Fuel injector manifold for a turbine engine

Abstract

A fuel injector manifold for a turbine engine includes a fuel manifold ring, a plurality of fuel injectors, and a variable fuel flow system. A fuel manifold flow path is within the fuel manifold ring, the fuel manifold flow path receiving fuel therein. The plurality of fuel injectors are in fluid communication with the fuel manifold flow path, each of the plurality of fuel injectors having one or more fuel injector flow paths. The variable fuel flow system is disposed within the fuel manifold flow path, the variable fuel flow system including a closed state, a partially open state, and a fully open state to vary a flow of fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors.

Description

Technical Field

[0001] This disclosure generally relates to fuel injector manifolds for turbine engines, particularly for turbine engines used in aircraft. Background Technology

[0002] Turbine engines typically include propellers (e.g., fans or propellers) arranged in fluid communication with each other, and turbocharged engines. A turbocharged engine includes a compressor section, a combustor, and a turbine section. The combustor is arranged in the turbocharged engine to produce combustion gases for driving the turbine section. Attached Figure Description

[0003] Features and advantages will become apparent from the following more specific description of various exemplary embodiments as shown in the accompanying drawings, wherein similar reference numerals generally denote identical, functionally similar, or structurally similar elements.

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

[0005] Figure 2 It is based on this disclosure Figure 1 The section cut at point 2-2 in the middle Figure 1 A schematic rear view of the fuel injector manifold of a turbine engine.

[0006] Figure 3A It is based on this disclosure Figure 2 The section cut at point 3A-3A in the middle Figure 2 A schematic cross-sectional view of the fuel injector manifold.

[0007] Figure 3B It is based on this disclosure Figure 3A The section cut at point 3B-3B in the middle Figure 3A A schematic partial cross-sectional view of the fuel injector manifold.

[0008] Figure 3C Based on this disclosure Figure 3A A schematic partial cross-sectional view of the fuel injector manifold.

[0009] Figure 4A It is based on this disclosure Figure 3A Details captured at point 4A Figure 3A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0010] Figure 4B It is based on this disclosure Figure 3A The section cut at point 4B-4B in the middle Figure 3A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0011] Figure 5A Based on this disclosure Figure 4A A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0012] Figure 5B It is based on this disclosure Figure 3A Details captured at point 5B Figure 3A A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0013] Figure 6A Based on this disclosure Figure 4A and Figure 5A A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0014] Figure 6B Based on this disclosure Figure 5B A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0015] Figure 7 This is a schematic partial cross-sectional view of a variable fuel flow system for a fuel injector manifold, taken along the longitudinal centerline axis of the fuel injector manifold according to another embodiment.

[0016] Figure 8 This is a schematic partial cross-sectional view of a variable fuel flow system for a fuel injector manifold, taken along the transverse centerline axis of the fuel injector manifold according to another embodiment.

[0017] Figure 9A This is a schematic partial cross-sectional view of the fuel injector manifold taken along the transverse centerline axis of the fuel injector manifold according to another embodiment.

[0018] Figure 9B It is based on this disclosure Figure 9A The section cut at point 9B-9B in the middle Figure 9A A schematic partial cross-sectional view of the fuel injector manifold.

[0019] Figure 10A It is based on this disclosure Figure 9A Details captured at point 10A Figure 9AA schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0020] Figure 10B It is based on this disclosure Figure 9A The section cut at point 10B-10B in the middle Figure 9A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0021] Figure 11A Based on this disclosure Figure 10A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0022] Figure 11B Based on this disclosure Figure 10B A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0023] Figure 12A Based on this disclosure Figure 10A and Figure 11A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0024] Figure 12B Based on this disclosure Figure 10B and Figure 11B A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0025] Figure 13 It is a section taken along the transverse centerline axis of the fuel injector manifold according to another embodiment for use Figure 9A A schematic partial cross-sectional view of a variable fuel flow system in a fuel manifold.

[0026] Figure 14A This is a schematic partial cross-sectional view of the fuel injector manifold taken along the transverse centerline axis of the fuel injector manifold according to another embodiment.

[0027] Figure 14B It is based on this disclosure Figure 14A Details captured at point 14B Figure 14A A schematic partial cross-sectional view of the fuel injector manifold.

