Gas turbine engine with steam generation system for providing steam to combustor

Abstract

A gas turbine engine includes a steam generation system and a combustor. The combustor includes a combustor liner defining a combustion chamber, an outer housing defining an outer airflow passage between the outer housing and the combustor liner, and an inner housing defining an inner airflow passage between the inner housing and the combustor liner. At least one steam injection nozzle extends through the outer housing or through the inner housing and, during operation of the gas turbine engine, is arranged to provide a stream of steam generated by the steam generation system to the secondary combustion zone of the combustion chamber without providing steam to the primary combustion zone of the combustion chamber.

Description

Technical Field

[0001] The present disclosure generally relates to a gas turbine engine, and more particularly, to a gas turbine engine including a steam generation system that provides steam to a combustor. Background Art

[0002] The combustor of a gas turbine engine typically includes a swirler that provides a swirling airflow mixed with fuel into a combustion chamber, where the fuel and air mixture is ignited and burned. The combustion of the fuel and air mixture in the combustion chamber results in the emission of carbon monoxide (CO) and nitrogen oxides (NO x ) from the combustor. One technique for attempting to reduce CO and NO x emissions is to directly inject steam or water into the swirler via, for example, a fuel nozzle to mix with the fuel and air mixture. Brief Description of the Drawings

[0003] The features and advantages of the present disclosure will become apparent from the following description of various exemplary embodiments shown in the drawings, where like reference numerals generally denote like, functionally similar, and / or structurally similar elements.

[0004] Figure 1 is a schematic partial cross-sectional side view of an exemplary high bypass turbofan jet engine and a steam generation system in accordance with one aspect of the present disclosure.

[0005] Figure 2 is a schematic view of a high bypass turbofan jet engine and a steam generation system in accordance with one aspect of the present disclosure Figure 1 thereof.

[0006] Figure 3 is a schematic partial cross-sectional side view of an exemplary combustor of a turbine engine as shown in accordance with one aspect of the present disclosure Figure 1 thereof.

[0007] Figure 4 is a schematic partial cross-sectional side view of a combustor in accordance with one aspect of the present disclosure, having an Figure 3 alternative arrangement of the steam injection nozzles as shown.

[0008] Figure 5 is a schematic partial cross-sectional side view of a combustor in accordance with one aspect of the present disclosure, having another alternative arrangement of the steam injection nozzles.

[0009] Figure 6 is a schematic partial cross-sectional rear view of a combustor taken along plane 6-6 through Figure 5 thereof.

[0010] Figure 7An enlarged detailed view of an outer steam injection nozzle and an outer steam manifold taken at detail 201 of Figure 5 in accordance with one aspect of the present disclosure.

[0011] Figure 8 A partial cross-sectional view through an outer steam injection nozzle taken at plane 8-8 of Figure 7 in accordance with one aspect of the present disclosure.

[0012] Figure 9 A partial cross-sectional side view of a burner in accordance with one aspect of the present disclosure, having an alternative arrangement of steam injection nozzles.

[0013] Figure 10 A partial cross-sectional rear view of a burner taken at plane 10-10 of Figure 9 in accordance with one aspect of the present disclosure. Figure 9 in accordance with one aspect of the present disclosure.

[0014] Figure 11 A partial cross-sectional side view of a burner in accordance with one aspect of the present disclosure, having an alternative arrangement of steam injection nozzles.

[0015] Figure 12 An enlarged cross-sectional detailed view of a steam injection nozzle taken at detail 245 of Figure 11 in accordance with one aspect of the present disclosure.

[0016] Figure 13A A partial cross-sectional view through a steam injection nozzle taken at plane 13-13 of Figure 12 in accordance with one aspect of the present disclosure. Figure 12 in accordance with one aspect of the present disclosure.

[0017] Figure 13B Depicts an alternative arrangement of a cross-section of Figure 13A in accordance with another aspect of the present disclosure.

[0018] Figure 13C Depicts another alternative arrangement of a cross-section of Figure 13A in accordance with another aspect of the present disclosure.

[0019] Figure 14 A partial cross-sectional rear view of a burner taken at plane 14-14 of Figure 11 in accordance with one aspect of the present disclosure. Figure 11 in accordance with one aspect of the present disclosure. DETAILED DESCRIPTION

[0020] The features, advantages, and embodiments of the present disclosure are set forth or are apparent from a consideration of the following detailed description, the drawings, and the claims. In addition, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the claimed present disclosure.

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

[0022] As used herein, the terms "first" or "second" can be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of the respective components.

[0023] The terms "upstream" and "downstream" refer to the relative directions with respect to the flow of fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction towards which the fluid flows.

[0024] The terms "front" and "rear" refer to relative positions within a gas turbine engine or a vehicle and refer to the normal operating attitude of the gas turbine engine or the vehicle. For example, for a turbine engine, the front refers to the position closer to the engine inlet, and the rear refers to the position closer to the engine nozzle or exhaust outlet.

[0025] Unless otherwise specified herein, the terms "coupled", "fixed", "attached", "connected", etc. refer to direct coupling, fixing, attachment, or connection, as well as indirect coupling, fixing, attachment, or connection through one or more intermediate components or features.

[0026] Unless the context clearly dictates otherwise, the singular forms "a", "an", and "the" include plural references.

[0027] As used herein, the terms "axial" and "axially" refer to directions and orientations extending generally parallel to the centerline of an aircraft gas turbine engine. In addition, the terms "radial" and "radially" refer to directions and orientations extending generally perpendicular to the centerline of an aircraft gas turbine engine. Further, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending arcuately around the centerline of the turbine engine.

[0028] Here and throughout the specification and claims, range limitations are combined and interchanged. Unless the context or language indicates otherwise, these ranges are identified and include all sub-ranges subsumed therein. For example, all ranges disclosed herein include the endpoints, and the endpoints can be combined independently of each other.

[0029] In an aircraft gas turbine engine, a combustor typically may include a swirler that provides a swirling airflow mixed with fuel into a combustion chamber, where the fuel and air mixture is ignited and burned. Combustion of the fuel and air mixture in the combustion chamber results in carbon monoxide (CO) and nitrogen oxides (NO x ) emissions from the combustor. One technique for attempting to reduce CO and NO x emissions is to directly inject steam or water, via, for example, a fuel nozzle, into the fuel and air mixture so as to mix with the fuel and air within the swirler before the mixture enters the combustion chamber for ignition. However, directly injecting steam into the fuel and air mixture within the swirler in this manner may result in flameout conditions, or may reduce the effectiveness and efficiency of the combustion process such that not all of the fuel is ignited and burned within the combustor.

[0030] The present disclosure provides a technique for reducing CO and NO x emissions by including a steam injection nozzle in the downstream end of the combustor to inject steam into a secondary combustion zone of the combustion chamber. The steam may be injected into the secondary combustion zone such that the steam can mix with the combustion products within the combustion chamber in the secondary combustion zone without injecting the steam into the primary combustion zone. Thus, there is a lower likelihood of initiating a flameout condition within the primary combustion zone while reducing NO x and CO emissions from the combustor. Additionally, injecting steam into the secondary combustion zone increases the density of the combustion gases flowing through a turbine section downstream of the combustor, thereby providing thrust augmentation for the gas turbine engine when needed during high power operating conditions.

[0031] Referring now to the drawings, Figure 1 is a schematic cross-sectional view of an aircraft gas turbine engine 10 taken along a longitudinal centerline axis 12 (provided for reference) of the aircraft gas turbine engine 10 according to an embodiment of the present disclosure. The aircraft gas turbine engine 10 may be mounted on an aircraft (not shown) and includes a steam generation system 100 (described below). The present disclosure may be implemented in various types of aircraft turbine engines, including high bypass turbofan engines, turbojet engines, and turboprop engines. As Figure 1 shown, the aircraft gas turbine engine 10 has a longitudinal direction L (extending parallel to the longitudinal centerline axis 12) and a radial direction R perpendicular to the longitudinal direction L. Generally, the aircraft gas turbine engine 10 includes a fan section 14 and a turbine engine 16 located downstream of the fan section 14.

[0032] The turbine engine 16 includes an outer casing 18 that is generally tubular and defines an annular inlet 20. As Figure 1As schematically shown, the outer casing 18 surrounds the compressor section 21, the combustor 26, the turbine section 27, and the exhaust section 31 in a series flow relationship. The compressor section 21 includes a booster or low-pressure compressor (LPC) 22, immediately downstream of which is the high-pressure compressor (HPC) 24. The turbine section 27 includes a high-pressure turbine (HPT) 28, immediately downstream of which is the low-pressure turbine (LPT) 30. The exhaust section 31 includes one or more core exhaust nozzles 32. The compressor section 21, the combustor 26, the turbine section 27, and the exhaust section 31 (including one or more core exhaust nozzles 32) together define a core air flow path 33 therethrough. The high-pressure (HP) shaft 34 drivingly connects the HPT 28 to the HPC 24 so that the HPT 28 and the HPC 24 rotate together. The low-pressure (LP) shaft 36 drivingly connects the LPT 30 to the LPC 22 so that the LPT 30 and the LPC 22 rotate together.

[0033] For Figure 1 the illustrated embodiment, the fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 that are circumferentially spaced and coupled to a disk 42. As Figure 1 shown, the fan blades 40 extend generally radially outward from the disk 42 along a radial direction R. By virtue of the fan blades 40 being operatively coupled to an actuator 44 configured to collectively and uniformly change the pitch of the fan blades 40, each fan blade 40 is capable of rotating relative to the disk 42 about a pitch axis P. The fan blades 40, the disk 42, and the actuator 44 are capable of rotating together about a longitudinal centerline axis 12 via a fan shaft 45, and the fan shaft 45 is powered by the LP shaft 36 via a power gearbox (also referred to as a gearbox assembly 46). The gearbox assembly 46 is Figure 1 schematically shown therein. The gearbox assembly 46 includes a plurality of gears (not shown) for adjusting the rotational speed of the fan shaft 45 and for adjusting the rotational speed of the fan 38 relative to the LP shaft 36.

