Turbine engine comprising fuel and steam system

Abstract

A turbine engine has a combustor in a core air flow path, the combustor generating combustion gases; and a fuel and steam system fluidly coupled to the combustor. The fuel and steam system has a steam system for providing a stream of steam to the burner; and a fuel system for providing a primary fuel stream and a secondary fuel stream to the combustor. The fuel system has a first state in which the flow of secondary fuel to the combustor has a first flow rate and a second state in which the flow of secondary fuel to the combustor has a second flow rate. The first flow rate and the second flow rate are different. The first state and the second state are based on conditions of the steam system.

Description

Technical Field

[0001] The present disclosure relates generally to fuel and steam systems, such as fuel and steam systems for turbine engines. Background Art

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

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

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

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

[0006] Figure 3 A schematic diagram of a fuel and steam system of a turbine engine according to the present disclosure is shown.

[0007] Figure 4 A schematic diagram of a fuel and steam system of a turbine engine according to the present disclosure is shown.

[0008] Figure 5 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a longitudinal centerline axis of the combustor.

[0009] Figure 6 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a longitudinal centerline axis of the combustor.

[0010] Figure 7 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a radial plane extending through a dilution opening of the combustor.

[0011] Figure 8 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a longitudinal centerline axis of the combustor.

[0012] Fig. 9 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a longitudinal centerline axis of the combustor.

[0013] Fig.10 A schematic cross-sectional view of a combustor of a turbine engine according to the present disclosure is shown, taken along a longitudinal centerline axis of the combustor.

[0014] Fig.11 A method of operating a turbine engine having a fuel and steam system according to the present disclosure is shown. DETAILED DESCRIPTION

[0015] Features, advantages and embodiments of the present disclosure are set forth or apparent through consideration of the following detailed description, drawings and claims.In addition, the following detailed description is exemplary and is intended to provide further explanation without limiting the scope of the present disclosure as claimed.

[0016] Various embodiments of the present disclosure are discussed in detail below. Although specific embodiments are discussed, this is for illustrative purposes only. Those skilled in the relevant art will recognize that other components and configurations may be used without departing from the spirit and scope of the present disclosure.

[0017] As used herein, the terms “first”, “second”, and the like may be used interchangeably to distinguish one component from another, and are not intended to indicate the position or importance of each component.

[0018] The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, while "downstream" refers to the direction to which the fluid is flowing.

[0019] The terms "front" and "rear" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, for a turbine engine, front refers to a position closer to the engine inlet, while rear refers to a position closer to the engine nozzle or exhaust.

[0020] As used herein, the terms "low," "medium" (or "medium level"), and "high," or their respective comparatives (e.g., "lower" and "higher," where applicable), when used with a compressor, turbine, shaft, fan, or turbine engine component, refer to relative pressures, relative speeds, relative temperatures, and / or relative power outputs within an engine, unless otherwise indicated. For example, a "low power" setting defines an engine configured to operate at a power output lower than a "high power" setting for the engine, while a "medium level power" setting defines an engine configured to operate at a power output higher than the "low power" setting and lower than the "high power" setting. The terms "low," "medium" (or "medium level"), or "high" in the above terms may additionally or alternatively be understood as relative to a minimum allowable speed, pressure, or temperature, or relative to a minimum or maximum allowable speed, pressure, or temperature for normal, desired, steady state, etc., operation of the engine.

[0021] The terms "coupled," "fixed," "attached," "connected," and the like refer to both direct coupling, fixing, attachment, or connection and indirect coupling, fixing, attachment, or connection through one or more intermediate components or features, unless otherwise specified herein. These terms include integral and unitary configurations (e.g., a blisk rotor blade system).

[0022] The singular forms "a," "an," and "the" include plural referents unless the context clearly dictates otherwise.

[0023] As used herein, the terms "axial" and "axially" refer to directions and orientations extending substantially parallel to the centerline of the turbine engine. Additionally, the terms "radial" and "radially" refer to directions and orientations extending substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to directions and orientations extending in an arc around the centerline of the turbine engine.

[0024] As used herein throughout the specification and claims, approximate language is used to modify any quantitative representation that can be allowed to vary without causing a change in the basic function associated therewith. Therefore, the value modified by one or more terms (such as "approximately", "approximately", "roughly" and "substantially") is not limited to the specified precise value. In at least some cases, approximate language can correspond to the accuracy of the instrument used to measure the value, or the accuracy of the method or machine used to construct a component or system or manufacture a component or system. For example, approximate language can refer to a single value, a range of values, or an endpoint of a range of values ​​that is limited to one percent, two percent, four percent, ten percent, fifteen percent, or twenty percent margin.

[0025] 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 subranges contained therein. For example, all ranges disclosed herein include the endpoints, and the endpoints can be independently combined with each other.

[0026] The present disclosure provides a fuel and steam system for injecting fuel and steam into a combustor of a turbine engine. In an engine that injects steam into the core of the combustor (e.g., steam recovered from engine exhaust or steam provided from a steam source or water source), specific fuel consumption (SPC) increases compared to an engine without steam injection. To achieve SPC benefits, a large amount of steam (e.g., about 20 to 60 percent steam to air ratio) can be injected into the core of the combustor.

[0027] In such an engine with steam injection, partial or total steam loss may result in engine power loss. To offset this power loss, the present disclosure provides a secondary fuel injection introduced into the burner at the front end of the burner downstream of the primary fuel injection. Fuel is controlled to be selectively injected into the burner based on conditions of the steam system providing the steam flow, based on engine operating conditions or power conditions, or both.

[0028] Therefore, the fuel and steam system of the present disclosure can introduce fuel and steam into the combustor in the form of a combined fuel-steam flow, or can introduce separate fuel and steam flows. In some examples, both the fuel flow and the steam flow are injected into the secondary zone of the combustor. In some examples, the fuel flow is injected into the primary zone of the combustor, and the steam is injected into the secondary zone of the combustion chamber. In some examples, air can be introduced together with the fuel flow and the steam flow through the air opening or through an additional swirler provided in the combustor liner.

[0029] As described above, the present disclosure provides controlled injection of fuel flow to a combustor based on the steam condition of the engine. In the event of a partial or complete loss of steam flow into the combustor, fuel may be injected into the primary or secondary zone of the combustor to restore the power loss caused by the steam loss. The fuel and steam system of the present disclosure includes a controller that determines engine power loss, steam pressure loss, or both, and then controls the fuel system so that fuel may be injected to increase power to achieve a desired power level and thrust level.

[0030] As will be described in more detail below, the steam and fuel system of the present disclosure may include an injector or nozzle with independent steam and fuel circuits to inject steam when the steam system is operating normally (e.g., operating within predefined parameters) and to inject fuel when steam flow is lost. In some examples, the steam flow and the fuel flow may be mixed in a mixing device and then injected into the burner as a separate mixture of fuel and steam. The fuel and steam system of the present disclosure may include steam and fuel injected under all operating conditions to obtain additional NO x In such an example, the steam and fuel may be injected through separate circuits, or may be mixed and injected together as a combined stream to the combustor.

[0031] In some examples, the steam and fuel system of the present disclosure may inject steam and fuel at different axial positions so that the high temperature generated after the secondary fuel is injected can be reduced by the steam flow. In some examples, the steam and fuel system of the present disclosure may include steam and fuel injected at different circumferential positions so that steam can be injected in a high temperature area and fuel can be directed to be injected in a low temperature area.

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

[0033] The illustrated turbocharger engine 16 generally includes an outer casing 18 that is substantially tubular and defines an annular inlet 20. Figure 1 As schematically shown in FIG. 1 , the outer casing 18 encloses, in serial flow relationship: a compressor section 22, which includes a supercharger or low pressure (LP) compressor 24, followed immediately downstream by a high pressure (HP) compressor 26; a combustion section 28; a turbine section 30, which includes a high pressure (HP) turbine 32, followed immediately downstream by a low pressure (LP) turbine 34; and an injection exhaust nozzle section 36. Thus, the turbocharged engine 16 includes the compressor section 22, the combustion section 28, and the turbine section 30 and components thereof. A high pressure (HP) shaft 38 or spool drives the HP turbine 32 to the HP compressor 26 so that the HP turbine 32 and the HP compressor 26 rotate in unison. A low pressure (LP) shaft 40 drives the LP turbine 34 to the LP compressor 24 so that the LP turbine 34 and the LP compressor 24 rotate in unison. The compressor section 22, the combustion section 28, the turbine section 30, and the injection exhaust nozzle section 36 together define a core air flow path.

[0034] for Figure 1 In the illustrated embodiment, fan section 14 includes a fan 42 (eg, a variable pitch fan) having a plurality of fan blades 44 coupled to a disk 46 in a spaced-apart manner. Figure 1 As shown, fan blades 44 extend outwardly from disk 46 generally in radial direction R. Each fan blade 44 is rotatable relative to disk 46 about pitch axis P by virtue of fan blades 44 being operably coupled to actuating member 48, which is configured to collectively and uniformly change the pitch of fan blades 44. Fan blades 44, disk 46, and actuating member 48 are rotatable together about longitudinal centerline axis 12 via fan shaft 50, which is powered by LP shaft 40 across a power gearbox (also referred to as gearbox assembly 52). Gearbox assembly 52 is Figure 1 The gearbox assembly 52 includes a plurality of gears for adjusting the rotational speed of the fan shaft 50 , thereby adjusting the rotational speed of the fan 42 relative to the LP shaft 40 .