[0028] Figure 14C It is based on this disclosure Figure 14AThe section cut at point 14C-14C in the middle Figure 14A A schematic partial cross-sectional view of the fuel injector manifold.

[0029] Figure 15A Based on this disclosure Figure 14B A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0030] Figure 15B Based on this disclosure Figure 14C A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the off state.

[0031] Figure 16A Based on this disclosure Figure 14B A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0032] Figure 16B Based on this disclosure Figure 14C A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0033] Figure 17A Based on this disclosure Figure 14B A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0034] Figure 17B Based on this disclosure Figure 14C A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0035] Figure 18A This is a schematic partial cross-sectional view of the fuel injector manifold taken along the transverse centerline axis of the fuel injector manifold according to another embodiment.

[0036] Figure 18B It is in accordance with this disclosure along Figure 18A The section line 18B-18B in the middle is cut off Figure 18A A schematic partial cross-sectional view of the fuel injector manifold.

[0037] Figure 18C It is in accordance with this disclosure along Figure 18A The section line 18C-18C is cut from the section line. Figure 18A A schematic partial cross-sectional view of the fuel injector manifold.

[0038] Figure 19 Based on this disclosure Figure 18A A schematic partial cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in a partially open state.

[0039] Figure 20 Based on this disclosure Figure 18A A schematic cross-sectional view of a fuel injector manifold, wherein the variable fuel flow system of the fuel injector manifold is in the fully open state.

[0040] Figure 21 This is a schematic partial cross-sectional top view of a fuel injector manifold taken along the longitudinal axis of the fuel injector manifold according to another embodiment.

[0041] Figure 22 This is a schematic partial cross-sectional top view of a fuel injector manifold taken along the longitudinal axis of the fuel injector manifold according to another embodiment.

[0042] Figure 23 This is a schematic partial cross-sectional top view of a fuel injector manifold taken along the longitudinal axis of the fuel injector manifold according to another embodiment.

[0043] Figure 24 This is a schematic partial cross-sectional top view of a fuel injector manifold taken along the longitudinal axis of the fuel injector manifold according to another embodiment. Detailed Implementation

[0044] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation, without limiting the scope of the claimed disclosure.

[0045] Various embodiments of this disclosure are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from this disclosure.

[0046] As used herein, the terms “first,” “second,” and “third,” etc., are used interchangeably to distinguish one component from another and do not imply the position or importance of the components.

[0047] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0048] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and specifically to the normal operating posture of the turbine engine or carrier. For example, in a high-bypass turbine engine, "front" refers to the position closer to the engine inlet, and "rear" refers to the position closer to the engine nozzle or exhaust port. In one example, in a counter-flow turbine engine, "front" refers to the position closer to the engine nozzle or exhaust port, and "rear" refers to the position closer to the engine inlet.

[0049] Unless otherwise specified herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features.

[0050] Unless the context clearly indicates otherwise, the singular forms “a,” “one,” and “the” include plural references.

[0051] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the turbine engine.

[0052] As used herein, a "thruster" is a component of a turbine engine that is drivenly coupled to a turbocharged engine, such that rotation of components of the turbocharged engine causes the thruster to rotate and generate thrust. A thruster may include a fan or a propeller. In a turbofan engine, for example... Figure 1 In a turbine engine, the propulsion device is a fan. In a turboprop engine, the propulsion device is a propeller.

[0053] As used herein, the “off state” of a variable fuel flow system means that components of the variable fuel flow system cover one or more fuel injector flow paths to prevent fuel from flowing into one or more fuel injector flow paths.

[0054] As used in this article, a “partially open state” of a variable fuel flow system refers to a component of the variable fuel flow system partially covering and partially uncovering the fuel injector flow path, such that fuel flows through the partially uncovered fuel injector flow path.

[0055] As used herein, a “fully open state” for a variable fuel flow system means that the components of the variable fuel flow system are completely (e.g., all) uncovered from the fuel injector flow path, such that fuel flows through the completely uncovered fuel injector flow path.

[0056] As used throughout this specification and claims, approximate language is used to modify any quantitative representation that allows for variation without altering its underlying function. Therefore, values ​​modified by one or more terms (e.g., “about,” “approximate,” “roughly,” and “substantially”) are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component or system. For example, approximate language might refer to a margin of one percent, two percent, four percent, ten percent, fifteen percent, or twenty percent of a single value, a range of values, or the endpoints of a defined range of values.