[0034] Still referring to Figure 1 the exemplary embodiment of, the disk 42 is covered by a rotatable fan hub 48 that has an aerodynamic profile to facilitate air flow through the plurality of fan blades 40. Additionally, the fan section 14 includes an annular fan casing or nacelle 50 that circumferentially surrounds the fan 38 and / or at least a portion of the turbomachine 16. The nacelle 50 is supported relative to the turbomachine 16 by a plurality of circumferentially spaced struts or exit guide vanes 52. Further, a downstream section 54 of the nacelle 50 extends over an outer portion of the turbomachine 16 to define a bypass air flow passage 56 therebetween. One or more core exhaust nozzles 32 may extend through the nacelle 50 and be formed therein. In Figure 1In an embodiment, one or more core exhaust nozzles 32 include one or more discrete nozzles that are circumferentially spaced about nacelle 50. Other arrangements of one or more core exhaust nozzles 32 may be employed instead, including, for example, a single core exhaust nozzle that is annular or partially annular about nacelle 50.

[0035] During standard operating modes of aircraft gas turbine engine 10, a quantity of air 58 enters aircraft gas turbine engine 10 through inlet 60 of nacelle 50 and / or fan section 14. As the quantity of air 58 passes through fan blades 40, a first portion of air 58 (shown as bypass air 62) is directed or guided into bypass air flow path 56, while a second portion of air 58 (shown as core air 64) is directed or guided into an upstream section of core air flow path 33, or more specifically, into annular inlet 20 of LPC 22. The ratio between bypass air 62 and core air 64 is referred to as the bypass ratio. The pressure of core air 64 is then increased by LPC 22 to produce compressed air 65, which is directed through HPC 24 where it is further compressed and then directed into combustor 26. In combustor 26, compressed air 65 is mixed with fuel 67 and burned to produce combustion gases 66 (also referred to as combustion products). One or more stages may be used in both LPC 22 and HPC 24, where each subsequent stage further compresses compressed air 65.

[0036] Combustion gas 66 is directed from the burner 26 into the HPT 28 and expands through the HPT 28. In the HPT 28, a portion of the thermal energy and / or kinetic energy in the combustion gas 66 is extracted via successive stages of HPT stator vanes 68 coupled to the outer casing 18 and HPT rotor blades 70 coupled to the rotor connected to the HPT shaft 34, causing the HP shaft 34 to rotate, thereby supporting the operation of the HPC 24. The combustion gas 66 is then directed into the LPT 30 and further expands through the LPT 30. At this time, a second portion of the thermal energy and / or kinetic energy is extracted from the combustion gas 66 via successive stages of LPT stator vanes 72 coupled to the outer casing 18 and LPT rotor blades 74 coupled to the LPT rotor connected to the LP shaft 36, causing the LP shaft 36 to rotate, thereby supporting the operation of the LPC 22 and the rotation of the fan 38 via the gearbox assembly 46. The HPT 28 and the LPT 30 can each employ one or more stages. Subsequently, the combustion gas 66 is directed through one or more core exhaust nozzles 32 of the turbine engine 16 to provide propulsion thrust. While the core air 64 flows through the core air flow path 33, the bypass air 62 is directed through the bypass air flow passage 56 and then discharged from the fan bypass nozzle 76 of the aircraft gas turbine engine 10, also providing propulsion thrust. The HPT 28, the LPT 30, and the one or more core exhaust nozzles 32 at least partially define a hot gas path 78 for directing the combustion gas 66 through the turbine engine 16.

[0037] As described above, the compressed air 65 is mixed with the fuel 67 in the burner 26, and a combusted fuel and air mixture is formed, generating combustion gas 66 (combustion products). The fuel 67 can include any type of hydrocarbon fuel for a turbine engine, such as sustainable aviation fuel (SAF), including biofuel, Jet A, Jet A-1, or other hydrocarbon fuels. Other fuel types, which may or may not be hydrocarbon fuels but are generally usable in an aircraft gas turbine engine, can also be used to implement the present disclosure. The aircraft gas turbine engine 10 also includes a fuel system 80 for supplying the fuel 67 to the burner 26. The fuel system 80 includes a fuel tank 82 for storing the fuel 67 therein and a fuel delivery assembly 84. The fuel tank 82 can be located on an aircraft (not shown) to which the aircraft gas turbine engine 10 is attached. Although Figure 1 a single fuel tank 82 is shown, the fuel system 80 can include any number of fuel tanks 82 as needed. The fuel delivery assembly 84 delivers the fuel 67 from the fuel tank 82 to the burner 26 via one or more fuel supply lines 85. The fuel delivery assembly 84 also includes a fuel pump 86 to direct the flow of the fuel 67 through the fuel supply line 85 to the burner 26. Thus, the fuel pump 86 pumps the fuel 67 from the fuel tank 82 through the fuel supply line 85 and into the burner 26.

[0038] The aircraft gas turbine engine 10 of the present disclosure includes a steam generation system 100 which, as will be described in more detail below, is in fluid communication with one or more core exhaust nozzles 32 and fan bypass nozzles 76. As will be described in more detail below, when combustion gases 66 flow through the steam generation system 100, the steam generation system 100 utilizes the combustion gases 66 to generate steam and can deliver at least a portion of the generated steam to the combustor 26.

[0039] Figure 1 The aircraft gas turbine engine 10 shown in is only an example. In other exemplary embodiments, the aircraft gas 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. Additionally, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable aircraft gas turbine engine, such as a turbofan engine, a propfan engine, and / or a turboprop engine.

[0040] Figure 2 is in accordance with one aspect of the present disclosure Figure 1 Schematic diagram of the aircraft gas turbine engine 10 and the steam generation system 100 in. For clarity, Figure 2 the aircraft gas turbine engine 10 is schematically shown in, while Figure 1 some of the components described and illustrated above in are not shown in Figure 2 As shown in Figure 2 the steam generation system 100 includes a boiler 102, a condenser 104, a water / exhaust separator 106, a water pump 108, and a steam turbine 110.

[0041] The boiler 102 is a heat exchanger that evaporates liquid water from a water source to produce steam or water vapor, as will be described in further detail below. Thus, the boiler 102 is a steam source. Specifically, the boiler 102 is an exhaust-water heat exchanger where the boiler 102 is in fluid communication with the hot gas path 78 ( Figure 1 ) and is located downstream of the LPT 30 such that the combustion gases 66 provide heat to the boiler 102 to boil the water within the boiler 102. The boiler 102 is also in fluid communication with the water pump 108, as will be described in further detail below, to replenish the water within the boiler 102. The boiler 102 may include any type of boiler or heat exchanger for extracting heat from the combustion gases 66 and evaporating the liquid water into steam or water vapor as the liquid water and the combustion gases 66 flow through the boiler 102.

[0042] The condenser 104 is located downstream of the boiler 102 and is a heat exchanger that further cools the combustion gas 66 as the combustion gas 66 flows from the boiler 102 through the condenser 104, as described in further detail below. Specifically, the condenser 104 is an air-exhaust heat exchanger. The condenser 104 is in fluid communication with the boiler 102 and is located within the bypass air flow passage 56. The condenser 104 can include any type of condenser for condensing water from the exhaust (e.g., the combustion gas 66).

[0043] The water / exhaust separator 106 is located downstream of the condenser 104 and is in fluid communication with the condenser 104 for receiving the cooled exhaust (combustion gas 66) entraining condensed water therein from the condenser 104. The water / exhaust separator 106 is also in fluid communication with one or more core exhaust nozzles 32 to supply the separated exhaust thereto and is in fluid communication with the water storage tank 107 to supply the separated water to the water storage tank 107. The water / exhaust separator 106 includes any type of water separator for separating water from the exhaust. For example, the water / exhaust separator 106 can include a cyclone separator that uses vortex separation to separate water from the exhaust. In such an embodiment, the water / exhaust separator 106 generates a swirling flow within the water / exhaust separator 106 to separate water from the cooled exhaust. In Figure 2 the figure, the water / exhaust separator 106 is schematically shown as being located within the nacelle 50, but the water / exhaust separator 106 can be located at other locations within the aircraft gas turbine engine 10, e.g., radially inside the nacelle 50, closer to the turbine engine 16. The water / exhaust separator 106 can be driven to rotate by one of the engine shafts (e.g., the HP shaft 34 or the LP shaft 36) via, for example, an accessory gearbox (not shown).

[0044] As described above, the boiler 102 receives liquid water from a water source to generate steam or water vapor. The water source can be the water storage tank 107 disposed between the water / exhaust separator 106 and the water pump 108. Thus, in Figure 2In the illustrated embodiment, the water storage tank 107 can be a water source for the boiler 102. The water pump 108 is in fluid communication with the water storage tank 107 and with the boiler 102. The water pump 108 can be any suitable pump, such as a centrifugal pump or a positive displacement pump. The water pump 108 directs the separated water 112 stored in the water storage tank 107 to the boiler 102, where the separated water 112 is stored as water 111 and then converted back to steam 114. The steam 114 is conveyed through the steam turbine 110 via the steam supply line 88 to provide work to drive the steam turbine 110, and a first portion 120 (also referred to as "steam 120") of the remaining steam 114 from the steam turbine 110 can be directed to the burner 26 via the steam supply line 94. Alternatively, a second portion 122 of the remaining steam 114 can be directed back to the boiler 102 via the steam supply line 90.