[0035] Still refer to Figure 1In an exemplary embodiment of the present invention, disk 46 is covered by a rotatable fan hub 54 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 44. In addition, fan section 14 includes an annular fan casing or nacelle 56 that circumferentially surrounds fan 42 and at least a portion of turbocharger engine 16. Nacelle 56 is supported relative to turbocharger engine 16 by a plurality of circumferentially spaced outlet guide vanes 58. In addition, a downstream section 60 of nacelle 56 extends over an outer portion of turbocharger engine 16, thereby defining a bypass airflow passage 62 therebetween.

[0036] During operation of the turbine engine 10, a volume of air 64 enters the turbine engine 10 through the nacelle 56 or the inlet 60 of the fan section 14. As the volume of air 64 passes through the fan blades 44, a first portion of air 68 is directed or directed to the bypass airflow passage 62, while a second portion of air 70 is directed or directed to an upstream section of the core air flow path, or more specifically, to the annular inlet 20 of the LP compressor 24. The ratio between the first portion of air 68 and the second portion of air 70 is generally referred to as a bypass ratio. The pressure of the second portion of air 70 is then increased, producing compressed air 72, which is directed through the HP compressor 26 and into the combustion section 28. The combustor of the combustion section 28 is positioned in the core air flow path, where the compressed air 72 is mixed with a fuel flow and combusted to produce combustion gases 74. As described in more detail below, the fuel flow may be a primary fuel flow provided to the combustor.

[0037] The combustion gases 74 are directed to and expanded through the HP turbine 32, wherein a portion of the heat and kinetic energy from the combustion gases 74 is extracted via successive stages of HP turbine stator blades 76 coupled to the outer casing 18 and HP turbine rotor blades 78 coupled to the HP shaft 38, thereby rotating the HP shaft 38, thereby supporting operation of the HP compressor 26. The combustion gases 74 are then directed to and expanded through the LP turbine 34. Here, a second portion of the heat and kinetic energy is extracted from the combustion gases 74 via successive stages of LP turbine stator blades 80 coupled to the outer casing 18 and LP turbine rotor blades 82 coupled to the LP shaft 40, thereby rotating the LP shaft 40, thereby supporting operation of the LP compressor 24 and supporting rotation of the fan 42 via the gearbox assembly 52.

[0038] The combustion gases 74 are then directed through the jet exhaust nozzle section 36 of the turbocharger engine 16 to provide propulsive thrust. At the same time, the pressure of the first portion of air 68 increases significantly as it is directed through the bypass airflow passage 62 and then discharged from the fan nozzle exhaust section 84 of the turbine engine 10, also providing propulsive thrust. The HP turbine 32, the LP turbine 34, and the jet exhaust nozzle section 36 at least partially define a hot gas path 86 for directing the combustion gases 74 through the turbocharger engine 16.

[0039] The turbine engine 10 includes a fuel and steam system 100. The fuel and steam system 100 is fluidly coupled to a combustor of a combustion section 28. The fuel and steam system 100 includes a fuel system 102 and a steam system 104. The fuel system 102 provides a fuel flow to the combustion section 28 to produce combustion gases 74. The fuel system 102 includes a fuel tank or fuel supply for storing fuel therein, a fuel supply line 106, and a fuel injector 108. The fuel flow is provided from the fuel tank along the fuel supply line 106 to the fuel injector 108, and the fuel injector 108 introduces the fuel flow into the combustion section 28. The fuel system 102 may include one or more flow control devices or valves along the fuel supply line 106 for controlling the amount of fuel provided to the combustion section 28.

[0040] The fuel injector 108 is disposed at the front end of the burner (not shown) of the combustion section 28, as will be described in more detail below. Thus, the fuel provided along the fuel supply line 106 is provided at the front end of the burner of the combustion section 28. The fuel system 102 includes a fuel supply line 110 to provide a fuel flow to the combustion section 28 downstream of the fuel flow provided by the fuel supply line 106. Thus, the fuel supply line 106 may be referred to as a primary fuel supply line 106, and the fuel supply line 110 may be referred to as a secondary fuel supply line 110. The fuel flow from the fuel supply line 110 may be provided to the combustion section 28 together with a steam flow provided along a steam supply line 112 of the steam system 104. The combined fuel and steam flow (referred to herein as a fuel-steam flow) may be provided to a fuel-steam injector 116 along a fuel-steam supply line 114, and the fuel-steam injector 116 introduces the fuel-steam flow into the combustion section 28 downstream of the fuel injector 108.

[0041] In some examples, fuel and steam are injected simultaneously such that the flow along fuel-steam supply line 114 is a combined mixture of fuel (from fuel supply line 110 ) and steam (from steam supply line 112 ) introduced to the combustor.

[0042] In other examples, during normal operating conditions of the engine (e.g., when the steam pressure is within a predetermined value or range), no fuel is provided along fuel supply line 110, and steam is only provided along steam supply line 112 and along fuel-steam supply line 114 to fuel-steam injectors 116. In this case, when the engine experiences a partial or complete loss of steam flow, fuel flow along fuel supply line 110 is directed to the combustor, as described with respect to Figure 3 When fuel is injected into the combustor in this example, the flow through the fuel-steam supply line 114 may be fuel only (in the event of a total loss of steam flow) or may be a combined mixture of fuel and steam (in the event of a partial loss of steam flow).

[0043] However, in both of the above examples, fuel is supplied to the combustor via the primary fuel supply line 106 under all operating conditions to provide primary combustion within the combustor.

[0044] Figure 2 Shows Figure 1 1 is a schematic cross-sectional view of a turbine engine 10 having another exemplary fuel and steam system 200. The fuel and steam system 200 is similar to the fuel and steam system 100, except that the fuel and steam flows are separately introduced into the combustion section 28, as described below.

[0045] The fuel and steam system 200 includes a fuel system 202 including a fuel tank or fuel supply for storing fuel therein, a fuel supply line 206, and a fuel injector 208. The fuel system 202 provides a fuel flow along the fuel supply line 206, through the fuel injector 208, and into the combustion section 28 to generate the combustion gases 74, as described with reference to FIG. Figure 1 The fuel system 202 may include one or more valves or flow control devices along a fuel supply line 206 for controlling the amount of fuel provided to the combustion section 28. The fuel injector 208 is disposed at a front end of a burner (not shown) of the combustion section 28. Thus, the fuel provided along the fuel supply line 206 is provided at a front end of the burner of the combustion section 28.

[0046] The fuel system 202 includes a fuel supply line 210 to provide a fuel flow to the combustion section 28 downstream of the fuel flow provided by the fuel supply line 206. Therefore, the fuel supply line 206 may be referred to as a primary fuel supply line 206, and the fuel supply line 210 may be referred to as a secondary fuel supply line 210. The fuel flow from the fuel supply line 210 may be provided to the combustion section 28 via a fuel injector 216. Therefore, the fuel injector 208 may be referred to as a primary fuel injector 208, and the fuel injector 216 may be referred to as a secondary fuel injector 216.

[0047] The fuel and steam system 200 includes a steam system 204 that provides steam along a steam supply line 212 to a steam injector 218 and into the combustion section 28. The steam system 204 introduces steam into the combustion section 28 downstream of the fuel injector 208.

[0048] By the fuel system 102 ( Figure 1 ) and fuel system 202( Figure 2 The fuel provided by the turbine engine may be any type of fuel for a turbine engine, including liquid fuel or gaseous fuel. For example, the fuel may be JetA, sustainable aviation fuel (SAF) including biofuel, hydrogen-based fuel (H 2 ), etc., or a combination thereof.

[0049] By steam system 104 ( Figure 1 ) and steam system 204( Figure 2 ) The steam provided by the turbine engine 10 may come from a discrete steam source (e.g., a separate steam source and / or a water source converted to steam). Alternatively or additionally, the steam may be provided by the steam system 104 and the steam system 204 that generate steam from the exhaust of the turbine engine 10. That is, for example, the steam system 104 and the steam system 204 may include a heat recovery system in fluid communication with any component of the turbocharger engine 16, the injection exhaust nozzle section 36, or any combination thereof. In such an example, the steam system 104 and the steam system 204 extract steam from the turbine engine 10 and inject the steam into the combustion section 28 along the steam supply line 112 and the steam supply line 212, respectively.

[0050] In some examples, the fuel and steam are injected simultaneously such that flow along fuel supply line 210 and steam along steam supply line 212 are introduced into the combustor simultaneously.

[0051] In other examples, during normal operating conditions of the engine (e.g., when the steam pressure is within a predetermined value or range), fuel is not provided along fuel supply line 210 and fuel injector 216, and steam is provided only along steam supply line to steam injector 218. In this case, when the engine experiences a partial or complete loss of steam flow, fuel flow along fuel supply line 210 is directed to the combustor, as described with respect to Figure 3 and Figure 4 In this example, when fuel is injected into the combustor, flow through the steam supply line 212 may not occur (in the case of a total loss of steam flow) or may be reduced compared to normal operating conditions (in the case of a partial loss of steam flow).

[0052] However, in both of the above examples, fuel is supplied to the combustor via the primary fuel supply line 206 under all operating conditions to provide primary combustion within the combustor.

[0053] Figure 1 and Figure 2 The turbine engine 10 shown in is only by way of example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 42 may be configured in any other suitable manner (e.g., as a fixed pitch fan), and may also be supported using any other suitable fan frame configuration. In addition, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, aspects of the present disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, a propfan engine, a turbojet engine, a turboprop engine, or a turboshaft engine.

[0054] therefore, Figure 1 and Figure 2 A turbine engine 10 is shown that includes fuel injection and steam injection to a combustion section 28 of the turbine engine 10. The fuel injection includes primary fuel injection (e.g., fuel injection to the combustion section 28) and secondary fuel injection (e.g., fuel injection downstream of the primary fuel injection). The secondary fuel injection is combined with the steam injection. Figure 1 In the example of , the secondary fuel injection is combined with the steam injection before being injected into the combustion section 28. Figure 2 In the example of FIG. 2 , secondary fuel injection is combined with steam injection at or within the combustion section 28 . Figure 3 and Figure 4 It shows that it is possible to realize Figure 1 and Figure 2 Schematic diagrams of fuel and steam systems 100 and 200 are depicted.