[0057] A turbine engine has a fuel system that delivers fuel to a combustor, where the fuel is mixed with compressed air to produce combustion gases. The combustor in a turbine engine ignites the fuel-air mixture to produce combustion gases, which in turn drive one or more turbines in the turbine engine, thereby rotating one or more loads (e.g., fans, propellers, etc.). In turbine engines used in aircraft, the combustion gases are expelled from the turbine engine to generate thrust. Some turbine engines include a fuel injector manifold comprising a fuel manifold ring and multiple fuel injectors. The fuel manifold ring receives fuel from the fuel system and distributes it to the multiple fuel injectors, which then inject fuel into the combustor for mixing with air. Current fuel injector manifolds provide a fixed flow rate of fuel to the fuel injectors. Specifically, fuel flows through the fuel manifold ring and through an orifice associated with a corresponding one in each fuel injector. The orifice is of a fixed diameter, such that the area of ​​the orifice and the area of ​​the fuel flow path supplied to the fuel injector is constant during all operating conditions (e.g., engine start-up and during normal operation of the turbine engine).

[0058] During engine startup, fuel pressure is relatively low, and the pressure differential (delta pressure) between the fuel manifold rings and the multiple fuel injectors is low. Under these conditions, fuel and air may not atomize to produce a fuel mist, making it difficult to ignite the fuel-air mixture. Therefore, starting a turbocharged engine under low pressure differentials is challenging. Fuel atomization is also reduced when the fuel is cold (e.g., at high altitudes and low ambient temperatures) or if the type of fuel used has high viscosity.

[0059] Therefore, this disclosure provides a fuel injector manifold with a variable fuel flow system that alters the fuel flow to multiple fuel injectors to generate a higher pressure differential at or near the injection point during all operating conditions of a turbine engine. Specifically, the variable fuel flow system includes one or more pistons and one or more actuation mechanisms coupled to the one or more pistons. The piston is disposed within a fuel manifold ring and includes orifices for guiding fuel from the fuel manifold ring through the piston and into the fuel injectors. The piston slides back and forth within the fuel manifold ring to open and close the orifices of the fuel injectors. As the piston slides back and forth, the orifices on the piston are partially or fully aligned with the orifices of the fuel injectors. This creates a variable inlet area of ​​the fuel injector orifices compared to fuel injector manifolds without this disclosure, for generating a higher pressure differential at the fuel injectors. The piston has a crosshole extending through the piston to create a pressure drop across the piston, thereby passively actuating the piston.

[0060] In some embodiments, one or more pistons include a single piston annularly arranged around a fuel manifold ring. In some embodiments, the piston includes a plurality of pistons, each disposed at a corresponding fuel injector. The orifices of the pistons can typically be circular, elliptical, slit, etc. These orifices can include a single orifice at each fuel injector or multiple orifices at each fuel injector. In some embodiments, a pressure atomizer is disposed within the fuel injector to assist in atomizing the fuel. In some embodiments, the actuation mechanism is a passive actuation mechanism (e.g., a spring, a memory material, etc.) for passively moving the piston. In some embodiments, the actuation mechanism is an active actuation mechanism (e.g., a hydraulic actuator, a pneumatic actuator, a mechanical actuator, etc.) controlled to move the piston.

[0061] Therefore, compared to turbine engines without the benefits of this disclosure, the variable fuel flow system regulates the pressure differential between the fuel manifold rings and multiple fuel injectors to ensure a high pressure differential for increased fuel and air atomization. This increases the momentum of the fuel jet from the fuel injectors to improve fuel and air atomization and mixing, thereby making the fuel and air mixture easier to ignite and burn compared to turbine engines without the benefits of this disclosure. In this way, the variable fuel flow system provides improved ignition capability by increasing fuel and air atomization, particularly for cold fuels (e.g., at higher altitudes) or high-viscosity fuels. Compared to turbine engines without the benefits of this disclosure, this results in improved sub-idle and low-power burner efficiency due to the increased atomization, and less smoke is produced during high-power operation.