[0045] In the operation of the steam generation system 100, the combustion gas 66 (also referred to as the exhaust gas) flows from the LPT 30 into the boiler 102 and into the condenser 104. The combustion gas 66 transfers heat to the water 111 within the boiler 102 to generate steam 114 within the boiler 102. Then, the combustion gas 66 flows into the condenser 104, and the condenser 104 condenses the water contained within the combustion gas 66. The bypass air 62 flows through the bypass air flow passage 56 and through or across the condenser 104, and extracts heat from the combustion gas 66, cooling the combustion gas 66 and condensing the water within the combustion gas 66 to produce an exhaust - water mixture 116. Then, the bypass air 62 is discharged from the aircraft gas turbine engine 10 through the fan bypass nozzle 76 to produce thrust, as described above. Thus, the condenser 104 can be located within the bypass air flow passage 56.

[0046] The exhaust - water mixture 116 flows into the water / exhaust separator 106. The water / exhaust separator 106 separates water and exhaust from the exhaust - water mixture 116 to produce separated exhaust 118 and water 112. The exhaust 118 is discharged from the aircraft gas turbine engine 10 through one or more core exhaust nozzles 32 to produce thrust, as described above. The boiler 102, the condenser 104, and the water / exhaust separator 106 thus also define a portion of the hot gas path 78 ( Figure 1 ) for directing the combustion gas 66, the exhaust - water mixture 116, and the exhaust 118 through the steam generation system 100 of the aircraft gas turbine engine 10.

[0047] The water pump 108 helps to pump the water 112 from the water / exhaust separator 106 into the water storage tank 107 and pumps the water 112 through one or more water pipelines, such as Figure 2As indicated by the arrow of the intermediate water 112, the intermediate water 112 flows into the boiler 102 to mix with the water 111. The water 111 flows through the boiler 102, and the combustion gas 66 flowing through the boiler 102 transfers heat to the water 111 to evaporate the water 111 and generate steam 114.

[0048] The steam turbine 110 is connected to the LP shaft 36, but can also be connected to the HP shaft 34. The steam turbine 110 includes one or more stages of steam turbine blades (not shown) and steam turbine stators (not shown). The steam 114 flows from the boiler 102 into the steam turbine 110 via the steam supply line 88, causing the steam turbine blades of the steam turbine 110 to rotate, thereby generating additional work in the LP shaft 36. In addition, at least a portion of the steam 114 can flow through one or more steam supply lines 98 into the burner 26, and a steam supply control valve 92 can be provided in the steam supply line 98 to control the flow of the steam 114 into the burner 26. As for the steam 114 supplied to the steam turbine 110, the remaining steam 120 of the steam 114 can then flow from the steam turbine 110 through one or more steam supply lines 94 and into the burner 26, and a steam supply control valve 93 can be included in the steam supply line 94. Alternatively, a second portion 122 of the remaining steam 114 can then flow back from the steam turbine 110 to the boiler 102 through one or more steam supply lines 90.

[0049] Figure 3 is according to one aspect of the present disclosure Figure 1 A partial cross-sectional side view of an exemplary burner 26 of the turbine engine 16 as shown in Figure 3 The exemplary burner 26 shown in Figure 3 is depicted as an annular combustion section circumferentially extending around the longitudinal centerline axis 12, although Figure 3 only the upper portion (above the longitudinal centerline axis 12) is shown. With respect to the burner 26, the longitudinal centerline axis 12 of the gas turbine engine 10 can also correspond to the burner longitudinal centerline axis 12'. The burner 26 includes an outer housing 124, an inner housing 126, and a burner liner 128 disposed between the outer housing 124 and the inner housing 126. As Figure 3 shown, the burner liner 128 includes an inner liner 130, an outer liner 132, and a dome structure 134, each of which circumferentially extends around the burner longitudinal centerline axis 12'. The outer liner 132 can include various liner openings therethrough, including a plurality of main combustion zone liner openings 136, a plurality of outer liner dilution openings 138 ( Figure 3One) and a plurality of secondary combustion zone bushing openings 146 are shown. Additionally, the dome structure 134 may include a plurality of cooling air flow openings 148 therethrough. Further, the downstream end 143 of the outer housing 124 may include a plurality of turbine cooling openings 141 to provide a turbine cooling air flow 183 into the HPT 28, and the downstream end 149 of the inner housing 126 may include a plurality of turbine cooling openings 147 to provide a turbine cooling air flow 189 into the HPT 28. As will be described in more detail below, each of the openings through the inner bushing 130, through the outer bushing 132, and through the dome structure 134 allows air to flow into the combustion chamber 131 to provide cooling for the burner bushing 128 or the dome structure 134, or to quench the combustion gases within the combustion chamber 131. Additionally, as will be described in more detail below, the air flowing through the various openings may be mixed with steam to help reduce NO x emissions, or to increase the thrust of the gas turbine engine 10.

[0050] The burner 26 also includes a plurality of swirler assemblies 156 ( Figure 3 one of which is shown) connected to the dome structure 134, and a plurality of fuel nozzle assemblies 158 ( Figure 3 one of which is shown) connected to respective ones of the plurality of swirler assemblies 156.

[0051] The inner bushing 130 and the outer bushing 132 are connected to the dome structure 134, thereby defining a combustion chamber 131 therebetween. The inner bushing 130 and the outer bushing 132 extend from the dome structure 134 to a burner outlet 150 at the inlet of the HPT 28 ( Figure 1 ), at least partially defining a hot gas path between the dome structure 134 and the HPT 28. The combustion chamber 131 may theoretically be divided into a primary combustion zone 133 in an upstream portion 127 of the burner bushing 128 and a secondary combustion zone 137 in a downstream portion 129 of the burner bushing 128. The primary combustion zone 133 may extend from the dome structure 134 to the starting point of the dilution zone 135, which Figure 3 is marked as a dashed line 139 in, and the dashed line 139 extends between the upstream side of the outer bushing dilution opening 138 and the upstream side of the inner bushing dilution opening 144. The dilution zone 135 is a part of the secondary combustion zone 137 and is also a region of the combustion chamber 131 where the combustion gases 66 are initially quenched when dilution air flows (as described below) through the outer bushing dilution opening 138 and the inner bushing dilution opening 144 into the dilution zone 135. The outer bushing dilution opening 140 and the inner bushing dilution opening 144 are arranged at the upstream end 145 of the secondary combustion zone 137.

[0052] The burner 26 further includes a shroud 152 that is connected to the inner liner 130, the outer liner 132, and the dome structure 134, thereby defining an air chamber 154 therein. The shroud 152 extends circumferentially around the longitudinal centerline axis 12' of the burner and may be formed of a single shroud structure or multiple shroud structures connected together. The shroud 152 includes a plurality of shroud air flow openings 157 ( Figure 3 one is shown), and each shroud air flow opening 157 corresponds to a respective one of the plurality of swirler assemblies 156. As described below, each shroud air flow opening 157 provides an air flow therethrough into the air chamber 154. The shroud 152 is connected to the outer housing 124 via a shroud mounting arm 153.

[0053] As Figure 3 shown, the outer housing 124 and the inner housing 126 surround the burner liner 128. An outer air flow passage 160 is defined between the outer housing 124 and the outer liner 132, and an inner air flow passage 162 is defined between the inner housing 126 and the inner liner 130. A diffuser 164 is connected to the burner 26 between the upstream end 166 of the outer housing 124 and the upstream end of the inner housing 126. A pressure air chamber 170 is defined between the upstream end 166 of the outer housing 124 and the upstream end 168 of the inner housing 126. The diffuser 164 supplies the compressed air 65 flow from the HPC 24 into the pressure air chamber 170.

[0054] Still referring to Figure 3 , during operation of the aircraft gas turbine engine 10, the compressed air 65 flows through the diffuser 164 and into the pressure air chamber 170 of the burner 26 to pressurize the pressure air chamber 170. A first portion of the compressed air 65 in the pressure air chamber 170 (as indicated by the arrow representing the compressed air 172) flows from the pressure air chamber 170 into the air chamber 154 of the shroud 152. Then, the compressed air 172 flows through the swirler assembly 156, where the compressed air 172 is mixed with the fuel supplied to the swirler assembly 158 by the fuel nozzle assembly 158. Then, the swirler fuel-air mixture 191 is ejected into the combustion chamber 131 by the swirler assembly 156, and the swirler fuel-air mixture 191 is ignited and burned by an igniter (not shown) to generate combustion gases 66 within the combustion chamber 131. The initial combustion (ignition and burning) of the swirler fuel-air mixture 191 occurs within the main combustion zone 133, and the combustion gases 66 generally flow within the combustion chamber 133 in the axial flow direction 197. A portion of the compressed air 172 within the air chamber 154 (schematically indicated by the arrow representing the cooling air 190) may flow through the cooling air flow openings 148 in the dome structure 134 to provide cooling of the downstream side of the dome structure 134. Although Figure 3Although not shown in the figure, the dome structure 134 may include a flow guide or a heat insulator on the downstream side to protect the dome structure 134 from the heat generated in the combustion chamber 131, and the cooling air flow opening 148 may also be provided through the flow guide or the heat insulator.

