

[0270] According to any of the foregoing clauses, the combustor steam system of the turbine engine further includes a steam manifold fluidly connected between the one or more steam injectors and the steam path.

[0271] According to any of the preceding clauses, the steam manifold of the turbine engine comprises one or more discrete steam manifolds.

[0272] According to any of the foregoing clauses of the turbine engine, the steam manifold is annular around the combustion chamber.

[0273] The turbine engine according to any of the foregoing clauses further includes a heat shield connected to at least one of the outer liner, the inner liner, or the annular dome.

[0274] According to any of the preceding clauses of the turbine engine, the steam path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0275] The turbine engine according to any of the foregoing clauses further includes one or more air impingement holes configured to operatively direct the compressed air into the steam path to impinge on the heat shield through at least one of the outer liner, the inner liner, or the annular dome.

[0276] According to any of the preceding clauses of the turbine engine, the combustor steam system further includes one or more steam cooling holes configured to guide steam from the steam path into the combustion chamber to cool the heat shield.

[0277] According to any of the preceding clauses of the turbine engine, the one or more steam cooling holes are angled rearward relative to the longitudinal centerline axis of the burner.

[0278] According to any of the preceding clauses of the turbine engine, the combustor steam system further includes one or more steam injector lines fluidly connected between the steam manifold and the steam path for operatively directing the steam from the steam manifold to the steam path.

[0279] According to any of the preceding clauses of the turbine engine, the steam path includes a front portion located in front of the one or more air dilution holes or at least one of the one or more steam dilution holes, and a rear portion located behind the one or more air dilution holes or at least one of the one or more steam dilution holes.

[0280] In any of the foregoing clauses, the front portion of the turbine engine is fluidly connected to the rear portion.

[0281] According to any of the foregoing clauses of the turbine engine, the combustor steam system further includes one or more front steam inlet ports located in front of the one or more steam dilution ports and providing fluid communication from the steam manifold to the front of the steam path.

[0282] According to any of the preceding clauses of the turbine engine, the combustor steam system further includes one or more rear steam inlet ports located behind the one or more steam dilution ports and providing fluid communication from the steam manifold to the rear of the steam path.

[0283] According to any of the preceding clauses, the one or more front steam inlet ports and the one or more rear steam inlet ports comprise substantially equal dimensions, such that the pressure drop through the one or more front steam inlet ports is substantially equal to the pressure drop through the one or more rear steam inlet ports.

[0284] According to any of the preceding clauses of the turbine engine, the size of the one or more front steam inlet orifices is set to be different from that of the one or more rear steam inlet orifices, such that the pressure drop through the one or more front steam inlet orifices is different from the pressure drop through the one or more rear steam inlet orifices.

[0285] According to any of the preceding clauses of the turbine engine, the dimensions of the one or more steam dilution orifices and the one or more steam injection orifices are set such that the one or more steam dilution orifices are operable to direct more than 50% of the steam into the combustion chamber, and the one or more steam injection orifices are operable to direct less than 50% of the steam into the combustion chamber.

[0286] According to any of the preceding clauses of the turbine engine, the dimensions of the one or more steam dilution holes and the one or more steam injection holes are set such 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] According to any of the preceding clauses of the turbine engine, the one or more steam injectors are positioned to direct the steam to the rear of the steam path.

[0288] According to any of the foregoing clauses of the turbine engine, the steam path operatively directs the steam from the rear to the front.

[0289] In any of the foregoing clauses, the front section of the turbine engine is fluid-separated from the rear section.

[0290] According to any of the preceding clauses, the turbine engine's combustor steam system includes one or more first steam injector lines in fluid communication with the rear section and one or more second steam injector lines in fluid communication with the front section.

[0291] According to any of the preceding clauses of the turbine engine, the one or more steam injection ports are located at the front portion such that steam is injected from the front portion, and the one or more steam injection ports are located at the rear portion such that steam is injected from the rear portion.

[0292] According to any of the foregoing clauses, the steam injected from the rear comprises a larger amount of steam than the steam injected from the front.

[0293] According to any of the foregoing clauses, 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.