[0055] Reference now Figure 3 , the fuel and steam system 300 may be used with respect to Figure 1 The fuel and steam system 100 is depicted to enable fuel and steam injection within the combustion section 28 of the turbine engine 10. The fuel and steam system 300 includes a fuel system 302 and a steam system 304.

[0056] The fuel system 302 includes a fuel supply line 306 and a fuel injector 308. The fuel injector 308 (schematically shown) introduces a fuel flow from the fuel supply line 306 to the primary zone 28a of the burner of the combustion section 28. As will be described in more detail below, the primary zone 28a is defined between the front end of the burner of the combustion section 28 and the dilution opening (not shown) in the wall of the burner. The fuel system 302 includes a fuel supply line 310 for introducing a fuel flow to the secondary zone 28b of the burner of the combustion section 28. As will be described in more detail below, the secondary zone 28b is defined between the dilution opening (not shown) and the far end of the burner. The fuel supply line 310 includes a fuel flow control device 320 for controlling the fuel flow from the fuel system (e.g., from a fuel tank) to the secondary zone 28b. That is, the fuel flow control device 320 can control the rate, volume, on / off properties or a combination thereof of the fuel flow along the fuel supply line 310. In some examples, fuel flow control device 320 is a valve.

[0057] Prior to injection into the secondary zone 28b, the fuel flow along the fuel supply line 310 is combined with a steam flow from a steam supply line 312 (from the steam system 304). The combined fuel and steam flows form a fuel-steam flow along a fuel-steam supply line 314. The fuel-steam flow is introduced from the fuel-steam supply line 314 into the secondary zone 28b via a fuel-steam injector 316 (schematically shown).

[0058] As previously described, the steam system 304 may include a heat recovery system 322 to recover some energy from the waste heat of the exhaust. The steam system 304 recovers energy by generating steam to drive a steam turbine 324, which inputs additional work to the LP turbine 34 via a flow path 326. The heat recovery system 322 can capture steam from the injection exhaust nozzle section 36 along a flow path 328. The heat recovery system 322 can provide steam to the steam turbine 324 along a flow path 330. Therefore, after flowing through the steam turbine 324, the steam can be injected into the burner of the combustion section 28 via a steam supply line 312. The heat recovery system 322, the steam turbine 324, or both are optional and can be omitted. When omitted, the steam system 304 includes another steam source for supplying steam along the steam supply line 312.

[0059] The fuel and steam system 300 includes a sensor system 332 and a controller, such as an engine controller 334. The sensor system 332 is arranged to sense the pressure at the outlet of the LP turbine 34, as shown by sensor line 336, and is arranged to sense the pressure of the steam supply line 312, as shown by sensor line 338. Sensor line 336 and sensor line 338 are data or communication lines and represent the sensor system 332 monitoring the pressure at various points. In some examples, the sensor system 332 may include a sensor located at each of the outlet of the LP turbine 34 and the steam supply line 312, which communicates with the engine controller 334. The sensor may be one or more pressure sensors. Additionally, or alternatively, the sensor system 332 may include other sensors, such as a flow rate sensor.

[0060] Fuel system 302 may be communicatively and operatively coupled to turbine engine 10 along communication line 346. Figure 1 ) of the turbine engine 10. The engine controller 334 is configured to operate various aspects of the turbine engine 10, including the fuel system 302 in the embodiment discussed herein. The engine controller 334 may be a full authority digital engine control (FADEC). In this embodiment, the engine controller 334 is a computing device having one or more processors 340 and one or more memories 342. The processor 340 may be any suitable processing device, including but not limited to a microprocessor, a microcontroller, an integrated circuit, a logic device, a programmable logic controller (PLC), an application specific integrated circuit (ASIC), and / or a field programmable gate array (FPGA). The memory 342 may include one or more computer-readable media, including but not limited to non-transitory computer-readable media, computer-readable non-volatile media (e.g., flash memory), RAM, ROM, a hard drive, a flash drive, and / or other storage devices.

[0061] The memory 342 can store information accessible to the processor 340, including computer-readable instructions that can be executed by the processor 340. The instructions can be any set of instructions or sequence of instructions that, when executed by the processor 340, cause the processor 340 and the engine controller 334 to perform operations. In some embodiments, the instructions can be executed by the processor 340 to cause the processor 340 to perform any operations and functions that the engine controller 334 is configured for, as will be further described below. The instructions can be software written in any suitable programming language, or they can be implemented in hardware. Additionally, and / or alternatively, the instructions can be executed in logical and / or virtual separate threads on the processor 340. The memory 342 can also store data that can be accessed by the processor 340.

[0062] The technology discussed herein relates to computer-based systems and actions taken by computer-based systems and information sent to and from computer-based systems. It will be appreciated by those of ordinary skill in the art that the inherent flexibility of computer-based systems allows for various possible configurations, combinations, and divisions of tasks and functions between and in components. For example, the processes discussed herein can be implemented using a single computing device or multiple computing devices working in combination. Databases, memories, instructions, and applications can be implemented on a single system or distributed across multiple systems. Distributed components can run sequentially or in parallel.

[0063] The engine controller 334 may be communicatively coupled to one or more sensors of the sensor system 332 along a communication line 344 to receive input from the sensor system 332, and based on the input received from the one or more sensors of the sensor system 322, the engine controller 334 is configured to control the flow of fuel through the fuel supply line 310 by directly or indirectly controlling the fuel flow control device 320. In some examples, the sensor system 332 detects or senses pressure at one or more locations in the fuel and steam system 300 or the turbine engine 10. If the sensor system 332 indicates a predetermined pressure or a pressure within a predetermined pressure range or above or below a predetermined pressure threshold, the engine controller 334 opens, closes, partially opens, or partially closes the fuel flow control device 320 to introduce, not introduce, or control the flow rate of the fuel flow introduced into the combustor of the combustion section 28, as described in more detail below.

[0064] Thus, the engine controller 334 can bidirectionally communicate with each of the fuel system 302 and the sensor system 332. For example, the engine controller 334 can receive and optionally store or record pressure from one or more sensors of the sensor system 332 located at the LP turbine (e.g., via sensor line 336), pressure from one or more sensors of the sensor system 332 located at the steam supply line 312 (e.g., via sensor line 338), pressure from one or more sensors at both locations, pressure from another location of the fuel and steam system 300, or pressure from another location of the turbine engine 10. The engine controller 334 can control the flow rate of fuel through the fuel supply line 310 based on the information or data sensed or detected by the sensor system 332. The engine controller 334 also communicates with the fuel system 302, and in particular, with the fuel flow control device 320. The engine controller 334 can open, close, partially open, or partially close the fuel flow control device 320 to control the flow rate of fuel to the combustor of the combustion section 28, as will be described in more detail below.

[0065] In adopting Figure 3The fuel and steam system 300 of the turbine engine described herein (e.g., Figure 1 During operation of the turbine engine 10 described herein, the sensor system 332 is used to monitor the pressure (or flow rate as described herein) of the steam system 304. The pressure at the outlet of the LP turbine 34 is monitored (e.g., indicated by the sensor line 336) or the pressure at the steam supply line 312 is monitored (e.g., indicated by the sensor line 338), or both are measured. By measuring or monitoring the pressure at these two locations, the sensor system can provide an indication of whether there is a pressure loss in the steam system 304 from the LP turbine outlet to the injection at the fuel-steam injector 316. That is, for example, if the pressure at the sensor line 338 is zero, the sensor system 332 senses a full steam loss condition in the steam system 304. If the pressure at the sensor line 338 is lower than the pressure at the sensor line 336, the sensor system 332 senses a partial steam loss condition in the steam system 304. The sensor system 332 can transmit this condition as an input to the controller 334. As described in more detail below, the condition sensed by the sensor system 332 determines the state of the fuel system 302 and the flow rate of fuel through the fuel system 302.

[0066] Once the sensor system 332 detects the condition of the steam system 304, the fuel flow control device 320 is actuated to open or close based on the steam system condition. The fuel flow control device 320 can be automatically controlled based on the pressure in the steam system 304. For example, a pressure change in the steam system 304 can cause the fuel flow control device 320 to open or close to increase the fuel flow to the burner. In such an example, the controller 334 and the sensor system 332 can be omitted.

[0067] In some examples, the fuel flow control device 320 can be automatically controlled based on the pressure in the steam system 304, or can be controlled to do so, for example, by a controller 334. Once the controller 334 receives the sensor input, the controller 334 determines whether to increase the fuel flow through the fuel supply pipeline 310, and if it is necessary to increase, the controller 334 determines the degree of increase. For example, a predetermined pressure threshold or a predetermined pressure range can be set before the turbine engine is operated. During operation of the fuel and steam system 300, if the controller 334 receives input from the sensor system 332 that the pressure of the sensed steam system is outside the predetermined threshold or range of the initial operating pressure of the steam system (e.g., below at least five to twenty percent), the controller 334 can control the fuel system 302 to supply the secondary fuel flow to the burner of the combustion section 28. The controller 334 actuates the fuel flow control device 320 to open, close, partially open, or partially close to allow a desired flow rate or volume of fuel flow to enter the combustion section 28. The flow rate of the introduced fuel can be based on the amount of steam loss detected (e.g., the detected condition). In some examples, the amount of fuel introduced or the fuel flow rate increases as the steam loss increases, such that the higher the percentage of steam loss, the higher the rate or amount of fuel introduced to the combustor.