[0055] A second portion of the compressed air 65 in the pressure air chamber 170 (schematically shown by the arrows indicating the compressed air 174 and the compressed air 176) can be respectively guided into the outer air flow channel 160 and the inner air flow channel 162. The compressed air 174 and the compressed air 176 flow in the downstream direction 177 in the outer air flow channel 160 and the inner air flow channel 162 respectively, and as described below, steam can be injected into the outer air flow channel 60 and the inner air flow channel 162 in the upstream direction 179. A part of the compressed air 174 flowing through the outer air flow channel 160 (schematically shown as the cooling air 178) can be guided through a plurality of main combustion zone bushing openings 136 into the combustion chamber 131. Another part of the compressed air 174 flowing through the outer air flow channel 160 (schematically shown as the dilution air flow 180) can be guided through the outer bushing dilution opening 138 into the dilution zone 135 of the combustion chamber 131 to provide quenching of the combustion gas 66. Yet another part of the compressed air 174 flowing through the outer air flow channel 160 (schematically shown as the cooling air 182) can be guided through the secondary combustion zone bushing opening 140 into the secondary combustion zone 137 of the combustion chamber 131.

[0056] Similarly, a part of the compressed air 176 flowing through the inner air flow channel 162 (schematically shown as the cooling air 184) can be guided through a plurality of main combustion zone bushing openings 142 into the main combustion zone 133 of the combustion chamber 131. Another part of the compressed air 176 flowing through the inner air flow channel 162 (schematically shown as the dilution air flow 186) can be guided through the inner bushing dilution opening 144 of the inner bushing 130 into the dilution zone 135 of the combustion chamber 131 to provide quenching of the combustion gas 66. Yet another part of the compressed air 176 flowing through the inner air flow channel 162 (schematically shown as the cooling air 188) can be guided through the secondary combustion zone bushing opening 146 into the secondary combustion zone 137 of the combustion chamber 131.

[0057] As Figure 3Further shown, the burner 26 may include at least one outer steam injection nozzle 192 extending through the outer housing 124, or may include at least one inner steam injection nozzle 194 extending through the inner housing 126. The burner 26 may include one of the outer steam injection nozzle 192 or the inner steam injection nozzle 194, or may include both the outer steam injection nozzle 192 and the inner steam injection nozzle 194. The outer steam injection nozzle 192 and the inner steam injection nozzle 194 are connected to the steam supply line 98 and the steam supply line 94. The outer steam injection nozzle 192 is arranged to inject steam 114 or steam 120 into the downstream portion 196 of the outer air flow passage 160, and the inner steam injection nozzle 194 is arranged to inject steam 114 or steam 120 into the downstream portion 198 of the inner air flow passage 162. In particular, in Figure 3 the aspect of, the outer steam injection nozzle 192 is arranged downstream of the outer liner dilution opening 138, and the inner steam injection nozzle 194 is arranged downstream of the inner liner dilution opening 144. The velocity of the compressed air 174 within the outer air flow passage 160 is generally high enough such that the steam 114 or steam 120 injected into the downstream portion 196 of the outer air flow passage 60 does not flow upstream beyond the outer liner dilution opening 138. Instead, the steam 114 or steam 120 injected into the downstream portion 196 of the outer air flow passage 160 mixes with the compressed air 174 in the downstream portion 196 of the outer air flow passage 60 to produce a steam-air mixture 182', and the steam-air mixture 182' flows through the sub-combustion zone liner opening 140 and into the sub-combustion zone 137 of the combustion chamber 131. Some of the steam-air mixture 182' may also flow as a steam-air mixture 183' through the turbine cooling opening 141 into the turbine HPT 28. Additionally, the steam supply control valve 92 and the steam supply control valve 93 ( Figure 2 ) may respectively control the amount of steam 114 or steam 120 provided to the outer steam injection nozzle 192 to prevent the steam 114 or steam 120 from flowing upstream beyond the outer liner dilution opening 138. As a result, the steam 114 or steam 120 can be provided to the sub-combustion zone 137 without being provided to the main combustion zone 133, thereby reducing the likelihood of initiating a flameout condition within the main combustion zone 133 while also reducing the CO and NO in the combustion gas 66 as the combustion gas 66 flows through the sub-combustion zone 137 x emissions.

[0058] Similarly, with respect to the inner steam injection nozzle 194 that injects steam 114 into the downstream portion 198 of the inner air flow passage 162, the velocity of the compressed air 176 within the inner air flow passage 162 is generally high enough such that the steam 114 or steam 120 injected into the downstream portion 198 of the inner air flow passage 162 does not flow upstream beyond the liner dilution opening 144. Instead, the steam 114 or steam 120 injected into the downstream portion 198 of the inner air flow passage 162 mixes with the compressed air 176 in the downstream portion 198 of the inner air flow passage 162 to produce a steam-air mixture 188', and then the steam-air mixture 188' flows through the sub-combustion zone liner opening 146 and into the sub-combustion zone 137 of the combustion chamber 131. Some of the steam-air mixture 188' can also flow as a steam-air mixture 189' through the turbine cooling opening 147 into the turbine HPT 28. Similarly, the steam supply control valve 92 and the steam supply control valve 93( Figure 2 ) can respectively control the amount of steam 114 or steam 120 provided to the inner steam injection nozzle 194 to prevent the steam 114 or steam 120 from flowing upstream beyond the liner dilution opening 144. As a result, the steam 114 or steam 120 can be provided to the sub-combustion zone 137 without being provided to the main combustion zone 133, thereby reducing the likelihood of initiating a flameout condition within the main combustion zone 133 while also reducing the CO and NO x emissions in the combustion gas 66 as the combustion gas 66 flows through the sub-combustion zone 137.

[0059] Figure 4 is a partial cross-sectional side view of the burner 26a according to one aspect of the present invention, having Figure 3 an alternative arrangement of the illustrated steam injection nozzles. In Figure 4 aspects, elements that are the same as those in Figure 3 aspects have the same reference numerals, and the description of these elements will not be repeated here. In Figure 4In one aspect, the outer steam injection nozzle 193 extends through the outer air flow passage 160 and through the outer liner 132 to directly supply a stream of steam 114 or steam 120 into the secondary combustion zone 137 of the combustion chamber 131. The outer steam injection nozzle 193 may extend through one of the secondary combustion zone liner openings 140 through the outer liner 132. Similarly, the burner 26a includes an inner steam injection nozzle 195 that extends through the inner air flow passage 162 and through the inner liner 130 to directly supply a stream of steam 114 or steam 120 into the secondary combustion zone 137 of the combustion chamber 131. The inner steam injection nozzle 195 may extend through one of the secondary combustion zone liner openings 146 of the inner liner 130. The steam 114 or steam 120 may interact and mix with the combustion gases 66 within the secondary combustion zone 137 rather than first mixing with the compressed air 174 within the outer air flow passage 160 or first mixing with the compressed gas 176 within the inner air flow passage 162.

[0060] Figure 5 FIG. 4 is a partial cross-sectional side view of a burner 26b according to one aspect of the present disclosure, having an alternative arrangement of steam injection nozzles. In Figure 5 one aspect, elements identical to those in Figure 3 the same aspect have the same reference numerals and the description of these elements will not be repeated here. In Figure 5 this aspect, the burner 26b includes an outer steam manifold 200 that may be connected to the inner side of the outer housing 124. The outer steam manifold 200 has a steam passage 202, and at least one outer steam injection nozzle 204 is connected to the outer steam manifold 200 and is in fluid communication with the steam passage 202. The outer steam manifold 200 is also connected to a steam supply line connector 206 that is connected to the steam supply line 98 and the steam supply line 94. The steam 114 or steam 120 is supplied from the steam supply line 98 or the steam supply line 94 to the outer steam manifold 200, the steam fills the steam passage 202, and then flows through at least one outer steam injection nozzle 204 into the outer air flow passage 160. In the same manner as in the Figure 3 above aspect, the steam 114 or steam 120 mixes with the compressed air 174 in the downstream portion 196 of the outer air flow passage 160 to produce a steam-air mixture 182', and then this mixture flows through the secondary combustion zone liner opening 140 into the secondary combustion zone 137.

[0061] Figure 5The burner 26b also includes an inner steam manifold 208 that can be connected to the outside of the inner casing 126. The inner steam manifold 208 has a steam passage 210, and at least one inner steam injection nozzle 212 is connected to the inner steam manifold 208 and is in fluid communication with the steam passage 210. The inner steam manifold 208 is also connected to a steam supply line connector 214, which is connected to the steam supply line 98 and the steam supply line 94. Steam 114 or steam 120 is provided to the inner steam manifold 208 from the steam supply line 98 or from the steam supply line 94, the steam fills the steam passage 210, and then flows through the at least one inner steam injection nozzle 212 into the inner air flow passage 162. In the same manner as described above Figure 3 In a similar manner, steam 114 or steam 120 mixes with compressed air 176 in the downstream portion 198 of the inner flow passage 162 to produce a steam-air mixture 188 ′, which then flows through the secondary combustion zone liner opening 146 into the secondary combustion zone 137 .

[0062] Figure 6 According to one aspect of the present disclosure Figure 5 The plane 6-6 is intercepted through Figure 5 A partial cross-sectional rear view of the burner 26b. Figure 6 , only the upper half of the burner 26b above the horizontal reference plane 216 passing through the longitudinal centerline axis 12' of the burner is shown, but the lower half of the burner 26b below the horizontal reference plane 216 can be a mirror image of the upper half, as shown in FIG. Figure 6 As shown. Figure 6 As shown, the burner 26b may include a plurality of external steam manifolds 200, including a first external steam manifold 200a, a second external steam manifold 200b (partially located at Figure 6 ) and a third outer steam manifold 200c (also partially in Figure 6 ). Each outer steam manifold 200 extends at least partially annularly about the combustor longitudinal centerline axis 12'. In addition, each outer steam manifold 200 includes a plurality of outer steam injection nozzles 204 extending into the outer airflow channel 160. Alternatively, rather than including a plurality of outer steam manifolds 200, a single annular outer steam manifold may be provided (as shown by the dashed line connecting, for example, the first outer steam manifold 200a with the second outer steam manifold 200b, and the dashed line connecting the first outer steam manifold 200a with the third outer steam manifold 200c, and continuing about the combustor longitudinal centerline axis 12 for the mirrored lower half).