[0294] According to any of the foregoing clauses of the turbine engine, 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 operatively direct the steam to the one or more second steam injector lines.

[0295] According to any of the preceding clauses, the one or more air dilution orifices include a dilution orifice insert disposed within the one or more air dilution orifices.

[0296] According to any of the preceding clauses of the turbine engine, the one or more air dilution orifices include dilution orifice supports disposed within the one or more air dilution orifices for preventing the one or more air dilution orifices from closing during thermal expansion of at least one of the heat shield and the outer liner, the inner liner or the annular dome.

[0297] According to any of the foregoing clauses of the turbine engine, the combustor further includes an air path positioned axially forward of the one or more dilution orifices.

[0298] According to any of the preceding clauses of the turbine engine, the air path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0299] According to any of the preceding clauses of the turbine engine, the one or more air impingement holes are operable to direct the compressed air into the air path to impinge on the heat shield.

[0300] According to any of the preceding clauses of the turbine engine, the combustor further includes one or more air injection ports configured to pass through the heat shield, the one or more air injection ports being operable to direct the compressed air from the air path to the combustion chamber to cool the heat shield.

[0301] According to any of the preceding clauses of the turbine engine, the steam path is located axially rearward of the one or more dilution orifices.

[0302] According to any of the preceding clauses of the turbine engine, the steam manifold includes one or more steam impingement holes disposed in the steam manifold, the one or more steam impingement holes being operable to guide the steam from the steam manifold into the steam path to impinge on the heat shield.

[0303] According to any of the preceding clauses, the steam manifold includes a front portion located axially forward of the one or more dilution orifices and a rear portion located axially rearward of the one or more dilution orifices.

[0304] According to any of the foregoing clauses of the turbine engine, the steam manifold is operable to direct the steam from the rear to the front.

[0305] According to any of the preceding clauses, the one or more steam injectors include one or more first steam injectors operably directing the steam to the rear portion, and one or more second steam injectors operably directing the steam to the front portion.

[0306] According to any of the preceding clauses, the plurality of fuel injectors includes a fuel supply line located axially rearward of the one or more dilution orifices, the fuel supply line being operable to direct the fuel to the plurality of fuel injectors.

[0307] The turbine engine according to any of the foregoing clauses further includes 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.

[0308] According to any of the preceding clauses, the fuel path extends substantially axially from the fuel supply line to the plurality of fuel injectors.

[0309] According to any of the foregoing clauses of the turbine engine, the fuel path operatively directs the fuel from the fuel supply line to the fuel injector.

[0310] According to any of the preceding clauses, in a turbine engine, when the fuel flows through the fuel path, the fuel in the fuel path absorbs heat from the steam in the steam path.

[0311] According to any of the preceding clauses of the turbine engine, the steam flows through the steam path in a direction opposite to the flow direction of the combustion gases.

[0312] According to any of the preceding clauses of the turbine engine, the fuel flows through the fuel path in a direction opposite to the flow direction of the combustion gases.

[0313] According to any of the preceding clauses, the steam path is provided in the outer liner or the inner liner of the turbine engine.

[0314] According to any of the preceding clauses, the one or more steam injection holes are provided in the outer liner or the inner liner of the turbine engine.

[0315] In any of the preceding clauses of the turbine engine, the steam path is disposed in the annular dome.

[0316] According to any of the preceding clauses, the turbine engine has one or more steam injection holes disposed in the annular dome.

[0317] According to any of the preceding clauses of the turbine engine, the combustor steam system further includes one or more flame-forming orifices configured to pass through the annular dome, the one or more flame-forming orifices being operatively directed 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 orifices.

[0318] According to any of the preceding clauses, the one or more flame-forming holes are angled toward the flame.

[0319] According to any of the preceding clauses, the annular dome includes one or more mixing component holes for receiving the plurality of mixing components, the one or more flame-forming holes being radially positioned between the one or more mixing component holes and the one or more steam injection holes.

[0320] According to any of the preceding clauses, the one or more flame-forming holes are larger than the one or more steam injection holes.