[0068] In other words, the fuel system 302 provides a primary fuel flow through the primary fuel supply 306 and a secondary fuel flow through the secondary fuel supply 310. The fuel system 302 includes a first state and a second state, in which the secondary fuel flow to the burner of the combustion section 28 has a first flow rate, and in the second state, the secondary fuel flow to the burner has a second flow rate. The first flow rate and the second flow rate may be the same or different. In some examples, the first state and the first flow rate may be arranged so that the flow rate is zero, so that the secondary fuel flow is not provided to the burner (e.g., the fuel flow control device is closed). This may be when the steam system 304 is operated at a predetermined pressure threshold or the turbine engine 10 is operated at a predetermined power output, or both. In this example, the secondary fuel flow may not be required. The second state and the second flow rate may be arranged so that there is a flow rate greater than the first flow rate (e.g., the fuel flow control device is open). This may be when the steam system 304 is operated below a predetermined pressure threshold or the turbine engine 10 is operated below a predetermined power output. In such an example, a secondary fuel flow may be required to maintain or increase the power output of the turbine engine. This will be described in more detail below.

[0069] In an example where the fuel flow control device 320 automatically provides fuel to the combustion section 28 based on the pressure in the steam system 304, the fuel flow control device 320 can be a valve actuated based on a pneumatic signal or a hydraulic signal from the steam system 304. For example, the steam pressure can act on (e.g., push) a valve closing device within the fuel flow control device 320. When the steam pressure is at a predetermined level, the valve closing device maintains the fuel flow control device 320 in a closed position. When the steam pressure increases or decreases based on the conditions of the steam system 304, the valve closing device can open to allow fuel to pass through the fuel flow control device 320. The conditions that can open or close the fuel flow control device 320 will be discussed in more detail below.

[0070] In examples where the fuel flow control device 320 is controlled via a controller 334, an electrical signal from the controller 334 causes an actuator (not shown) to open or close a valve closure within the fuel flow control device 320 based on certain conditions, as discussed in more detail below. In some examples, the fuel flow control device 320 may thus be a solenoid valve.

[0071] The predetermined pressure threshold or predetermined pressure range may be or may be based at least in part on a predetermined pressure difference between sensor line 336 and sensor line 338, a predetermined pressure or pressure range of sensor line 336, or a predetermined pressure or pressure range of sensor line 338, or any combination thereof. The predetermined pressure threshold or predetermined pressure range may vary by the operation of the turbine engine, such that during certain operating conditions (e.g., takeoff, flight or cruise, or landing), the predetermined pressure range or threshold is based on the expected steam pressure or expected power range during the particular operating condition. Therefore, the predetermined pressure threshold or predetermined pressure range may be different during different stages of engine operation. In some examples, the predetermined pressure range or threshold may be the same under all operating conditions. Although described as a predetermined pressure, the predetermined value compared to the sensed value may be other parameters, such as power output, temperature, etc.

[0072] During the operation of turbine engine 10 described above, fuel is continuously introduced along primary fuel supply line 106 and primary fuel injector 108 to achieve normal combustion for engine operation. The fuel flow along primary fuel supply line 106 does not increase based on the conditions of the steam system. Instead, the fuel flow along primary fuel supply line 106 remains constant based on the desired operating conditions of the engine or based on a predetermined value.

[0073] As used herein, "partial loss" means a loss of at least 5% to 100%, but not including 100%, and in some examples, a partial loss means a loss of at least 5% to 20% of a predetermined value or predetermined range. "Total loss" means a loss of 100% of a predetermined value or predetermined range.

[0074] Supplying steam flow to the combustors of the combustion section 28 inputs additional work to the LP turbine 34. Figure 1 )When operating with steam injected into the combustor, the power output of the turbine engine 10 is increased compared to an engine without steam injected into the combustor. Since the turbine engine 10 is operated with such steam injection, if the steam pressure is lost, the power in the turbine engine 10 will be lost accordingly. Therefore, the controller 334 detects such pressure loss (or as described below, can detect power loss) through the sensor system 332 to determine the condition of the steam system 304. The controller 334 compensates for the steam loss by increasing the flow rate of the secondary fuel flow to the combustor (e.g., by actuating the fuel flow control device 320). The additional flow of the secondary fuel flow to the combustor allows additional combustion within the combustor, thereby providing additional work to the LP turbine 34. The fuel flow control device 320 can be opened to a desired degree (e.g., fully open or partially open) to achieve the desired fuel flow rate, thereby allowing the desired combustion to offset the loss of power and steam and maintain or improve engine operation. That is, the flow rate of the secondary fuel flow can be increased based on the condition of the steam flow. For example, a first condition of the steam system may cause the fuel system 302 to have a first state with a first flow rate of the secondary fuel flow, while a second condition of the steam system may cause the fuel system 302 to have a second state with a second flow rate of the secondary fuel flow. Depending on the condition of the steam system, the first flow rate and the second flow rate may be the same or may be different.

[0075] In some examples, fuel flow may flow through the fuel supply line 310 only when a steam loss or a power loss exists. That is, during normal operation (e.g., operation of the steam system at an initial operating pressure within a predetermined level), only steam may be supplied to the burners of the combustion section 28. In this case, the fuel flow control device 320 is in a closed position and no secondary fuel flow is provided to the burners. Only when the controller 334 determines a steam loss or a power loss, the fuel flow control device 320 is opened (partially or fully) to introduce a secondary fuel flow to the burners to offset the power loss.

[0076] In other examples, the introduction of fuel into the burner through the fuel supply line 310 occurs simultaneously with the introduction of fuel into the burner through the steam supply line 312. That is, during normal operation, both fuel and steam are supplied to the burner of the combustion section 28. In this case, the fuel flow control device 320 is at least partially open. When the controller 334 determines that a steam loss or a power loss exists, the fuel flow control device 320 can be opened to a greater extent (partially or completely) to introduce fuel into the burner to offset the power loss. The steam loss detected by the controller 334 may be a steam pressure loss (e.g., when the sensor system 332 includes a pressure sensor), or a steam flow rate loss (e.g., when the sensor system 332 includes a flow rate sensor), or a combination of both.

[0077] Figure 4 A fuel and steam system 400 is shown which may be used with respect to Figure 2 The fuel and steam system 200 described above is used to inject fuel and steam into the combustion section 28 of the turbine engine 10. The fuel and steam system 400 includes a fuel system 402 and a steam system 404. The fuel and steam system 400 is similar to the Figure 3 The described fuel and steam system 300 is substantially similar, except that the manner in which the fuel and steam flows are introduced into the secondary region 28b of the burner of the combustion section 28 is different. Therefore, the same reference numerals will be used for the components of the fuel and steam system 400 that are the same or similar to the components of the above-described fuel and steam system 300. The above-described description of these components also applies to the present embodiment, and a detailed description of these components is omitted here.

[0078] Therefore, the fuel and steam system 400 includes a fuel system 402 and a steam system 404. The fuel system 402 is the same as the fuel system 302, except that the fuel supply line 410 introduces the fuel flow into the secondary zone 28b through a fuel injector 416 (schematically shown). As with the fuel and steam system 300, the fuel supply line 410 is provided with a fuel flow control device 320 that communicates with the engine controller 334. The steam system 404 is the same as the steam system 304, except that the steam supply line 412 introduces the steam flow into the secondary zone 28b through a steam injector 418. The steam injector 418 and the fuel injector 416 are separated and axially spaced apart from each other. On the contrary, in the fuel and steam system 300, the fuel flow and the steam flow are combined so that the fuel-steam injector 316 is a combined injector of fuel and steam. As with the fuel and steam system 300, the fuel flow through the fuel supply line 410 is controlled by the engine controller 334 based on the input received from the sensor system 332. This control may be achieved by directly or indirectly controlling a fuel flow control device 320 provided along the fuel supply line 410 .

[0079] Although illustrated as introducing the fuel flow into the secondary region 28b, in some examples, the fuel and steam system 400 may introduce the fuel into the primary region 28a, e.g. Figure 6 described.

[0080] The operation of the fuel and steam system 400 is substantially the same as the operation of the fuel and steam system 300. The only difference is that, rather than mixing or combining the fuel and steam flows prior to introduction into the combustor, the fuel and steam flows are introduced into the combustor along separate, independent lines (e.g., along fuel supply line 410 and steam supply line 412, respectively).

[0081] Figures 5 to 10 Shown as Figures 1 to 4 Various exemplary embodiments of burners and injectors for introducing fuel and steam into the combustion section 28 are described.

[0082] Figure 5 A schematic cross-sectional view of a burner 500 is shown. The burner 500 may include Figure 1 or Figure 3 500 is a combustor that is configured to provide a combined fuel-steam flow to a secondary zone, as previously described. The combustor has an outer casing 502 and an inner casing 504. Within the outer casing 502 and the inner casing 504, the combustor 500 includes an outer liner 506 and an inner liner 508. The combustor 500 includes a front end 510 and a rear end 512. The front end 510 may be a dome of the combustor 500. At the front end 510, the combustor 500 includes a swirler 514. The swirler 514 directs air and fuel into an interior 517 of the combustor 500 (e.g., an area between the outer liner 506 and the inner liner 508). Figure 1 and Figure 3 consider Figure 5 The swirler 514 may introduce fuel provided along the fuel supply line 106 and the fuel supply line 306, respectively. Therefore, the fuel injector 108 and the fuel injector 308 may be provided with a swirler 514 to introduce the fuel into the interior 517 of the combustor 500.