[0063] Similarly, the combustor 26b may include a plurality of internal steam manifolds 208, including a first internal steam manifold 208a, a second internal steam manifold 208b (partially located at Figure 6 ) and a third inner steam manifold 208c (also partially inFigure 6 (shown in). Each inner steam manifold 208 extends at least partially annularly around the longitudinal centerline axis 12' of the burner. In addition, the inner steam manifold 208 includes a plurality of inner steam injection nozzles 212 that extend into the inner gas flow passage 162. Alternatively, a single annular inner steam manifold (as shown by the dashed lines connecting, for example, the first inner steam manifold 208a to the second inner steam manifold 208b, and the dashed lines connecting the first inner steam manifold 208a to the third inner steam manifold 208c, and continuing for the mirror image lower half around the longitudinal centerline axis 12 of the burner) may be provided instead of including a plurality of inner steam manifolds 208.

[0064] Although Figure 5 and Figure 6 the burner 26b is depicted as including both an outer steam manifold 200 with outer steam injection nozzles 204 and an inner steam manifold 208 with inner steam injection nozzles 212, the burner 26b does not have to include both at the same time. Instead, the burner 26b may include an outer steam manifold 200 with outer steam injection nozzles 204, or an inner steam manifold 208 with inner steam injection nozzles 212.

[0065] Figure 7 is an enlarged cross-sectional detail view of the outer steam injection nozzle 204 and the outer steam manifold 200 taken at detail 201 in Figure 5 in accordance with one aspect of the present disclosure. Figure 8 is a partial cross-sectional view through the outer steam injection nozzle 204 taken at plane 8-8 in Figure 7 in accordance with one aspect of the present disclosure. With common reference to Figure 7 and Figure 8 , the outer steam injection nozzle 204 has a closed tip 199 and includes a plurality of steam injection ports 203. Although Figure 8 eight steam injection ports 203 are shown in Figure 8 , more than eight or fewer than eight steam injection ports 203 may be included in the outer steam injection nozzle 204. In addition, although

[0066] The steam injection ports 203 are also shown as directing the flow of steam 114 or steam 120 in different directions within the outer air flow passage 160. For example, the first steam injection port 203a is arranged to direct the flow of steam 114 or steam 120 in the upstream direction 205. The second steam injection port 203b is arranged to direct the flow of steam 114 or steam 120 in an upstream-lateral direction, which directs the steam 114 and steam 120 in the upstream direction 205 and in the second lateral direction 211. The third steam injection port 203c is arranged to direct the flow of steam 114 or steam 120 in the second lateral direction 211. The fourth steam injection port 203d is arranged to direct the flow of steam 114 or steam 120 in a downstream-lateral direction, which directs the steam 114 and steam 120 in the second lateral direction 211 and in the downstream direction 207. The fifth steam injection port 203e is arranged to direct the flow of steam 114 or steam 120 in the downstream direction 207. The sixth steam injection port 203f is arranged to direct the flow of steam 114 or steam 120 in a downstream-lateral direction, which directs the steam 114 or steam 120 in the downstream direction 207 and in the first lateral direction 209. The seventh steam injection port 203g is arranged to direct the flow of steam 114 or steam 120 in the first lateral direction 209. The eighth steam injection port 203h is arranged to direct the flow of steam 114 or steam 120 in an upstream-lateral direction, which directs the steam 114 and steam 120 in the first lateral direction 209 and in the upstream direction 205. Thus, the steam injection ports 203 can disperse the flow of steam 114 or steam 120 in different directions within the outer air flow passage 160 to better mix with the compressed air 174. Of course, other arrangements of the steam injection ports 203 can also be implemented, and the present disclosure is not limited to Figure 7 and Figure 8 the arrangement shown. In addition, although Figure 7 and Figure 8 the outer steam manifold 200 and the outer steam injection nozzles 204 are described, Figure 7 and 8 the arrangements in

[0067] Figure 9 also apply to the inner steam manifold 208 and the inner steam injection nozzles 212.

[0067] Figure 9 is a partial cross-sectional side view of a burner 26c according to one aspect of the present disclosure, having another alternative arrangement of steam injection nozzles. Figure 10 is a partial cross-sectional rear view of a burner 26b taken at the plane 10-10 of Figure 9 according to one aspect of the present disclosure. In Figure 10 , only the upper half of the burner 26c above the horizontal reference plane 216 passing through the longitudinal centerline axis 12' of the burner is shown, but the lower half of the burner 26c below the horizontal reference plane can be a mirror image of the upper part as shown in Figure 10 . Referring jointly toFigure 9 and Figure 10 , and Figure 3 、 Figure 5 and Figure 6 For the same components in the aspects, the same reference numerals are used, and the description of these components will not be repeated here. In Figure 9 and Figure 10 aspects, one difference between the burner 26b and the burner 26c of Figure 5 and Figure 6 is that the steam injection nozzles are arranged to directly inject steam 114 into the combustion chamber 131, rather than injecting steam 114 into the outer gas flow channel 160 or the inner gas flow channel 162. In Figure 9 and Figure 10 , the burner 26c includes an outer steam manifold 218 and a plurality of outer steam injection nozzles 222. A steam channel 220 is provided inside the outer steam manifold 218, and the plurality of outer steam injection nozzles 222 are in fluid communication with the outer steam manifold 218. The outer steam manifold 218 can also be connected to an outer steam supply line 224, and a steam channel 226 is provided inside the outer steam supply line 224 to supply steam 114 to the outer steam manifold 218. The outer steam supply line 224 is connected to a steam supply line connector 228, and the steam supply line connector 228 is connected to the steam supply line 98( Figure 2 ) or to the steam supply line 94( Figure 2 ). Alternatively, the outer steam manifold 218 can include a steam supply line connector 206 as shown in Figure 5 instead of having the outer steam supply line 224. Similar to the outer steam manifold 200 shown in Figure 6 , in Figure 10 , the outer steam manifold 218 at least partially extends annularly around the longitudinal centerline axis 12' of the burner, and can include a plurality of outer steam manifolds 218, including a first outer steam manifold 218a, a second outer steam manifold 218b, and a third outer steam manifold 218c. Similar to the aspect of Figure 6 , the outer steam manifold 218 can alternatively extend annularly around the longitudinal centerline axis 12' of the burner. For example, as shown by the dashed lines connecting the first outer steam manifold 218a to the second outer steam manifold 218b and the dashed lines connecting the first outer steam manifold 218a to the third outer steam manifold 218c.

[0068] As described above for Figure 3 , the outer liner 132 includes a plurality of outer liner dilution openings 138 passing therethrough. Figure 10 Depicts a plurality of outer liner dilution openings 138 circumferentially spaced apart around the longitudinal centerline axis 12' of the burner. In Figure 9 and Figure 10In this aspect, a respective one of the plurality of outer steam injection nozzles 222 extends through a respective one of the outer liner dilution openings 138 that pass through the outer liner 132. The outer steam injection nozzles 222 extend into the combustion chamber 131, and more specifically, into the dilution zone 135 of the combustion chamber 131. As Figure 10 shown, the outer liner 132 may include more outer liner dilution openings 138 than the number of outer steam injection nozzles 222. Accordingly, at least one outer liner dilution opening 138 may be disposed between a respective pair of the outer steam injection nozzles 222. This arrangement allows the dilution air flow 180 to flow through the outer liner dilution openings 138 through which no outer steam injection nozzle 222 extends. On the other hand, the outer steam injection nozzles 222 may inject the steam 114 or the steam 120 directly into the dilution zone 135, rather than injecting the steam 114 or the steam 120 into the outer air flow passage 160.

[0069] Similarly, the burner 26c includes an inner steam manifold 230 and a plurality of inner steam injection nozzles 234 that are in fluid communication with the inner steam manifold 230, the inner steam manifold 230 having a steam passage 232 therein. The inner steam manifold 230 may also be connected to an inner steam supply line 236 that has a steam passage 238 therein to supply the steam 114 or the steam 120 to the inner steam manifold 230. The inner steam supply line 236 is connected to a steam supply line connector 228 that is connected to the steam supply line 98 ( Figure 2 ) or is connected to the steam supply line 94 ( Figure 2 ). Accordingly, both the outer steam manifold 218 and the inner steam manifold 230 may be supplied with the steam 114 or the steam 120 via a single connection (i.e., via the steam supply line connector 228). Alternatively, the inner steam manifold 230 may include a steam supply line connector 214 as Figure 5 shown, rather than having the inner steam supply line 236.

[0070] Similar to Figure 6 the inner steam manifold 208 shown, Figure 10 the inner steam manifold 230 extends at least partially annularly around the longitudinal centerline axis 12' of the burner and may include a plurality of inner steam manifolds 230, including a first inner steam manifold 230a, a second inner steam manifold 230b, and a third inner steam manifold 230c. Similar to Figure 6 this aspect, the inner steam manifold 230 may alternatively extend annularly around the longitudinal centerline axis 12' of the burner, for example, as shown by the dashed lines connecting the first inner steam manifold 230a to the second inner steam manifold 230b and the dashed lines connecting the first inner steam manifold 230a to the third inner steam manifold 230c.