[0321] According to any of the preceding clauses, the steam path of the turbine engine has a generally swirling shape.

[0322] According to any of the foregoing clauses, the outer liner, the inner liner, and the annular dome form a single, single component in the turbine engine.

[0323] According to any of the preceding clauses, the steam path of the turbine engine includes a bushing steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0324] According to any of the foregoing clauses of the turbine engine, the bushing steam path is fluidly connected to the dome steam path.

[0325] According to any of the foregoing clauses, the steam injected from the outer liner or the inner liner constitutes 70% to 90% of the steam injected into the combustion chamber, and the steam injected from the annular dome constitutes 10% to 30% of the steam injected into the combustion chamber.

[0326] According to any of the preceding clauses, in a turbine engine, 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 the combustion chamber outlet of the combustion chamber.

[0327] According to any of the preceding clauses, the combustion chamber includes a total combustion chamber length axially defined from the downstream surface of the annular dome to the combustion chamber outlet.

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

[0329] According to any of the preceding clauses of the turbine engine, the length of the dilution hole 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 components; 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 using the combustor steam system into a steam path defined by at least one of the outer liner, the inner liner, or the annular dome; and directing the steam from the steam path into the combustion chamber.

[0331] The method according to any of the foregoing clauses further includes guiding the steam away from the combustion zone.

[0332] The method according to any of the foregoing clauses further includes injecting the steam using the burner steam system during medium-power operation of the turbine engine and during high-power operation of the turbine engine.

[0333] The method according to any of the foregoing clauses further includes directing the steam into the combustion chamber such that the water-to-air ratio of the steam in the combustion chamber to the compressed air is 0.0% to 60%.

[0334] According to any of the foregoing clauses, the burner 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 guiding at least a portion of the steam axially rearward through the one or more air dilution holes or the at least one of the one or more steam dilution holes into the combustion chamber.

[0335] The method according to any of the foregoing clauses, wherein the burner steam system includes one or more steam cooling holes of 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 at least one of the outer liner, the inner liner, or the annular dome.

[0336] According to any of the foregoing clauses, the burner steam system includes one or more steam injectors in fluid communication with the steam path, and the method further includes directing the steam through the one or more steam injectors and into the steam path.

[0337] According to any of the foregoing clauses, the burner steam system includes one or more steam injection holes of at least one of the outer liner, the inner liner, or the annular dome, and the method further includes guiding the steam from the steam path through the one or more steam injection holes and into the combustion chamber.

[0338] The method according to any of the foregoing clauses further includes guiding the steam from the steam path through the one or more steam injection holes and entering the combustion chamber at a position of at least 25% of the total combustion chamber length of the combustion chamber.

[0339] The method according to any of the foregoing clauses further includes guiding the steam from the steam path through the one or more steam injection holes and entering the combustion chamber at a location ranging from 10% to 90% of the total combustion chamber length.

[0340] The method according to any of the foregoing clauses further includes supplying the steam to the burner steam system using a steam system.

[0341] The method according to any of the foregoing clauses further includes supplying the steam to the burner steam system via one or more steam lines.

[0342] The method described according to the foregoing clauses further includes supplying the steam to the one or more steam injectors.

[0343] The method according to any of the foregoing clauses further includes using the steam system to generate steam from the exhaust gas of the turbine engine.

[0344] According to any of the foregoing clauses, the plurality of mixing components includes a plurality of fuel injectors, and the method includes supplying fuel to the plurality of mixing components through the plurality of fuel injectors.

[0345] According to the method described in the foregoing clause, the plurality of mixing components include a mixer, and the method includes mixing the compressed air with the fuel from the plurality of fuel injectors.

[0346] The method according to any of the foregoing clauses further includes directing the compressed air into the combustion chamber through the one or more air dilution orifices.

[0347] According to any of the preceding clauses, the steam path includes a front portion and a rear portion behind the front portion, wherein the one or more steam injection holes are located at the front portion.

[0348] According to any of the preceding clauses of the method, the steam path is annular around at least one of the outer liner, the inner liner, or the annular dome.