[0083] The combustor 500 includes one or more dilution openings 516. Figure 5As shown, one or more dilution openings 516 may be provided in the inner liner 508 and the outer liner 506. Although one dilution opening 516 is shown in each liner, multiple dilution openings may be provided, for example, along the circumferential or axial direction of the outer liner 506, the inner liner 508, or both the outer liner 506 and the inner liner 508. The one or more dilution openings 516 introduce air into the interior 517 of the combustor 500. The air introduced through the one or more dilution openings 516 is provided from an outer passage 550 between the outer liner 506 and the outer casing 502 and an inner passage 552 between the inner liner 508 and the inner casing 504.

[0084] The interior 517 of the combustor 500 includes a primary zone 518 and a secondary zone 520 within the interior 517 of the combustor 500. The primary zone 518 is defined in the axial direction A by a primary zone dimension 528 extending between an interior surface 522 and a first axis 524. The interior surface 522 is an interior surface of a front wall at the front end 510 of the combustor 500. The first axis 524 extends through a front end 526 of the one or more dilution openings 516. The secondary zone 520 is defined in the axial direction A by a secondary zone dimension 534 extending between the first axis 524 and a second axis 530. The second axis 530 extends through a rearmost end 532 of the combustor 500. In combination Figure 3 and Figure 4 consider Figure 5 , the primary region 518 is aligned with the primary region 28a, and the secondary region 520 is aligned with the secondary region 28b.

[0085] The combustor 500 includes fuel-steam injectors 536 within the outer liner 506, which may be used to Figure 1 The fuel-steam injector 116 described or related Figure 3 The fuel-steam injector 316 described above. The fuel-steam injector 536 introduces the combined fuel-steam flow into the secondary zone 520. In such an example, the secondary fuel flow and the steam flow are introduced at the same axial position along the length of the combustor 500. The fuel-steam injector 536 may include a nozzle shape (e.g., an extended cross-sectional shape) at the end of the fuel-steam injector 536 for introducing the fuel-steam flow into the secondary zone 520. Although an extended cross-sectional shape is shown, other shapes are contemplated, such as a right cylindrical cross-sectional shape, or other converging or diverging cross-sectional shapes. In addition, it is contemplated that such shapes may be used for either or both of the fuel injection and steam injection to the combustor of any of the embodiments described herein.

[0086] Figure 6 A schematic cross-sectional view of a burner 600 is shown. The burner 600 may include Figure 2 or Figure 4The combustion section 28 of the burner 600 is provided to provide a separate fuel flow and steam flow to the secondary zone, as previously described. The burner 600 is substantially similar to the burner 500, except that the fuel flow and steam flow are introduced into the secondary zone in a different manner. Therefore, for the components of the burner 600 that are the same or similar to the components of the burner 500 described above, the same reference numerals will be used. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here.

[0087] Combination Figure 2 and Figure 4 consider Figure 6 , the swirler 514 may introduce fuel provided along the fuel supply line 206 and the fuel supply line 306, respectively. Therefore, the fuel injector 208 and the fuel injector 308 may be provided with a swirler 514 to introduce the fuel into the combustor 600. The combustor 600 includes a fuel injector 636 and a steam injector 638. The fuel injector 636 is separated from the steam injector 638. The fuel injector 636 is located in front of or upstream of the steam injector 638. The fuel injector 636 has a longitudinal centerline axis 640 extending through the center of the fuel injector 636. The fuel injector 636 is angled at an angle α relative to the outer liner 506. The angle α is defined between the longitudinal centerline axis 640 and the vertical axis 642. The vertical axis 642 is perpendicular to the longitudinal centerline axis 12 ( Figure 1 ).like Figure 6 As shown, vertical axis 642 extends through the center of the outlet of fuel injector 636. A distance 644 defining an axial distance of fuel injector 636 from forward end 510 of combustor 600 may be defined between interior surface 522 and vertical axis 642.

[0088] The steam injector 638 has a longitudinal centerline axis 646 extending through the center of the steam injector 638. The steam injector 638 is angled at an angle β relative to the outer liner 506. The angle β is defined between the longitudinal centerline axis 646 and a vertical axis 648. The vertical axis 648 is perpendicular to the longitudinal centerline axis 12 ( Figure 1 ).like Figure 6 As shown, the vertical axis 648 extends through the center of the outlet of the steam injector 638. A distance 650 defining the axial distance of the steam injector 638 from the forward end 510 of the combustor 600 may be defined between the interior surface 522 and the vertical axis 648. A distance 652 defining the overall axial length of the combustor 600 is defined between the interior surface 522 and the rearmost end 532 of the combustor 600. The fuel injector 636 and the steam injector 638 may be angled in opposite directions.

[0089] Fuel injector 636 may be used as Figure 2 The fuel injector 216 described and the Figure 4 The fuel injector 416 is depicted. The steam injector 638 can be used to supply Figure 2 The steam ejector 218 described and Figure 4 The depicted steam injector 418. Fuel injector 636 introduces a fuel flow into primary zone 518 upstream of steam injector 638, and steam injector 638 introduces a steam flow into secondary zone 520. Fuel injector 636, steam injector 638, or both fuel injector 636 and steam injector 638 may include a nozzle shape at the end of the body for introducing the respective fuel and steam flows into combustor 600.

[0090] exist Figure 6 In the example of , the fuel injector 636 can be positioned in the primary zone 518 such that the distance 644 is ten percent to sixty percent of the combustor length (represented by the distance 652). The distance 644 is selected to be within the above range to define the fuel injector 636 relative to the dome (e.g., the front end 510) and the turbine (e.g., the HP turbine 32) of the combustor to optimize combustion efficiency. Positioning the fuel injector 636 less than ten percent from the front end 510 results in fuel wetting and high dome temperatures on the front end 510. Positioning the fuel injector 636 greater than sixty percent results in a high outlet temperature distribution of the combustor and a reduction in combustion efficiency.

[0091] The steam injector 638 is positioned in the secondary zone 520 such that the distance 650 is thirty percent to ninety percent of the burner length (represented by the distance 652). The distance 650 is selected within the above range to define the steam injector 638 so as to optimize the flame quenching efficiency in the desired area to reduce the NOx of the burner 600. X To reduce NO emissions. X Exhaust, steam is intended to be injected in high temperature areas in the primary zone 518 and the secondary zone 520 via steam injectors 638. Positioning the steam injectors 638 too close to the flame location / dome (e.g., less than thirty percent) will result in flame quenching and eventual flameout.

[0092] The angle α ranges from forty-five degrees to negative forty-five degrees relative to the vertical axis 642 . Figure 6 The angle α shown in FIG. 6 is approximately forty-five degrees. Increasing the angle α to greater than forty-five degrees (in either direction relative to the vertical axis 642) causes the flame to be closer to the liner, thereby causing the liner temperature to increase, which presents durability challenges to the liner (eg, outer liner 506 and inner liner 508).

[0093] The angle β ranges from negative thirty degrees to sixty degrees relative to the vertical axis 648 . Figure 6The angle β shown in is about negative thirty degrees. Steam is injected by steam injectors 638 in the higher temperature areas of the interior 517 of the combustor 600. Most of these areas are generally located in the core area of ​​the combustor 600. There are also high temperature areas near the liners (e.g., the outer liner 506 and the inner liner 508). Therefore, keeping the angle β within the aforementioned range takes into account the geometric constraints of the nozzle angle and also takes into account that keeping too much steam near the liner will not effectively use the steam to reduce NO x .

[0094] In some examples, angle α and angle β may be the same. In some examples, angle α and angle β may be mirror images. In some examples, angle α and angle β may be parallel. In some examples, angle α and angle β may be different.

[0095] Thus, combustor 600 includes fuel and steam injection after primary fuel injection (e.g., via swirler 514). The fuel and steam injections may be axially staggered such that steam is injected at steam injector 638 axially downstream of the fuel injected at fuel injector 636. Injecting steam axially downstream of the fuel allows steam to be introduced into the combustor to reduce the high temperatures generated by secondary fuel injection via fuel injector 636. Figure 6 In the example of FIG. 1 , the fuel injector 636 and the steam injector 638 may be located at the same circumferential position, or may be circumferentially offset relative to each other, as shown in FIG. Figure 7 discussed.

[0096] Figure 7 A schematic cross-sectional view of a burner 700 is shown. The burner 700 may include Figures 1 to 4 The combustor 700 is substantially similar to the combustor 500 and illustrates an exemplary circumferential orientation of fuel and steam injectors. Figure 7 The burner of FIG. 700 is illustrated in an axial cross-section taken from a radial plane extending through a dilution opening (e.g., through dilution opening 516). Therefore, for components of the burner 700 that are the same or similar to the components of the above-described burner 500, the same reference numerals will be used. The above description of these components also applies to this embodiment, and a detailed description of these components is omitted here.

[0097] The combustor 700 includes a fuel injector 736 and a steam injector 738. Figure 7In the example, the fuel injectors 736 and the steam injectors 738 are staggered circumferentially. That is, around the circumference of the combustor 700, the fuel and steam may be introduced at circumferentially staggered locations. In some examples, this may be an "ABAB" pattern, where the fuel injectors 736 (e.g., "A" or "B") and the steam injectors 738 (e.g., the other of A" or "B") alternate in an "every other" arrangement around the circumference. In some examples, the staggering may have other patterns. The arrangement of the fuel injectors 736 and the steam injectors 738 may be based on the temperatures expected within the combustor at each particular swirler 514. That is, in low temperature regions, fuel injectors 736 may be included, and in high temperature regions, steam injectors 738 may be included. In some examples, the fuel injectors 736 and steam injectors 738 are located at the same axial position, while in other examples, the fuel injectors 736 and steam injectors 736 are both circumferentially staggered and axially staggered. With regard to Figure 7 The circumferential staggering described can be applied to any of the embodiments described herein. Figure 6 In addition to the axial interlacing depicted and described, Figure 6 The depicted fuel injectors 636 and steam injectors 638 may also be circumferentially staggered.