[0062] Now refer to the attached diagram, Figure 1This is a schematic cross-sectional view of the turbine engine 10 taken along the longitudinal centerline axis 12 of the turbine engine 10 according to an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 10 defines an axial direction A extending parallel to the longitudinal centerline axis 12, a radial direction R orthogonal to the axial direction A, and a circumferential direction C extending in an arc around the longitudinal centerline axis 12. Figure 1 In the orientation, the portion of the turbine engine 10 above the longitudinal centerline axis 12 is called the top portion 11, and the portion of the turbine engine 10 below the longitudinal centerline axis 12 is called the bottom portion 13.

[0063] Typically, the turbine engine 10 includes a propeller section 14 and a turbocharger engine 16 disposed downstream of the propeller section 14. The turbocharger engine 16 includes a compressor section 21, a combustor 26, and a turbine section 27 in a series flow relationship. The turbocharger engine 16 is substantially enclosed within a housing 18, which is substantially tubular and defines a core inlet 20 that is annular about a longitudinal centerline axis 12. Figure 1 As schematically shown, compressor section 21 includes a turbocharger or low-pressure (LP) compressor 22, downstream of which a high-pressure (HP) compressor 24 follows. Combustion 26 is located downstream of compressor section 21. Turbine section 27 is located downstream of combustor 26 and includes a high-pressure (HP) turbine 28, downstream of which a low-pressure (LP) turbine 30 follows. The turbocharged engine 16 also includes an exhaust nozzle section 32, a high-pressure (HP) shaft 34, and a low-pressure (LP) shaft 36 located downstream of turbine section 27. HP shaft 34 drivesly connects HP turbine 28 to HP compressor 24, and HP compressor 24, HP turbine 28, and HP shaft 34 together are referred to as the HP spool. HP turbine 28 and HP compressor 24 rotate synchronously via HP shaft 34. LP shaft 36 drivesly connects LP turbine 30 to LP compressor 22, and LP compressor 22, LP turbine 30, and LP shaft 36 together are referred to as the LP spool. LP turbine 30 and LP compressor 22 rotate synchronously via LP shaft 36. Compressor section 21, burner 26, turbine section 27 and injection exhaust nozzle section 32 together define the core airflow path.

[0064] for Figure 1 In the illustrated embodiment, thruster section 14 includes a thruster 38 (e.g., a variable pitch thruster) having a plurality of thruster blades 40 spaced apart and coupled to disk 42. Figure 1In this configuration, the thruster 38 is a fan, and the thruster blades 40 are fan blades. The thruster blades 40 typically extend outward from the disk 42 along a radial direction R. In the case of a variable-pitch thruster, multiple thruster blades 40 are operably coupled to an actuating member 44 by means of the thruster blades 40, enabling them to rotate relative to the disk 42 about a pitch axis P. The actuating member 44 is configured to collectively and uniformly change the pitch of the thruster blades 40. The thruster blades 40, disk 42, and actuating member 44 are rotatable together about a longitudinal centerline axis 12 via a thruster shaft 45, which is powered by an LP shaft 36 across a power gearbox (also called a gearbox assembly 46) (e.g., the turbine engine 10 is an indirect-drive engine). In this way, the thruster 38 is drivenly coupled to and powered by the turbocharged engine 16. The gearbox assembly 46 is located in... Figure 1 The diagram is schematically shown. Gearbox assembly 46 is a reduction gearbox assembly used to regulate the rotational speed of the propeller shaft 45 as power is transmitted from the LP shaft 36 to the propeller shaft 45, thereby regulating the rotational speed of the propeller 38 relative to the LP shaft 36.

[0065] Still referencing Figure 1 In an exemplary embodiment, the disk 42 is covered by a thruster hub 48 having an aerodynamic profile to facilitate airflow through a plurality of thruster blades 40. Furthermore, the thruster section 14 includes an annular thruster housing or nacelle 50 circumferentially surrounding at least a portion of the thruster 38 and the turbocharged engine 16. The nacelle 50 is supported relative to the turbocharged engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced around the nacelle 50 and the turbocharged engine 16. Additionally, a downstream section 54 of the nacelle 50 extends above the outer portion of the turbocharged engine 16 and, together with the housing 18, defines a bypass airflow passage 56 therebetween.