[0349] According to any of the preceding clauses, the steam path includes one or more discrete steam paths within at least one of the outer liner, the inner liner, or the annular dome.

[0350] According to any of the foregoing provisions, the steam path includes one or more circumferential extensions and one or more axial extensions, the one or more axial extensions being fluidly connected to the one or more circumferential extensions.

[0351] According to any of the methods described in the foregoing clauses, the steam path has a generally zigzag shape.

[0352] According to the method described in the foregoing clauses, the one or more circumferential extensions and the one or more axial extensions are fluidly connected to form the generally zigzag shape.

[0353] According to any of the preceding clauses, the vapor path extends axially rearward behind the one or more dilution orifices.

[0354] According to any of the preceding clauses, the one or more steam injectors are positioned axially in front of the one or more dilution orifices.

[0355] According to any of the preceding clauses, the one or more steam injectors are positioned axially rearward of the one or more dilution orifices.

[0356] According to any of the preceding clauses, the one or more steam injection holes are located on the one or more circumferential extensions of the steam path.

[0357] According to any of the foregoing provisions of the method, the one or more circumferential extensions extend circumferentially from the one or more steam injectors, and the one or more axial extensions extend axially rearward from the one or more circumferential extensions.

[0358] According to any of the preceding clauses, the one or more axially extending portions include one or more discrete axially extending portions that are circumferentially spaced around at least one of the outer liner, the inner liner, or the annular dome.

[0359] According to any of the preceding clauses, the one or more axially extending portions extend axially rearward of the one or more dilution holes.

[0360] According to any of the preceding clauses, the steam path is in the outer liner or the inner liner.

[0361] According to any of the foregoing clauses, the one or more dilution orifices include one or more steam dilution orifices in fluid communication with the steam path, the method comprising guiding the steam from the steam path into the combustion chamber through the one or more steam dilution orifices.

[0362] According to any of the foregoing clauses, the one or more dilution orifices include one or more air dilution orifices 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 orifices.

[0363] According to any of the foregoing provisions of the method, the one or more air dilution holes and the one or more vapor dilution holes alternate circumferentially around the outer liner or the inner liner.

[0364] According to any of the foregoing clauses, the burner steam system further includes one or more steam channels configured to pass through the outer liner or the inner liner, and the method further includes directing the steam into the combustion chamber through the one or more steam channels.

[0365] According to the method described in the foregoing clause, the one or more steam tanks are positioned axially rearward of the one or more dilution holes.

[0366] According to any of the preceding clauses, the one or more steam tanks are positioned axially in front of the one or more steam injection holes.

[0367] According to any of the preceding clauses, the one or more steam tanks are generally arc-shaped tanks.

[0368] According to any of the foregoing descriptions, the burner steam system further includes a steam manifold fluidly connected between the one or more steam injectors and the steam path.

[0369] According to any of the preceding clauses, the steam manifold comprises one or more discrete steam manifolds.

[0370] According to any of the preceding descriptions, the steam manifold is annular around the combustion chamber.

[0371] The method according to any of the foregoing clauses further includes a heat shield connected to at least one of the outer liner, the inner liner, or the annular dome.

[0372] According to any of the preceding clauses of the method, the vapor path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0373] The method according to any of the foregoing clauses further includes one or more air impingement holes configured to impinge the heat shield through at least one of the outer liner, the inner liner, or the annular dome, the method further including directing the compressed air through the one or more air impingement holes into the steam path to impinge the heat shield.

[0374] According to any of the foregoing clauses, the burner steam system further includes one or more steam cooling holes configured to pass through the heat shield, and the method further includes guiding 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] According to any of the foregoing descriptions, the one or more steam cooling holes are angled relative to the longitudinal centerline axis of the burner.

[0376] According to any of the foregoing clauses, the burner steam system further includes one or more steam injector lines 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 lines.

[0377] According to any of the foregoing provisions of the method, the steam path includes a front portion located in front of the one or more air dilution holes or at least one of the one or more steam dilution holes, and a rear portion located behind the one or more air dilution holes or at least one of the one or more steam dilution holes.