[0098] exist Figure 7 In some examples, the secondary fuel injection (also called post fuel injection) can be circumferentially staggered with the steam injection. By injecting steam at predetermined circumferential positions, high temperature areas can be reduced by the steam flow. By injecting fuel at predetermined circumferential positions, low temperature areas can be increased by the combustion of the fuel flow. This allows for more uniform temperatures at the outlet of the combustor and the inlet of the turbine section. In some examples, the steam injection can also be located axially downstream of the fuel injection. In some examples, the fuel injector 736, the steam injector 738, or both can be in-line with the swirler 514 (e.g., as shown in FIG. 1 ). Figure 7 514). In some examples, the fuel injector 736, the steam injector 738, or both may be located between or offset from the swirlers 514. In some examples, the steam may be introduced in-line with one or more swirlers, and the fuel may be introduced in-line with other swirlers. In some examples, both the fuel and the steam may be injected between the swirlers. In some examples, the steam flow, the fuel flow, or both may be tangentially inclined relative to the circumferential direction.

[0099] Figure 8 A schematic cross-sectional view of a burner 800 is shown. The burner 800 may include Figure 2 or Figure 4The combustion section 28 of the burner 800 is provided to provide a separate fuel flow and steam flow to the secondary zone, as previously described. The burner 800 is substantially similar to the burner 500, except that the fuel flow and steam flow are introduced into the secondary zone in a different manner. Therefore, for the components of the burner 800 that are the same or similar to the components of the burner 500 described above, the same reference numerals will be used. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here.

[0100] Combination Figure 2 and Figure 4 consider Figure 8 , swirler 514 may introduce fuel provided along fuel supply line 206 and fuel supply line 306, respectively. Therefore, fuel injector 208 and fuel injector 308 may be provided with swirler 514 to introduce fuel into combustor 800. Combustor 800 includes fuel-steam injector 836 within outer liner 506, which may be used as Figure 2 The fuel injector 216 and the steam injector 218, and the Figure 4 The fuel injector 416 and the steam injector 418. The fuel-steam injector 836 provides separate fuel injectors and steam injectors therein.

[0101] The fuel-steam injector 836 is a combination steam and fuel injector, but provides separate steam and fuel flows to the combustor. Therefore, the fuel-steam injector 836 includes a steam injector 840, a first fuel injector 842, and a second fuel injector 844. The steam injector 840 is located between the first fuel injector 842 and the second fuel injector 844. The steam injector 840 can be located in the center between the first fuel injector 842 and the second fuel injector 844. Although described as two separate fuel injectors, the first fuel injector 842 and the second fuel injector 844 can be a single annular fuel injector that circumferentially surrounds the steam injector 840. For example, the steam injector and the fuel injector can be configured as a coaxial fluid line or tube. In such an example, Figure 8 The cross-sectional view shown is taken through the center of a single annular fuel injector so that it appears that there are two fuel injectors. The fuel-steam injector 836 introduces a separate stream of fuel (along separate fuel injectors 842, 844 or along a single annular fuel injector) and a stream of steam (along steam injector 840) into the secondary region 520. One or more of the steam injector 840, the first fuel injector 842, and the second fuel injector 844 may include a nozzle shape at the end of each respective passage for introducing the fuel-steam stream into the secondary region 520.

[0102] In some examples, the steam introduced by steam injectors 840 may be swirled to improve mixing of the product.

[0103] Fig. 9 A schematic cross-sectional view of a burner 900 is shown. The burner 900 may include Figure 2 or Figure 4 of the combustion section 28 to provide separate fuel and steam flows to the secondary zone, as previously described. Burner 900 is substantially similar to burner 800, but with the addition of air openings around the fuel-steam injector 836. Therefore, the same reference numbers will be used for components of burner 800 that are the same as or similar to the components of the burner 800 described above. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here. The air openings may be a first air opening 946 and a second air opening 948 located on the axial front and axial rear sides of the fuel-steam injector 836, respectively. Although described as two air openings, the first air opening 946 and the second air opening 948 may be a single annular air opening circumferentially surrounding the fuel-steam injector 836 (e.g., in a coaxial arrangement). In such an example, Fig. 9 The cross-sectional view shown in is taken through the center of a single annular air opening so that it appears that there are two air openings. Air openings 946, 948 introduce air from air passage 950 into the secondary region 520 around the fuel-steam injector 836. Air passage 950 may be an air passage between the outer liner 506 and the outer casing 502.

[0104] In the combustor 900, non-swirling air is introduced into the combustor via air openings 946, 948 around the fuel-steam injector 836. The radial introduction of non-swirling air increases the penetration of the fuel flow and steam flow into the central region of the combustor (e.g., the center between the inner liner 508 and the outer liner 506). The direction and velocity of the introduced air pulls or moves the fuel flow and steam flow to the central region of the combustor. By increasing the penetration of the fuel flow and steam flow in this manner, the combustion of the fuel flow from the fuel-steam injector 836 occurs at a position closer to the core or central region of the combustor. Increasing the penetration also enables the high temperature in the combustor core to be quenched with the steam flow.

[0105] Fig.10 A schematic cross-sectional view of a burner 1000 is shown. The burner 1000 may include Figure 2 or Figure 4of the combustion section 28 to provide separated fuel and steam flows to the secondary zone, as previously described. The burner 1000 is substantially similar to the burner 800, but a swirler is added around the fuel-steam injector 836. Therefore, the same reference numbers will be used for components of the burner 800 that are the same as or similar to the components of the burner 800 described above. The above description of these components also applies to the present embodiment, and a detailed description of these components is omitted here. The swirlers may be a first swirler 1046 and a second swirler 1048 located on the axial front and axial rear sides of the fuel-steam injector 836, respectively. Although described as two swirlers, the first swirler 1046 and the second swirler 1048 may be a single annular air opening circumferentially surrounding the fuel-steam injector 836 (for example, in a coaxial arrangement). In such an example, Fig.10 The cross-sectional view shown in is taken through the center of a single swirler, so it appears that there are two swirlers. Swirlers 1046, 1048 introduce air from air passage 1050 to the secondary region 520 around the fuel-steam injector 836. Air passage 1050 may be an air passage between the outer liner 506 and the outer casing 502.

[0106] In the combustor 1000, swirling air is introduced into the combustor via swirlers 1046, 1048 around the fuel-steam injectors 836. The radial and swirling introduction of swirling air increases the diffusion of the fuel and steam flows and increases the mixing of the fuel and steam flows in the combustor 1000 entering the central region of the combustor (e.g., the center between the inner liner 508 and the outer liner 506). By increasing the mixing within the core of the combustor, the combustion of the fuel flow is enhanced compared to examples without swirling air flow.

[0107] Although about Figures 1 to 10 Steam injection is described, but the system may include injecting water or a combination of water and steam into the burner. In the example of injecting water, monitoring may include monitoring the pressure of the injected water or the pressure of water along the water supply line, and the fuel increase may be based on the monitored pressure.

[0108] As about Figures 5 to 10 As described above, the secondary region 520 is defined as the region in the burner located after the dilution opening, that is, the region downstream of the dilution opening. This definition may be applicable to some burners, such as rich burners. In some examples, such as for lean burners, the secondary region 520 may be defined as at least fifty percent of the entire burner length.

[0109] Fig.11 Shows the operation has about Figures 1 to 10 An example method 1100 for a turbine engine using any of the fuel systems described.

[0110] In method 1100, step 1102 provides a primary fuel flow to a combustor of a turbine engine. As previously described herein, the primary fuel flow is combusted with compressed air to produce combustion gases within the combustor to generate thrust. In some examples, step 1102 includes injecting the primary fuel flow into a front end of the combustor to produce the combustion gases. Step 1102 may include the primary fuel flow not being based on a pressure of a steam flow. Step 1102 may include introducing the primary fuel flow into the combustor in a primary zone of the combustor.

[0111] At step 1104, a steam flow is introduced into the combustor, as described previously herein. The steam flow has an initial operating condition. In some examples, step 1104 includes introducing the steam flow into a secondary zone of the combustor. Step 1104 may include generating the steam flow from a heat recovery system. Step 1104 may include providing the steam flow from a steam source.

[0112] In step 1106, the method monitors the turbine engine to determine the condition of the turbine engine or the condition of the steam system. Monitoring may include monitoring the pressure of the steam system, monitoring the flow rate of steam in the steam system, monitoring the power output of the turbine engine, or any combination thereof. In some examples, step 1106 includes monitoring the pressure of the steam flow to generate a monitoring pressure, detecting a pressure loss of the steam flow when the monitoring pressure is lower than a predetermined pressure value, and injecting a secondary fuel flow to the burner based on the detection of the pressure loss of the steam flow. Step 1106 may include monitoring the power output of the turbine engine to generate a monitoring power output, detecting a power output loss of the turbine engine when the monitoring power output is lower than a predetermined power value, and injecting a secondary fuel flow to the burner based on the detection of the power output loss of the turbine engine or both.

[0113] At step 1108, a secondary fuel flow is introduced into the combustor. The flow rate of the secondary fuel flow is based on the condition detected in step 1106. The condition may be a pressure loss in the steam flow or a power output loss of the turbine engine, or both. When the monitored pressure is below a predetermined pressure value, a pressure loss is detected. When the monitored power output is below a predetermined power value, a power output loss is detected.