[0066] During the operation of the turbine engine 10, a volume of air 58 enters the turbine engine 10 through the nacelle 50 or the inlet 60 of the propeller section 14. As the volume of air 58 passes through the propeller blades 40, a first portion of the air (also referred to as bypass air 62) is directed into the bypass airflow passage 56. Simultaneously, a second portion of air (also referred to as core air 64) is directed into the upstream section of the core airflow path through the core inlet 20 of the LP compressor 22. The pressure of the core air 64 is then increased by the LP compressor 22 to produce compressed air 65. The compressed air 65 is directed through the HP compressor 24, where its pressure is further increased. The compressed air 65 is then directed into the combustor 26, where it is mixed with fuel 67 and ignited to produce combustion gases 66.

[0067] Combustion gas 66 is directed into and expanded in HP turbine 28, where a portion of the thermal or kinetic energy from combustion gas 66 is extracted via one or more stages of HP turbine stator blades 68 and HP turbine rotor blades 70 connected to HP shaft 34. This causes HP shaft 34 to rotate, thereby supporting the operation of HP compressor 24 (self-sustaining cycle). In this way, combustion gas 66 performs work on HP turbine 28. Combustion gas 66 is then directed into and expanded in LP turbine 30. Here, a second portion of thermal or kinetic energy is extracted from combustion gas 66 via one or more stages of LP turbine stator blades 72 and LP turbine rotor blades 74 connected to LP shaft 36. This causes LP shaft 36 to rotate, thereby supporting the operation of LP compressor 22 (self-sustaining cycle) and the rotation of propeller 38 via gearbox assembly 46 through LP shaft 36. In this way, combustion gas 66 performs work on LP turbine 30.

[0068] Combustion gas 66 is then directed through the injector exhaust nozzle section 32 of the turbocharged engine 16 to provide propulsive thrust. Simultaneously, bypass air 62 is directed through bypass airflow passage 56 before exiting from the propeller nozzle exhaust section 76 of the turbocharged engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injector exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through the turbocharged engine 16.

[0069] As described above, core air 64 (e.g., compressed air 65) is mixed with fuel 67 in combustor 26 to produce combustion gases 66. The turbine engine 10 also includes a fuel system 80 for supplying fuel 67 to combustor 26. Fuel system 80 includes a fuel tank (not shown) for storing fuel 67 therein and one or more fuel supply lines 82 for supplying fuel 67 to combustor 26. Fuel system 80 may include one or more valves for controlling the amount of fuel 67 supplied to combustor 26. Fuel 67 can be any type of fuel used in a turbine engine, including liquid or gaseous fuels. For example, fuel 67 can be JetA, sustainable aviation fuel (SAF) including biofuels, hydrogen-based fuel (H2), etc. Turbine engine 10 also includes a fuel injector manifold 100. Fuel system 80 supplies fuel 67 to fuel injector manifold 100, and fuel injector manifold 100 distributes fuel 67 to a plurality of fuel injectors for injecting fuel 67 into combustor 26, as described in further detail below.

[0070] Figure 1The turbine engine 10 shown is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the thruster 38 may be configured in any other suitable manner (e.g., as a fixed-pitch thruster) and may also be supported using any other suitable thruster frame configuration. The turbine engine 10 may also be a direct-drive engine without a power gearbox. For a direct-drive engine, the thruster speed is the same as the LP shaft speed. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In some other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, propeller fan engine, turbojet engine, turboprop engine, or turboshaft engine.

[0071] Figure 2 It is based on this disclosure Figure 1 The turbine engine 10 (section line 2-2) is cut off at the cross section line 2-2. Figure 1 A schematic cross-sectional view of a fuel injector manifold 100. The fuel injector manifold 100 includes a fuel manifold ring 102 that is annular about a longitudinal centerline axis 12. The fuel manifold ring 102 defines a fuel manifold flow path 104 within the fuel manifold ring 102. The fuel manifold flow path 104 is annular about a longitudinal centerline axis 12. The fuel injector manifold 100 also includes a fuel manifold inlet 106. The fuel manifold inlet 106 defines a fuel manifold inlet flow path 108 within the fuel manifold inlet 106. The fuel manifold inlet flow path 108 passes through one or more fuel supply lines 82 ( Figure 1 ) and fuel system 80 ( Figure 1 It is in fluid communication with, and in fluid communication with, fuel manifold flow path 104. Although Figure 2 The diagram shows a fuel manifold inlet 106, but the fuel injector manifold 100 may include any number of fuel manifold inlets 106 for supplying fuel 67 to the fuel manifold flow path 104.