[0071] As described above Figure 3 As described above, the inner liner 130 includes a plurality of inner liner dilution openings 144 therethrough. Figure 10 A plurality of inner liner dilution openings 144 circumferentially spaced about the longitudinal centerline axis 12' of the burner are depicted. In Figure 9 and Figure 10 Aspects, a respective one of the plurality of inner steam injection nozzles 234 extends through a respective one of the inner liner dilution openings 144 through the inner liner 130. The inner steam injection nozzles 234 extend into the combustion chamber 131, and more particularly, into the dilution zone 135 of the combustion chamber 131. As Figure 10 shown, the inner liner 130 may include more inner liner dilution openings 144 than the number of inner steam injection nozzles 234. Accordingly, at least one inner liner dilution opening 144 may be disposed between a respective pair of the inner steam injection nozzles 234. This arrangement allows the dilution air stream 186 to flow through the inner liner dilution openings 144 through which no inner steam injection nozzle 234 extends. On the other hand, the inner steam injection nozzles 234 may inject the steam 114 or the steam 120 directly into the dilution zone 135, rather than injecting the steam 114 or the steam 120 into the inner gas flow passage 162.

[0072] Although Figure 9 and Figure 10 the burner 26c is depicted as including an outer steam manifold 218 having outer steam injection nozzles 222 and an inner steam manifold 230 having inner steam injection nozzles 234, the burner 26c need not include both. Instead, the burner 26c may include an outer steam manifold 218 having outer steam injection nozzles 222, or an inner steam manifold 230 having inner steam injection nozzles 234. Additionally, the arrangement of the outer steam manifold 218 and the outer steam injection nozzles 222 may be similar to Figure 7 and Figure 8 shown. The arrangement of the inner steam manifold 230 and the inner steam injection nozzles 234 may also be similar to Figure 7 and Figure 8 shown.

[0073] Figure 11 is a partial cross-sectional side view of a burner 26d according to one aspect of the present disclosure, having another alternative arrangement of steam injection nozzles. As Figure 11As shown, combustor 26d includes a steam injection nozzle 240 connected to an outer steam manifold 242, which receives a flow of steam 114 or steam 120 via a steam supply line connector 244 connected to steam supply line 98 or to steam supply line 94. Steam injection nozzle 240 extends through outer gas flow channel 160 and across combustion chamber 131 through outer liner 132, such that one end of steam injection nozzle 240 is adjacent to inner liner 130.

[0074] Figure 12 is captured at detail view 245 according to one aspect of the present disclosure Figure 11 An enlarged cross-sectional detail of the steam injection nozzle 240 is shown. Figure 12 As shown, the outer steam manifold 242 includes a steam passage 246 that receives the flow of steam 114 or 120 from the steam supply line connector 244. The steam injection nozzle 240 also includes a steam passage 248 that receives the flow of steam 114 or 120 from the steam passage 246 of the outer steam manifold 242. The steam injection nozzle 240 has a closed tip 249 and includes a plurality of steam injection ports 250 that provide the flow of steam 114 or 120 from the steam passage 248 into the combustion chamber 131. The steam injection ports 250 are shown as being arranged adjacent to each other so as to be dispersed radially (i.e., in the radial direction R) across the combustion chamber 131 between the outer liner 132 and the inner liner 130, thereby providing a more uniform distribution of steam 114 or 120 in the radial direction R across the combustion chamber 131.

[0075] Figure 13A According to one aspect of the present disclosure Figure 12 A partial cross-sectional view through the steam injection nozzle 240 taken at plane 13-13 of FIG. Figure 13A As shown, the steam injection nozzle 240 may be generally cylindrical in cross-section, similar to Figure 8 The outer steam injection nozzle 204 is shown. The steam injection ports 250 are shown as being arranged to inject steam 114 or steam 120 through the upstream side 252 of the steam injection nozzle 240. For example, the first steam injection port 250a is arranged to inject steam 114 or steam 120 in an upstream direction 254 that is generally opposite to the axial flow direction of the combustion gases 66 within the combustion chamber 131. The second steam injection port 250b is arranged to inject steam 114 or steam 120 in the upstream direction 254 and in a first lateral direction 256, while the third steam injection port 250c is arranged to inject steam 114 or steam 120 in the upstream direction 254 and in a second lateral direction 258. Although Figure 13Ais not shown, but may include additional steam injection ports 250 on the downstream side 260 of the steam injection nozzle 240. Additionally, while the arrangement of the steam injection ports 250 is shown at plane 13-13, a similar arrangement may be achieved at additional planes that match each of the additional radially adjacent steam injection ports 250 shown in Figure 12 the additional planes that match each of the additional radially adjacent steam injection ports 250 shown in

[0076] Figure 13B An alternative arrangement of a cross-section of Figure 13A is depicted in accordance with another aspect of the present disclosure. In Figure 13B this aspect, an alternative steam injection nozzle 240a having a teardrop (or airfoil) shape is shown. The alternative steam injection nozzle 240a includes a plurality of steam injection ports 262 through which a flow of steam 114 or steam 120 is provided from a steam passage 248a into the combustion chamber 131. The steam injection ports 262 may be arranged to provide a flow of steam 114 or steam 120 in different directions. For example, the alternative steam injection nozzle 240a may include a first steam injection port 262a, a second steam injection port 262b, and a third steam injection port 262c, each arranged similarly to Figure 13A the first steam injection port 250a, the second steam injection port 250b, and the third steam injection port 250c of Figure 13B However, the alternative steam injection nozzle 240a may include additional steam injection ports 262, such as a fourth steam injection port 262d, which is arranged to inject steam 114 or steam 120 in a second lateral direction 258. Additionally, one or more fifth steam injection ports 262e ( Figure 13A one is shown in Figure 13B may be arranged through a first sidewall 266 of the alternative steam injection nozzle 240a and may be arranged to inject steam 114 or steam 120 in the second lateral direction 258 and in a downstream direction 264. Additionally, one or more sixth steam injection ports 262f (

[0077] Figure 13C An alternative arrangement of a cross-section of Figure 13A shown in Figure 13CIn one aspect, an alternative steam injection nozzle 240b having an oval (or racetrack) shape is shown. The alternative steam injection nozzle 240b includes a plurality of steam injection ports 270 through which a flow of steam 114 or steam 120 is provided from a steam passage 248b into the combustion chamber 131. The steam injection ports 270 may be arranged to provide a flow of steam 114 or steam 120 in different directions. For example, the alternative steam injection nozzle 240b may include a first steam injection port 270a, a second steam injection port 270b, and a third steam injection port 270c, each arranged similar to Figure 13A the first steam injection port 250a, the second steam injection port 250b, and the third steam injection port 250c. However, the alternative steam injection nozzle 240b may include additional steam injection ports 270, such as one or more fourth steam injection ports 270d, which are arranged through the first sidewall 272 to inject steam 114 or steam 120 in an upstream direction 254 and in a first lateral direction 256. Additionally, one or more fifth steam injection ports 270e may be arranged to pass through the second sidewall 274 of the alternative steam injection nozzle 240b and may be arranged to inject steam 114 or steam 120 in an upstream direction 254 and in a second lateral direction 258. Of course, the steam injection ports 270 may be arranged in any other manner, and the present disclosure is not limited to Figure 13C the arrangement shown.

[0078] Figure 14 is a partial cross-sectional view of a burner 26d taken at plane 14-14 in Figure 11 in accordance with one aspect of the present disclosure. Similar to the Figure 11 aspect and the Figure 6 aspect, Figure 10 the partial cross-section shown in Figure 14 only depicts the upper half (i.e., above the horizontal reference plane 216) of the burner 26d, and the lower half (below the horizontal reference plane 216) may be a mirror image of the upper half. In Figure 14 it is shown that the burner 26d includes a plurality of steam injection nozzles 240, including a first steam injection nozzle 276, a second steam injection nozzle 278, and a third steam injection nozzle 280. Each of the plurality of steam injection nozzles 240 is circumferentially spaced from one another. For example, the first steam injection nozzle 276 may be circumferentially spaced from the second steam injection nozzle 278 by a circumferential angle 282, which may be, for example, sixty degrees. The first steam injection nozzle 276 may also be circumferentially spaced from the third steam injection nozzle 280 by a circumferential angle 284, which may also be sixty degrees. Additionally, in Figure 14 it is shown that the outer steam manifold 242 is an annular steam manifold ( Figure 14(only the upper half above the horizontal reference plane 216 is shown), the steam passage 246 also extends annularly such that the steam 114 or the steam 120 flows annularly therein, and the steam 114 or the steam 120 can be supplied to a plurality of steam injection nozzles 240. The burner 26d may also include a plurality of steam supply line connectors 244, and each steam supply line connector may be connected to the steam supply line 98 or the steam supply line 94. Thus, through Figure 14 this arrangement, the steam 114 or the steam 120 can be circumferentially distributed within the combustion chamber 131.

[0079] The above arrangement injects the steam 114 or the steam 120 into the downstream portion 196 of the outer air flow passage 160 and the downstream portion 198 of the inner air flow passage 162, or directly injects the steam 14 or the steam 120 into the combustion chamber 131, thereby injecting the steam into the secondary combustion zone 137 of the combustion chamber 131. The steam 114 or the steam 120 injected into the outer air flow passage 160 can be mixed with the compressed air 174 in the downstream portion 196, and then, the steam-air mixture 182' can flow through the secondary combustion zone liner opening 140 into the secondary combustion zone 137. Similarly, the steam 114 or the steam 120 injected into the inner air flow passage 162 can be mixed with the compressed air 176 in the downstream portion 198, and then the steam-air mixture 188' can flow through the secondary combustion zone liner opening 146 into the secondary combustion zone 137. In other embodiments, the steam 114 or the steam 120 is directly injected into the secondary combustion zone 137 of the burner 26 such that the steam 114 or the steam 120 can be directly mixed with the combustion gas 66 in the secondary combustion zone 137 without injecting the steam 114 or the steam 120 into the primary combustion zone 133, thereby reducing the possibility of causing a flameout condition within the primary combustion zone 133.