[0114] In some examples, injecting the secondary fuel flow in step 1108 occurs only when a pressure loss of the steam flow is detected. That is, when no pressure loss is detected, the secondary fuel flow is not introduced. In some examples, the method does not inject the secondary fuel flow to the burner in step 1108 based on monitoring that the pressure is equal to or above a predetermined value. During step 1108, a fuel flow control device can be used to control the secondary fuel flow. The controller can control the fuel flow control device.

[0115] As described herein, step 1108 may include injecting a secondary fuel flow upstream of the steam flow. Step 1108 may include controlling a fuel flow control device to inject the fuel flow. Step 1108 may include controlling the fuel flow control device using a controller. Step 1108 may include introducing non-swirling air into the burner together with a secondary fuel flow or a steam flow or both a secondary fuel flow and a steam flow. Step 1108 may include introducing swirling air into the burner together with a secondary fuel flow or a steam flow or both a secondary fuel flow and a steam flow. Step 1108 may include introducing a steam flow and a secondary fuel flow into the burner simultaneously. In some examples, step 1108 includes introducing a secondary fuel flow only when there is a pressure loss in the steam flow. Step 1108 may include introducing a secondary fuel flow into a secondary zone of the burner. Step 1108 may include injecting a secondary fuel flow downstream of the primary fuel flow.

[0116] In some examples, step 1108 includes injecting the secondary steam flow and the secondary fuel flow to the burner through separate fuel injectors. Step 1108 may include injecting the secondary steam flow and the secondary fuel flow to the burner through a single fuel injector. In some examples, the single fuel injector has separate flow paths for the secondary steam flow and the secondary fuel flow, and the flow paths are not fluidly connected. Step 1108 may include injecting the secondary steam flow and the secondary fuel flow to the burner through a single fuel injector, and the secondary steam flow and the secondary fuel flow are mixed together in a single fuel in the same flow path before being injected into the burner.

[0117] In some examples, the method includes angles of fuel flow and steam flow relative to a vertical axis perpendicular to a centerline axis of the combustor. In some examples, the angle is tangential to the combustor.

[0118] The term "injector" is used throughout the specification and is not intended to limit the structure for introducing fuel or steam into the burner. In some examples, the injector may be a nozzle.

[0119] Although described herein as injecting the secondary fuel flow only in front of the steam flow or injecting the secondary fuel flow both in front of and behind the steam flow, the secondary fuel flow may be introduced only behind the steam flow. Although a single fuel supply line and fuel injector and a single steam supply line and steam injector (whether combined or separated) are shown, more may be provided. The injectors of the present disclosure are shown and described in some examples as being introduced in a purely radial direction. An angled introduction or tangential introduction (e.g., tangential to the liner surface) is contemplated.

[0120] Although the introduction of fuel and steam in the secondary zone is described, one or both of the fuel and steam flows may be introduced into the primary zone.

[0121] In some examples, the flow of steam, the flow of fuel, or both the flow of steam and the flow of fuel may be swirled prior to or during introduction into the combustor.

[0122] The fuel and steam system of the present disclosure is described with respect to several examples of fuel introduction, steam introduction, injector location, injector configuration, separate injectors, combined injectors, separate flows, combined flows, axial staggering, circumferential staggering, etc. Each example described herein may be combined with other examples described herein without departing from the scope of the present disclosure.

[0123] Thus, the present disclosure provides a fuel and steam system that injects a fuel flow and a steam flow into a secondary region of a combustor. Such a system allows for improved specific fuel consumption, NO and CO2 emissions compared to turbine engines that do not inject both fuel and steam into the combustor. x Reduced heat, reduced smoke, lower dynamics, and allows engine power to be maintained with partial or total loss of steam. In some examples, steam is extracted from the engine exhaust in a heat recovery system and then reinjected into the combustor to gain specific fuel consumption benefits and NO x reduce.

[0124] In addition, the present disclosure provides a fuel and steam system that allows for controlled injection of fuel to the secondary zone. If there is a partial or total loss of steam injection to the secondary zone during engine operation, there will be a corresponding loss of engine power. By controlling the injection of fuel to the secondary zone, in the event of a failure in the steam flow provided to the engine core, power can be restored by injecting additional fuel to the burner to operate as a power booster. The system of the present disclosure can also be used to include steam or water injection for NO x Improved and power-enhanced systems.

[0125] The fuel and steam system of the present disclosure includes controlling the fuel flow based on the sensed condition of the steam flow. For example, in the event of a partial or complete loss of steam flow, fuel is injected into the primary or secondary zone of the combustor to restore the power loss caused by the steam loss. A control device can be used to detect engine power loss or steam pressure loss, and fuel can be injected to increase power to achieve the desired power / thrust level.

[0126] In some examples, the fuel and steam system of the present disclosure includes separate steam and fuel circuits to inject steam when the steam system is operating normally (e.g., without partial or complete loss of steam), or to inject fuel when there is a loss of steam flow. In some examples, the steam flow and the fuel flow may be mixed in a mixing device and then injected into the burner as a separate mixture of fuel and steam. In some examples, the fuel and steam system of the present disclosure includes steam and fuel injection under all operating conditions. This can achieve additional NOx In such an example, the steam and fuel may be injected simultaneously through separate circuits or may be mixed and the mixture may be injected to the combustor.

[0127] Further aspects are provided by the subject matter of the following clauses.

[0128] A turbine engine, comprising: a combustor, the combustor being positioned in a core air flow path, the combustor combusting a compressed air flow and a primary fuel flow to produce combustion gases; and a fuel and steam system, the fuel and steam system being fluidly connected to the combustor, the fuel and steam system comprising: a steam system for providing a steam flow to the combustor along a steam supply line; and a fuel system for providing the primary fuel flow and a secondary fuel flow to the combustor, the fuel system having a first state and a second state, in the first state, the secondary fuel flow flowing to the combustor has a first flow rate, in the second state, the secondary fuel flow flowing to the combustor has a second flow rate, the first flow rate and the second flow rate are different, and the first state and the second state are based on a condition of the steam system.

[0129] According to the turbine engine of the preceding clause, said steam flow and said secondary fuel flow are provided at the same axial position along the length of said combustor.

[0130] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is provided upstream of the steam flow.

[0131] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is provided downstream of the primary fuel flow.

[0132] A turbine engine as claimed in any preceding clause, wherein the first flow rate of the secondary fuel flow is zero such that in the first state no secondary fuel flow is provided to the combustor.

[0133] A turbine engine as described in any preceding clause, wherein the second flow rate is greater than the first flow rate.

[0134] A turbine engine as in any preceding clause, the steam system having an initial operating pressure, and the fuel system assuming the second state based on the pressure of the steam system being at least five percent less than the initial operating pressure.

[0135] According to the turbine engine of the preceding clause, the fuel system assumes the second state based on the pressure of the steam system being at least twenty percent lower than the initial operating pressure.

[0136] The turbine engine according to any preceding clause, further comprising a sensor system configured to detect a pressure of the steam system, wherein the fuel system assumes the first state based on the pressure of the steam system being higher than a predetermined value, and the fuel system assumes the second state based on the pressure of the steam system being at least five percent lower than the predetermined value.

[0137] According to the turbine engine described in any of the preceding items, the fuel and steam system further includes: a secondary fuel supply pipeline, which is used to provide the secondary fuel flow to the combustor; and a fuel flow control device, which is positioned along the secondary fuel supply pipeline, and the fuel flow control device is configured to control the first state and the second state.

[0138] A turbine engine as claimed in any preceding clause, wherein the fuel flow control device is closed in the first state and open in the second state.

[0139] A turbine engine according to any preceding clause, further comprising a controller configured to actuate the fuel flow control device to place the fuel system in the first state or the second state.

[0140] A turbine engine as described in any preceding clause, wherein the controller is configured to actuate the fuel flow control device based on a pressure of the steam system or a power output of the turbine engine.

[0141] A turbine engine according to any preceding clause, the fuel system comprising: a primary fuel supply line having a primary fuel injector at a front end of the combustor; and a secondary fuel supply line having a secondary fuel injector along an axial length of the combustor.

[0142] A turbine engine according to any preceding clause, said steam system further comprising a steam injector for providing said steam flow from said steam supply line at a location along said axial length of said combustor, wherein said steam injector and said secondary fuel injector are combined fuel-steam injectors.

[0143] A turbine engine according to any preceding clause, said steam system further comprising said steam supply line having a steam injector for providing said steam flow along said axial length of said combustor, wherein said steam injector and said secondary fuel injector are separate.

[0144] A turbine engine according to any preceding clause, wherein the separate fuel injectors and steam injectors are arranged in the same body.

[0145] A turbine engine as claimed in any preceding clause, the steam system comprising a heat recovery system for recapturing steam from exhaust gas of the turbine engine and providing the recaptured steam to a steam turbine and to the steam supply line.

[0146] A turbine engine as described in any preceding clause, wherein the fuel flow control device is a valve.

[0147] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is introduced into a secondary region of the combustor.

[0148] A turbine engine as claimed in any preceding clause, wherein the secondary region is defined between dilution openings in the combustor and a distal end of the combustor.

[0149] A turbine engine as recited in any preceding clause, wherein said secondary region is defined as at least fifty percent of a combustor length, said combustor length being defined between a forward end and a distal end of said combustor.

[0150] A turbine engine as claimed in any preceding clause, wherein said steam flow is introduced into said secondary region.

[0151] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is introduced into a primary zone of the combustor.

[0152] A turbine engine as claimed in any preceding clause, wherein the primary zone is defined between a forward end of the combustor and a dilution opening in the combustor.

[0153] A turbine engine as claimed in any preceding clause, wherein said steam flow is introduced into said primary zone.

[0154] A turbine engine as in any preceding clause, the combustor comprising a fuel-steam injector configured to introduce a combined flow of the secondary fuel flow and the steam flow into the combustor.