[0378] According to any of the foregoing provisions, the front portion is fluidly connected to the rear portion.

[0379] According to any of the foregoing clauses, the burner steam system further includes one or more front steam inlet holes positioned in front of the one or more steam dilution holes, and the method further includes guiding the steam from the steam manifold to the front of the steam path through the one or more front steam inlet holes.

[0380] According to any of the foregoing clauses, the burner steam system further includes one or more rear steam inlet ports located downstream of the one or more steam dilution ports, and the method further includes guiding the steam from the steam manifold to the rear portion of the steam path through the one or more rear steam inlet ports.

[0381] According to any of the foregoing provisions, the one or more front steam inlet holes and the one or more rear steam inlet holes comprise substantially equal dimensions, such 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.

[0382] According to any of the preceding clauses, the size of the one or more front steam inlet orifices is set to be different from that of the one or more rear steam inlet orifices, such that the pressure drop through the one or more front steam inlet orifices is different from the pressure drop through the one or more rear steam inlet orifices.

[0383] The method according to any of the foregoing clauses further includes directing more than 50% of the steam into the combustion chamber through the one or more steam dilution orifices, and directing less than 50% of the steam into the combustion chamber through the one or more steam injection orifices.

[0384] The method according to any of the foregoing clauses further includes directing 40% to 100% of the steam into the combustion chamber through the one or more steam dilution orifices, and directing 0.0% to 60% of the steam into the combustion chamber through the one or more steam injection orifices.

[0385] The method according to any of the foregoing clauses further includes directing the steam to the rear of the steam path via the one or more steam injectors.

[0386] According to any of the foregoing provisions, the method further includes guiding the steam from the rear to the front.

[0387] According to any of the foregoing provisions of the method, the front portion is fluidly separated from the rear portion.

[0388] According to any of the foregoing provisions, the burner steam system includes one or more first steam injector lines in fluid communication with the rear section and one or more second steam injector lines in fluid communication with the front section.

[0389] According to any of the preceding clauses of the method, the one or more steam injection holes are located at the front portion such that steam is injected from the front portion, and the one or more steam injection holes are located at the rear portion such that steam is injected from the rear portion.

[0390] The method according to any of the foregoing clauses further includes injecting a larger amount of the steam from the rear than from the front.

[0391] According to the method described in any of the foregoing clauses, 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.

[0392] According to any of the foregoing clauses, the burner 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, and the method further includes directing the steam to the one or more second steam injector lines.

[0393] According to any of the foregoing descriptions, the one or more air dilution orifices include a dilution orifice insert disposed within the one or more air dilution orifices.

[0394] According to any of the foregoing descriptions, the one or more air dilution holes include a dilution hole support disposed within the one or more air dilution holes for preventing the one or more air dilution holes from closing during thermal expansion of the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0395] According to any of the foregoing descriptions, the burner further includes an air path positioned axially forward of the one or more dilution orifices.

[0396] According to any of the preceding clauses of the method, the air path is defined between the heat shield and at least one of the outer liner, the inner liner, or the annular dome.

[0397] The method according to any of the foregoing clauses further includes guiding the compressed air into the air path through the one or more air impingement holes to impinge on the heat shield.

[0398] According to any of the foregoing clauses, the burner further includes one or more air injection ports configured through the heat shield, and the method further includes directing the compressed air from the air path to the combustion chamber through the one or more air injection ports to cool the heat shield.

[0399] According to any of the methods described in the foregoing clauses, the steam path is located axially rearward of the one or more dilution orifices.

[0400] According to any of the foregoing clauses, the steam manifold includes one or more steam impingement holes disposed in the steam manifold, and the method further includes guiding steam from the steam manifold into the steam path through the one or more steam impingement holes to impinge the heat shield.

[0401] According to any of the foregoing descriptions, the steam manifold includes a front portion located axially forward of the one or more dilution orifices and a rear portion located axially rearward of the one or more dilution orifices.

[0402] The method according to any of the foregoing clauses further includes guiding the steam from the rear to the front.

[0403] According to any of the foregoing clauses, the one or more steam injectors include one or more first steam injectors, and the method further includes using the one or more first steam injectors to direct the steam into the rear portion.