[0080] Although the above description generally relates to a gas turbine engine, the gas turbine engine can be implemented in various environments. For example, the engine can be implemented in an aircraft, but can also be implemented in non-aircraft applications such as power plants, marine applications, or oil and gas production applications. Thus, the present disclosure is not limited to use in an aircraft.

[0081] A further aspect of the present disclosure is provided by the subject matter of the following clauses.

[0082] A gas turbine engine, comprising: a steam generation system that generates steam; and a combustor that includes: a combustor liner including an outer liner and an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween, the combustion chamber having a main combustion zone disposed at an upstream portion of the combustion chamber and a secondary combustion zone disposed downstream of the main combustion zone, at least one of the outer liner or the inner liner including a plurality of secondary combustion zone liner openings therethrough; a housing disposed outside the outer liner, an outer air flow passage being defined between the housing and the outer liner; an inner housing disposed inside the inner liner, an inner air flow passage being defined between the inner housing and the inner liner; and at least one steam injection nozzle that extends through the housing or through the inner housing and, during operation of the gas turbine engine, is arranged to supply a steam flow generated by the steam generation system to the secondary combustion zone of the combustion chamber without supplying the steam to the main combustion zone of the combustion chamber.

[0083] The gas turbine engine according to the preceding clause, wherein the at least one steam injection nozzle includes at least one of an outer steam injection nozzle arranged to pass through the housing or an inner steam injection nozzle arranged to pass through the inner housing.

[0084] The gas turbine engine according to any of the preceding clauses, wherein the inner steam injection nozzle further extends through the inner air flow passage and through the inner liner via one of the plurality of secondary combustion zone liner openings of the inner liner to provide the steam flow directly into the secondary combustion zone.

[0085] The gas turbine engine according to any of the preceding clauses, wherein the plurality of secondary combustion zone liner openings of the inner liner include a plurality of inner liner dilution openings disposed at an upstream end of the secondary combustion zone, and the one secondary combustion zone liner opening of the plurality of secondary combustion zone liner openings of the inner liner constitutes one of the plurality of inner liner dilution openings.

[0086] The gas turbine engine according to any of the preceding clauses, wherein the outer steam injection nozzle is arranged to inject the steam into a downstream portion of the outer air flow passage, and the steam flows from the downstream portion of the outer air flow passage into the secondary combustion zone of the combustion chamber through the plurality of secondary combustion zone liner openings of the outer liner.

[0087] The gas turbine engine according to any of the preceding clauses, wherein the housing includes an outer steam manifold, and the outer steam injection nozzle is in fluid communication with the outer steam manifold.

[0088] A gas turbine engine according to any of the preceding clauses, wherein the airflow within the outer airflow passage flows in a downstream direction, and the outer steam injection nozzle is arranged to direct the steam flow at least partially in an upstream direction.

[0089] A gas turbine engine according to any of the preceding clauses, wherein the inner steam injection nozzle is arranged to inject the steam into a downstream portion of the inner airflow passage, and the steam flows from the downstream portion of the inner airflow passage through the plurality of secondary combustion zone liner openings of the inner liner into the secondary combustion zone of the combustion chamber.

[0090] A gas turbine engine according to any of the preceding clauses, wherein the inner casing includes an inner steam manifold, and the inner steam injection nozzle is in fluid communication with the inner steam manifold.

[0091] A gas turbine engine according to any of the preceding clauses, wherein the airflow within the inner airflow passage flows in a downstream direction, and the inner steam injection nozzle is arranged to direct the steam flow at least partially in an upstream direction.

[0092] A gas turbine engine according to any of the preceding clauses, wherein the outer steam injection nozzle further extends through the outer airflow passage and through the outer liner via one of the plurality of secondary combustion zone liner openings of the outer liner to provide a steam flow directly into the secondary combustion zone.

[0093] A gas turbine engine according to any of the preceding clauses, wherein the plurality of secondary combustion zone liner openings of the outer liner include a plurality of outer liner dilution openings arranged at an upstream end of the secondary combustion zone, and the one secondary combustion zone liner opening of the plurality of secondary combustion zone liner openings of the outer liner constitutes one of the plurality of outer liner dilution openings.

[0094] A gas turbine engine according to any of the preceding clauses, wherein the outer steam injection nozzle extends across the secondary combustion zone of the combustion chamber between the outer liner and the inner liner.

[0095] A gas turbine engine according to any of the preceding clauses, wherein the outer steam injection nozzle includes a plurality of steam injection ports arranged to inject the steam in an upstream direction or in the upstream direction and in a lateral direction relative to the axial flow direction within the combustion chamber.

[0096] A gas turbine engine according to any of the preceding clauses, wherein (a) the plurality of secondary combustion zone liner openings through the outer liner include a plurality of outer liner dilution openings arranged to pass through the outer liner at an upstream end of the secondary combustion zone and circumferentially spaced from each other about a longitudinal centerline axis of the burner, (b) the outer casing includes an outer steam manifold extending at least partially annularly about the longitudinal centerline axis of the burner, and (c) the outer steam injection nozzles include a plurality of outer steam injection nozzles in fluid communication with the outer steam manifold, with respective ones of the plurality of outer steam injection nozzles extending through respective ones of the plurality of outer liner dilution openings.

[0097] A gas turbine engine according to any of the preceding clauses, wherein between respective pairs of the plurality of outer steam injection nozzles, at least one of the plurality of outer liner dilution openings is arranged to have no steam injection nozzle passing therethrough so as to provide a dilution air flow through the outer liner into the secondary combustion zone of the combustion chamber.

[0098] A gas turbine engine according to any of the preceding clauses, wherein (d) the plurality of secondary combustion zone liner openings through the inner liner include a plurality of inner liner dilution openings arranged to pass through the inner liner at an upstream end of the secondary combustion zone and circumferentially spaced from each other about the longitudinal centerline axis of the burner, (e) the inner casing includes an inner steam manifold extending at least partially annularly about the longitudinal centerline axis of the burner, and (f) the inner steam injection nozzles include a plurality of inner steam injection nozzles in fluid communication with the inner steam manifold, with respective ones of the plurality of inner steam injection nozzles extending through respective ones of the plurality of inner liner dilution openings.

[0099] A gas turbine engine according to any of the preceding clauses, further comprising an outer steam supply line in fluid communication with the outer steam manifold and an inner steam supply line in fluid communication with the inner steam manifold, the outer steam supply line and the inner steam supply line being connected to a steam supply line connector in fluid communication with a steam generation system so as to supply the steam flow to the outer steam manifold and the inner steam manifold.

[0100] A gas turbine engine according to any of the preceding clauses, wherein the plurality of outer steam injection nozzles extend through the outer liner into the secondary combustion zone of the combustion chamber.

[0101] A gas turbine engine according to any of the preceding clauses, wherein at least one of the plurality of outer steam injection nozzles includes a steam passage therein and a closed tip having a plurality of steam injection ports, the plurality of steam injection ports providing a steam flow from the steam passage, and corresponding ones of the plurality of steam injection ports being arranged to direct the steam flow in any one of an upstream direction, a downstream direction, or a lateral direction relative to an axial flow direction in the combustion chamber.

[0102] A gas turbine engine according to any of the preceding clauses, wherein the steam injection nozzle includes a steam passage therein.

[0103] A gas turbine engine according to any of the preceding clauses, wherein the steam injection nozzle has a circular cross-sectional shape and the steam passage has a circular cross-sectional shape.

[0104] A gas turbine engine according to any of the preceding clauses, wherein the steam injection nozzle has a teardrop cross-sectional shape or an airfoil cross-sectional shape, and the steam passage has a teardrop cross-sectional shape or an airfoil cross-sectional shape.

[0105] A gas turbine engine according to any of the preceding clauses, wherein the steam injection nozzle has a racetrack cross-sectional shape or an oval cross-sectional shape, and the steam passage has a racetrack cross-sectional shape or an oval cross-sectional shape.

[0106] A burner for a gas turbine engine, the gas turbine engine comprising: a steam generation system to provide steam to the burner; a burner including: a burner liner including an outer liner and an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween, the combustion chamber having a main combustion zone disposed at an upstream portion of the combustion chamber and a secondary combustion zone disposed downstream of the main combustion zone, at least one of the outer liner or the inner liner including a plurality of secondary combustion zone liner openings therethrough; an outer housing disposed outside the outer liner, an outer gas flow passage being defined between the outer housing and the outer liner; an inner housing disposed inside the inner liner, an inner gas flow passage being defined between the inner housing and the inner liner; and at least one steam injection nozzle extending through the outer housing or extending through the inner housing and, during operation of the gas turbine engine, arranged to provide a steam flow generated by the steam generation system to the secondary combustion zone of the combustion chamber without providing the steam to the main combustion zone of the combustion chamber.

[0107] The burner according to the preceding clause, wherein the at least one steam injection nozzle includes at least one of an outer steam injection nozzle arranged to pass through the outer housing or an inner steam injection nozzle arranged to pass through the inner housing.

[0108] The burner according to any of the preceding clauses, wherein the inner steam injection nozzle further extends through the inner gas flow channel and through the inner lining sleeve via one of the plurality of secondary combustion zone lining sleeve openings of the inner lining sleeve to provide a steam flow directly into the secondary combustion zone.