[0155] A turbine engine as recited in any preceding clause, wherein when the fuel system is in the first state, the combined flow comprises steam only, and when the fuel system is in the second state, the combined flow comprises a mixture of steam and fuel.

[0156] A turbine engine as claimed in any preceding clause, wherein the fuel-steam injector is located downstream of a dilution opening in the combustor.

[0157] A turbine engine according to any preceding clause, further comprising a fuel injector for providing said secondary fuel flow and a steam injector for providing said steam flow.

[0158] A turbine engine as described in any preceding clause, wherein the fuel injector is angled relative to an axis perpendicular to a centerline axis of the combustor, wherein the angle relative to the axis is from forty-five degrees to negative forty-five degrees.

[0159] A turbine engine as in any preceding clause, said steam injector being angled relative to an axis perpendicular to said centerline axis of said combustor, wherein said angle is from negative thirty degrees to sixty degrees.

[0160] A turbine engine as described in any preceding clause, wherein the fuel injector or the steam injector or both are angled at a tangential angle to the combustor.

[0161] A turbine engine as described in any preceding clause, wherein said fuel injector and said steam injector are angled in opposite directions.

[0162] A turbine engine as claimed in any preceding clause, wherein said secondary fuel flow and said steam flow are axially staggered.

[0163] A turbine engine as claimed in any preceding clause, wherein said secondary fuel flow and said steam flow are circumferentially staggered.

[0164] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is introduced into the primary combustion zone.

[0165] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow and the primary fuel flow are provided by separate flow paths in the same injector.

[0166] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow and the primary fuel flow are provided by the same flow path in the same injector.

[0167] A turbine engine as claimed in any preceding clause, wherein the secondary fuel flow is provided upstream of the fuel flow.

[0168] A turbine engine according to any preceding clause, further comprising air openings surrounding said secondary fuel flow and said steam flow, said compressed air being provided to said combustor through said air openings.

[0169] A turbine engine according to any preceding clause, further comprising a swirler surrounding said secondary fuel flow and said steam flow, said compressed air being provided to said combustor through said swirler.

[0170] A turbine engine according to any of the preceding clauses, further comprising a fan shaft connected to the fan, a shaft and a turbine, the turbine being positioned downstream of the combustor to receive the combustion gases and rotate the turbine, the turbine drive being connected to the fan shaft to rotate the fan shaft when the turbine rotates.

[0171] The turbine engine of any preceding clause, further comprising a sensor system configured to monitor a pressure of the steam system, the controller configured to actuate the fuel flow control device based on the pressure of the steam system.

[0172] A method of operating a turbine engine according to any preceding clause.

[0173] A method of operating a turbine engine, the method comprising introducing a steam flow into a combustor; monitoring a pressure of the steam flow; and injecting a fuel flow to the combustor based on the pressure of the steam flow.

[0174] A method of operating a turbine engine according to any preceding clause, the method comprising introducing the steam flow into the combustor; and introducing the secondary fuel flow into the combustor based on a pressure loss of the steam flow or a power output loss of the turbine engine.

[0175] The method according to any of the preceding clauses further includes: monitoring the pressure of the steam flow to generate a monitoring pressure; monitoring the power output of the turbine engine to generate a monitoring power output; when the monitoring pressure is lower than a predetermined pressure value, detecting the pressure loss of the steam flow; when the monitored power output is lower than a predetermined power value, detecting the power output loss of the turbine engine; and injecting the secondary fuel flow into the combustor based on the detection of the pressure loss of the steam flow or based on the detection of the power output loss of the turbine engine, or both.

[0176] A method as in any preceding clause, injecting the secondary fuel flow into the combustor only when a detected pressure loss of the steam flow exists.

[0177] A method as in any preceding clause, further comprising not injecting the secondary fuel flow to the combustor based on a monitored pressure being equal to or above the predetermined value.

[0178] The method according to the preceding clause, injecting the fuel flow comprises not injecting the fuel flow when the pressure is equal to or higher than a predetermined value, and injecting the fuel flow when the pressure is at least five percent lower than the predetermined value.

[0179] A method as in any preceding clause, wherein the fuel flow is injected upstream of the steam flow.

[0180] A method according to any preceding clause, further comprising controlling a fuel flow control device to inject said fuel flow.

[0181] A method as claimed in any preceding clause, wherein controlling the fuel flow control means is performed by a controller.

[0182] A method as in any preceding clause, further comprising introducing non-swirling air into the combustor with the fuel flow or the steam flow or both the fuel flow and the steam flow.

[0183] A method as in any preceding clause, further comprising introducing swirling air into the combustor with the fuel flow or the steam flow or both the fuel flow and the steam flow.

[0184] A method as in any preceding clause, wherein the steam flow and the fuel flow are introduced into the combustor simultaneously.

[0185] A method as in any preceding clause, wherein the fuel flow is introduced only when a pressure loss in the steam flow exists.

[0186] A method as in any preceding clause, the fuel flow being introduced into a secondary zone of the combustor.

[0187] A method as in any preceding clause, wherein the steam flow is introduced into a secondary zone of the combustor.

[0188] A method as in any preceding clause, further comprising generating the steam stream from a heat recovery system.

[0189] A method as in any preceding clause, further comprising providing the steam flow from a steam source.

[0190] A method as in any preceding clause, wherein the fuel flow and the steam flow are angled relative to a vertical axis that is perpendicular to a centerline axis of the combustor.

[0191] A method as in any preceding clause, said angle being tangential to said burner.

[0192] A method as in any preceding clause, the fuel stream being a secondary fuel stream and the method further comprising injecting a primary fuel stream into a front end of the combustor to generate combustion gases.

[0193] A method as described in the preceding clause, wherein the secondary fuel flow is located downstream of the primary fuel flow.

[0194] A method as in any preceding clause, wherein the primary fuel flow is not based on the pressure of the steam flow.

[0195] A method as in any preceding clause, wherein the primary fuel flow is introduced into the burner in a primary zone of the burner.

[0196] A method according to any preceding clause, comprising monitoring the pressure of the steam flow to produce a monitoring pressure, detecting the pressure loss of the steam flow when the monitoring pressure is below a predetermined pressure value, and injecting the secondary fuel flow into the combustor based on the detection of the pressure loss of the steam flow.

[0197] A method according to any of the preceding clauses, comprising monitoring the power output of the turbine engine to produce a monitored power output; detecting a loss of power output of the turbine engine when the monitored power output is below a predetermined power value; and injecting the secondary fuel flow into the combustor based on the detection of the power output loss of the turbine engine, or both.

[0198] A method as claimed in any preceding clause, comprising injecting a secondary steam flow and said secondary fuel flow into said combustor via separate fuel injectors.

[0199] A method as in any preceding clause, comprising injecting a secondary steam flow and the secondary fuel flow into the combustor via a single fuel injector.

[0200] The method of the preceding clause, wherein the single fuel injector has separate flow paths for the secondary steam flow and the secondary fuel flow, the separate flow paths being not fluidly connected.

[0201] A method as in any preceding clause, comprising injecting a secondary steam flow and said secondary fuel flow to said combustor via a single fuel injector, said secondary steam flow and said secondary fuel flow being mixed together within said single fuel in the same flow path prior to injection into said combustor.

[0202] Although the above description is directed to the preferred embodiments of the present disclosure, other changes and modifications will be apparent to those skilled in the art and may be made without departing from the spirit or scope of the present disclosure. In addition, even if not explicitly stated above, the features described in conjunction with one embodiment of the present disclosure may also be used in conjunction with other embodiments.

Claims

1. A turbine engine, characterized in that: include: a combustor positioned in the core air flow path, the combustor combusting the compressed air flow and the primary fuel flow to produce combustion gases; as well as a fuel and steam system fluidly coupled to the burner, the fuel and steam system comprising: a steam system for providing a steam flow to the burner along a steam supply line; and A fuel system for providing the primary fuel flow and the secondary fuel flow to the burner, the fuel system having a first state and a second state, in the first state, the secondary fuel flow flowing to the burner has a first flow rate, in the second state, the secondary fuel flow flowing to the burner has a second flow rate, the first flow rate and the second flow rate are different, and the first state and the second state are based on the condition of the steam system.

2. The turbine engine according to claim 1, characterized in that Wherein the steam flow and the secondary fuel flow are provided at the same axial position along the length of the combustor.

3. The turbine engine according to claim 1, characterized in that: Wherein the secondary fuel flow is provided upstream of the steam flow.

4. The turbine engine according to claim 1, characterized in that: Wherein the secondary fuel flow is provided downstream of the primary fuel flow.

5. The turbine engine according to claim 1, characterized in that The first flow rate of the secondary fuel flow is zero, so that no secondary fuel flow is provided to the burner in the first state.

6. The turbine engine according to claim 1, characterized in that Wherein the second flow rate is greater than the first flow rate.

7. The turbine engine according to claim 1, characterized in that The steam system has an initial operating pressure, and the fuel system assumes the second state based on the pressure of the steam system being at least five percent less than the initial operating pressure.

8. The turbine engine according to claim 1, characterized in that Further comprising a sensor system configured to detect a pressure of the steam system, wherein the fuel system assumes the first state based on the pressure of the steam system being higher than a predetermined value, and the fuel system assumes the second state based on the pressure of the steam system being at least five percent lower than the predetermined value.

9. The turbine engine according to claim 1, characterized in that The fuel and steam system further comprises: a secondary fuel supply line for providing the secondary fuel flow to the burner; and A fuel flow control device is positioned along the secondary fuel supply line, the fuel flow control device being configured to control the first state and the second state.

10. The turbine engine according to claim 9, characterized in that The fuel flow control device is closed in the first state and opened in the second state.

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