[0404] According to any of the foregoing clauses, the one or more steam injectors include one or more second steam injectors, and the method further includes using the one or more second steam injectors to direct the steam into the front portion.

[0405] According to any of the foregoing clauses, the plurality of fuel injectors includes a fuel supply line positioned axially rearward of the one or more dilution orifices, the method further comprising directing the fuel to the plurality of fuel injectors through the fuel supply line.

[0406] The method according to any of the foregoing clauses further includes 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] According to any of the preceding clauses, the fuel path extends substantially axially from the fuel supply line to the plurality of fuel injectors.

[0408] According to any of the foregoing provisions, the method further includes guiding the fuel from the fuel supply line to the fuel injector via the fuel path.

[0409] The method according to any of the foregoing clauses further includes absorbing heat from the fuel from the steam in the steam path as the fuel flows through the fuel path.

[0410] The method according to any of the foregoing clauses further includes guiding the steam in the steam path in a direction opposite to the direction of the combustion gas.

[0411] The method according to any of the foregoing clauses further includes guiding the fuel through the fuel path in a direction opposite to the direction of the combustion gases.

[0412] According to any of the methods described in the foregoing clauses, the steam path is provided in the outer liner or the inner liner.

[0413] According to any of the preceding clauses, the one or more steam injection holes are provided in the outer liner or the inner liner.

[0414] According to any of the methods described in the foregoing clauses, the steam path is arranged in the annular dome.

[0415] According to any of the preceding clauses, the one or more steam injection holes are disposed in the annular dome.

[0416] According to any of the foregoing clauses, the burner steam system further includes one or more flame-forming orifices configured to pass through the annular dome, and the method further includes guiding the steam through the one or more flame-forming orifices 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 orifices.

[0417] According to any of the preceding descriptions, the one or more flame-forming holes are angled toward the flame.

[0418] According to any of the preceding clauses of the method, the annular dome includes one or more mixing component holes for receiving the plurality of mixing components, the one or more flame-forming holes being radially positioned between the one or more mixing component holes and the one or more steam injection holes.

[0419] According to any of the preceding clauses, the one or more flame-forming holes are larger than the one or more steam injection holes.

[0420] According to any of the methods described in the foregoing clauses, the steam path has a generally swirling shape.

[0421] According to any of the foregoing provisions, the outer liner, the inner liner, and the annular dome form a single, unified component.

[0422] According to any of the preceding clauses, the steam path includes a bushing steam path disposed within the outer liner or the inner liner and a dome steam path disposed within the annular dome.

[0423] According to any of the methods described in the foregoing clauses, the bushing steam path is fluidly connected to the dome steam path.

[0424] According to the method described in any of the foregoing clauses, 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] According to any of the foregoing provisions, 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 the combustion chamber outlet of the combustion chamber.

[0426] According to any of the preceding clauses, the combustion chamber includes a total combustion chamber length axially defined from the downstream surface of the annular dome to the combustion chamber outlet.

[0427] According to any of the preceding clauses, the one or more dilution holes are positioned on the outer or inner liner with a dilution hole length measured from the downstream surface of the annular dome to the axial center of the one or more dilution holes.

[0428] According to any of the preceding clauses, the length of the dilution hole is in the range of 10% to 90% of the total combustion chamber length.

[0429] While the foregoing description is directed to preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection 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 by Comprising: a combustion chamber comprising 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; one or more air dilution holes operable to direct compressed air through at least one of the outer liner or the inner liner into the combustion chamber; and a combustor steam system in fluid communication with the combustion chamber, the combustor steam system comprising: a steam path defined by and disposed within at least one of the outer liner or the inner liner such that the steam path is axially aft of the annular dome; one or more steam injectors extending from a forward portion of the steam path that is axially forward of the one or more air dilution holes; and one or more steam injection holes extending from an aft portion of the steam path into the combustion chamber that is axially aft of the one or more air dilution holes, wherein the combustor steam system is operable to direct steam into the steam path via the one or more steam injectors and into the combustion chamber via the one or more steam injection holes. wherein, the combustor steam system is operable to direct the steam away from the combustion zone.