[0109] The burner according to any of the preceding clauses, wherein the plurality of secondary combustion zone lining sleeve openings of the inner lining sleeve include a plurality of inner lining sleeve dilution openings arranged at the upstream end of the secondary combustion zone, and the one secondary combustion zone lining sleeve opening among the plurality of secondary combustion zone lining sleeve openings of the inner lining sleeve constitutes one of the plurality of inner lining sleeve dilution openings.

[0110] The burner according to any of the preceding clauses, wherein the outer steam injection nozzle is arranged to inject the steam into a downstream portion of the outer gas flow channel, and the steam flows from the downstream portion of the outer gas flow channel into the secondary combustion zone of the combustion chamber through the plurality of secondary combustion zone lining sleeve openings of the outer lining sleeve.

[0111] The burner according to any of the preceding clauses, wherein the outer housing includes an outer steam manifold, and the outer steam injection nozzle is in fluid communication with the outer steam manifold.

[0112] The burner according to any of the preceding clauses, wherein the gas flow in the outer gas flow channel flows in the downstream direction, and the outer steam injection nozzle is arranged to guide the steam flow at least partially in the upstream direction.

[0113] The burner according to any of the preceding clauses, wherein the inner steam injection nozzle is arranged to inject the steam into a downstream portion of the inner gas flow channel, and the steam flows from the downstream portion of the inner gas flow channel into the secondary combustion zone of the combustion chamber through the plurality of secondary combustion zone lining sleeve openings of the inner lining sleeve.

[0114] The burner according to any of the preceding clauses, wherein the inner housing includes an inner steam manifold, and the inner steam injection nozzle is in fluid communication with the inner steam manifold.

[0115] The burner according to any of the preceding clauses, wherein the gas flow in the inner gas flow channel flows in the downstream direction, and the inner steam injection nozzle is arranged to guide the steam flow at least partially in the upstream direction.

[0116] The burner according to any of the preceding clauses, wherein the outer steam injection nozzle further extends through the outer gas flow passage and through the outer liner via one of the plurality of secondary combustion zone liner openings of the outer liner to provide a steam flow directly into the secondary combustion zone.

[0117] The burner according to any of the preceding clauses, wherein the plurality of secondary combustion zone liner openings of the outer liner include a plurality of outer liner dilution openings arranged at an upstream end of the secondary combustion zone, and the one secondary combustion zone liner opening among the plurality of secondary combustion zone liner openings of the outer liner constitutes one of the plurality of outer liner dilution openings.

[0118] The burner according to any of the preceding clauses, wherein the outer steam injection nozzle extends across the secondary combustion zone of the combustion chamber between the outer liner and the inner liner.

[0119] The burner according to any of the preceding clauses, wherein the outer steam injection nozzle includes a plurality of steam injection ports arranged to inject the steam in an upstream direction or in the upstream direction and in a transverse direction with respect to the axial flow direction in the combustion chamber.

[0120] The burner according to any of the preceding clauses, wherein (a) the plurality of secondary combustion zone liner openings through the outer liner include a plurality of outer liner dilution openings arranged to pass through the outer liner at an upstream end of the secondary combustion zone and circumferentially spaced apart from each other about the longitudinal centerline axis of the burner, (b) the outer housing includes an outer steam manifold extending at least partially annularly about the longitudinal centerline axis of the burner, and (c) the outer steam injection nozzle includes a plurality of outer steam injection nozzles in fluid communication with the outer steam manifold, and a respective one of the plurality of outer steam injection nozzles extends through a respective one of the plurality of outer liner dilution openings.

[0121] The burner according to any of the preceding clauses, wherein between a respective pair of the plurality of outer steam injection nozzles, at least one of the plurality of outer liner dilution openings is arranged such that no steam injection nozzle passes therethrough to provide a dilution air flow through the outer liner into the secondary combustion zone of the combustion chamber.

[0122] The burner according to any of the preceding clauses, wherein (d) the plurality of secondary combustion zone liner openings through the inner liner include a plurality of inner liner dilution openings arranged to pass through the inner liner at the upstream end of the secondary combustion zone and circumferentially spaced from each other about the longitudinal centerline axis of the burner, (e) the inner housing includes an inner steam manifold extending at least partially annularly about the longitudinal centerline axis of the burner, and (f) the inner steam injection nozzles include a plurality of inner steam injection nozzles in fluid communication with the inner steam manifold, and respective ones of the plurality of inner steam injection nozzles extend through respective ones of the plurality of inner liner dilution openings.

[0123] The burner according to any of the preceding clauses further includes an outer steam supply line in fluid communication with the outer steam manifold and an inner steam supply line in fluid communication with the inner steam manifold, the outer steam supply line and the inner steam supply line being connected to a steam supply line connector in fluid communication with the steam generation system so as to provide the steam flow to the outer steam manifold and the inner steam manifold.

[0124] The burner according to any of the preceding clauses, wherein the plurality of outer steam injection nozzles extend through the outer liner into the secondary combustion zone of the combustion chamber.

[0125] The burner according to any of the preceding clauses, wherein at least one of the plurality of outer steam injection nozzles includes a steam passage therein and a closed tip having a plurality of steam injection ports for providing a steam flow from the steam passage, and respective ones of the plurality of steam injection ports are arranged to direct the steam flow in any one of an upstream direction, a downstream direction, or a lateral direction relative to the axial flow direction in the combustion chamber.

[0126] The burner according to any of the preceding clauses, wherein the steam injection nozzle includes a steam passage therein.

[0127] The burner according to any of the preceding clauses, wherein the steam injection nozzle has a circular cross-sectional shape and the steam passage has a circular cross-sectional shape.

[0128] The burner according to any of the preceding clauses, wherein the steam injection nozzle has a teardrop cross-sectional shape or an airfoil cross-sectional shape, and the steam passage has a teardrop cross-sectional shape or an airfoil cross-sectional shape.

[0129] The burner according to any of the preceding clauses, wherein the steam injection nozzle has a racetrack cross-sectional shape or an oval cross-sectional shape, and the steam passage has a racetrack cross-sectional shape or an oval cross-sectional shape.

[0130] Although the above description is directed to some exemplary embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and these variations and modifications may be made without departing from the present disclosure. Additionally, even if not explicitly stated above, the features described in connection with one embodiment of the present disclosure may be used in combination with other embodiments.

Claims

1. A gas turbine engine, characterized in that: Comprising: A steam generation system that generates steam; And A burner, the burner comprising: A burner liner, the burner liner including an outer liner and an inner liner, the outer liner and the inner liner defining a combustion chamber therebetween, the combustion chamber having a main combustion zone disposed at an upstream portion of the combustion chamber and a secondary combustion zone disposed downstream of the main combustion zone, at least one of the outer liner or the inner liner including a plurality of secondary combustion zone liner openings therethrough; An outer housing disposed outside the outer liner, an outer gas flow passage being defined between the outer housing and the outer liner; An inner housing disposed inside the inner liner, an inner gas flow passage being defined between the inner housing and the inner liner; And At least one steam injection nozzle that extends through the outer housing or through the inner housing and, during operation of the gas turbine engine, is arranged to supply a steam flow generated by the steam generation system to the secondary combustion zone of the combustion chamber without supplying the steam to the main combustion zone of the combustion chamber.

2. The gas turbine engine according to claim 1, wherein: Wherein the at least one steam injection nozzle includes at least one of an outer steam injection nozzle arranged to pass through the outer housing or an inner steam injection nozzle arranged to pass through the inner housing.

3. The gas turbine engine according to claim 2, characterized in that, Wherein the inner steam injection nozzle further extends through the inner gas flow passage and through the inner liner via one of the plurality of secondary combustion zone liner openings of the inner liner to provide the steam flow directly into the secondary combustion zone.

4. The gas turbine engine according to claim 3, characterized in that, Wherein the plurality of secondary combustion zone liner openings of the inner liner include a plurality of inner liner dilution openings disposed at an upstream end of the secondary combustion zone, and the one secondary combustion zone liner opening of the plurality of secondary combustion zone liner openings of the inner liner constitutes one of the plurality of inner liner dilution openings.

5. The gas turbine engine according to claim 2, characterized in that, Wherein the outer steam injection nozzle is arranged to inject the steam into a downstream portion of the outer gas flow passage, and the steam flows from the downstream portion of the outer gas flow passage into the secondary combustion zone of the combustion chamber through the plurality of secondary combustion zone liner openings of the outer liner.

6. The gas turbine engine according to claim 5, wherein Wherein the outer housing includes an outer steam manifold, and the outer steam injection nozzle is in fluid communication with the outer steam manifold.

7. The gas turbine engine according to claim 5, characterized in that, Wherein the gas flow in the outer gas flow passage flows in a downstream direction, and the outer steam injection nozzle is arranged to at least partially direct the steam flow in an upstream direction.

8. The gas turbine engine according to claim 2, characterized in that, Wherein the inner steam injection nozzle is arranged to inject the steam into a downstream portion of the inner gas flow passage, and the steam flows from the downstream portion of the inner gas flow passage into the secondary combustion zone of the combustion chamber through the plurality of secondary combustion zone liner openings of the inner liner.

9. The gas turbine engine according to claim 8, wherein, Wherein the inner housing includes an inner steam manifold, and the inner steam injection nozzle is in fluid communication with the inner steam manifold.

10. The gas turbine engine according to claim 8, characterized in that, Wherein the gas flow in the inner gas flow passage flows in a downstream direction, and the inner steam injection nozzle is arranged to at least partially direct the steam flow in an upstream direction.

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