2. The burner of claim 1, wherein wherein, the steam in the combustion chamber has a water-to-air ratio with the compressed air of 0.0% to 60%.

3. The burner of claim 1, wherein further comprising one or more steam dilution holes extending from the steam path and through the at least one of the outer liner or the inner liner into the combustion chamber, wherein the combustor steam system is operable to inject at least a portion of the steam into the combustion chamber axially aft of at least one of the one or more air dilution holes or the one or more steam dilution holes. wherein, 4. The burner of claim 1, wherein the combustor steam system comprises one or more steam cooling holes extending from the steam path and through the at least one of the outer liner or the inner liner into the combustion chamber, the one or more steam cooling holes being operable to direct the steam therethrough to cool the at least one of the outer liner or the inner liner.

5. The burner of claim 1, wherein wherein, the one or more steam injectors are annular about the combustion chamber.

6. The burner of claim 1, wherein wherein, the one or more steam injection holes are positioned on at least one of the outer liner or the inner liner at least 25% of a total combustion chamber length of the combustion chamber, wherein the total combustion chamber length of the combustion chamber is defined axially from a downstream surface of the annular dome to a combustion chamber exit.

7. The burner of claim 1, wherein wherein the combustor steam system is operable to direct steam through the steam path and into the combustion chamber downstream of the combustion zone and the one or more air dilution holes. ​ 8. The burner of claim 1, wherein ​ 9. The burner of claim 1, wherein wherein the steam path has a zig-zag shape extending axially rearward from the one or more steam injectors and around the one or more air dilution holes to the one or more steam injection holes.

10. The burner of claim 1, wherein wherein the steam path includes one or more circumferentially extending portions and one or more axially extending portions fluidly coupled with the one or more circumferentially extending portions.

11. The burner of claim 10, wherein wherein the one or more steam injection holes extend from the one or more circumferentially extending portions of the steam path and into the combustion chamber.

12. The burner of claim 10, wherein wherein the one or more steam injection holes extend from the one or more axially extending portions of the steam path and into the combustion chamber.

13. A method of operating a combustor as defined in claim 1, characterized by, The method includes: generating the fuel-air mixture with 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 with the combustor steam system via the one or more steam injectors, the steam path defined by and disposed within the at least one of the outer liner or the inner liner; and directing the steam from the steam path and into the combustion chamber via the one or more steam injection holes.

14. The method of claim 13, wherein, further comprising directing the steam away from the combustion zone.

15. The method of claim 13, wherein, further comprising injecting the steam with the combustor steam system during mid-power operation of the combustor and during high-power operation of the combustor.

16. The method of claim 13, wherein, further comprising directing the steam into the combustion chamber such that the steam in the combustion chamber has a water-to-air ratio of 0.0% to 60% of the compressed air.

17. The method of claim 13, wherein, wherein, the combustor includes one or more steam dilution holes extending from the steam path and into the combustion chamber through the at least one of the outer liner or the inner liner, and the method further comprises directing at least a portion of the steam into the combustion chamber axially rearward of at least one of the one or more air dilution holes or the one or more steam dilution holes.

18. The method of claim 13, wherein, wherein, the combustor steam system includes one or more steam cooling holes extending from the steam path and into the combustion chamber through the at least one of the outer liner or the inner liner, and the method further comprises operatively directing the steam through the one or more steam cooling holes to cool the at least one of the outer liner or the inner liner.

19. The method of claim 13, wherein, 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 that is at least 25% of a total combustion chamber length of the combustion chamber, wherein the total combustion chamber length of the combustion chamber is defined axially from a downstream surface of an annular dome to a combustion chamber exit.

20. The method of claim 13, wherein, Further comprising directing the steam from the steam path through one or more steam dilution holes and into the combustion chamber at a location ranging from 10% to 90% of the total combustion chamber length of the combustion chamber, wherein the total combustion chamber length of the combustion chamber is defined axially from a downstream surface of an annular dome to a combustion chamber exit.

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