[0072] The fuel injector manifold 100 includes a plurality of fuel injectors 110. The plurality of fuel injectors 110 are connected to the fuel manifold flow path 104 and the burner 26. Figure 1 Fluid communication. Although Figure 2 The diagram shows twelve fuel injectors 110, but the fuel injector manifold 100 may include any number of fuel injectors 110 for injecting fuel 67 into the combustor 26. The plurality of fuel injectors 110 are circumferentially spaced around the fuel manifold annulus 102. The fuel injector manifold 100 is mounted around the combustor 26 such that the plurality of fuel injectors 110 are oriented to inject fuel 67 into the combustor 26. Figure 2In this configuration, a plurality of fuel injectors 110 are oriented to inject fuel 67 generally radially into the burner 26. In some embodiments, the plurality of fuel injectors 110 are oriented to inject fuel 67 generally axially into the burner 26. In some embodiments, the plurality of fuel injectors 110 are oriented relative to the circumferential direction C or relative to the axial direction A. Figure 1 The fuel injectors 110 are configured to inject fuel 67 generally radially into the burner 26, and some fuel injectors 110 are configured to inject fuel 67 generally axially into the burner 26.

[0073] During operation, the fuel system 80 ( Figure 1 ) through one or more fuel supply lines 82 ( Figure 1 Fuel 67 is supplied to the fuel injector manifold 100. Specifically, the fuel manifold inlet flow path 108 directs fuel 67 from one or more fuel supply lines 82 into the fuel manifold flow path 104. The fuel manifold flow path 104 circumferentially directs fuel 67 around the fuel manifold annulus 102. Each of the plurality of fuel injectors 110 directs fuel 67 from the fuel manifold flow path 104 to the combustor 26. Figure 1 In order to inject fuel 67 into burner 26. As discussed above, at burner 26, fuel 67 and compressed air 65 ( Figure 1 ) are mixed and ignited to produce combustion gases 66 ( Figure 1 The fuel injector manifold 100 includes a variable fuel flow system to change the flow rate of fuel 67 through the plurality of fuel injectors 110, as described in further detail below.

[0074] Figure 3A It is based on this disclosure Figure 2 A schematic cross-sectional view of the fuel injector manifold 100 taken at section line 3A-3A. Figure 3B It is based on this disclosure Figure 3A A schematic partial cross-sectional view of the fuel injector manifold 100 taken at section line 3B-3B. Figure 3C This is a schematic partial cross-sectional view of the fuel injector manifold 100. (See attached image.) Figure 3A and Figure 3C As shown, the fuel injector manifold 100 extends axially from the rear end 101 to the front end 103. The fuel injector manifold 100 includes a fuel manifold heat shield 112 that covers at least a portion of the fuel manifold ring 102. Figure 3A and Figure 3B For clarity Figure 3C(Removed from the middle). Specifically, the fuel manifold heat shield 112 surrounds the fuel manifold ring 102 substantially around its entire circumference. In this way, the fuel manifold heat shield 112 is positioned around the longitudinal centerline axis 12 ( Figure 2 The fuel manifold heat shield 112 protects the fuel manifold ring 102 from the burner 26 (in a ring shape). Figure 1 The thermal combustion gas 66 in ) Figure 1 The fuel manifold ring 102 includes a radially outer groove 134 and a radially inner groove 138. A first sealing member 136 is located within the radially outer groove 134, and a second sealing member 140 is located within the radially inner groove 138.

[0075] The fuel manifold ring 102 includes a plug 114 that closes the fuel manifold flow path 104 at the rear end 101 of the fuel manifold ring 102. The plug 114 is attached to the fuel manifold ring 102 after the variable fuel flow system 120 of the fuel injector manifold 100 has been assembled within the fuel manifold ring 102.

[0076] Each of the plurality of fuel injectors 110 includes a fuel manifold flow path 104 and a burner 26 ( Figure 1 The orifice is in fluid communication, also referred to as fuel injector flow path 116. Fuel injector flow path 116 extends through the fuel manifold annulus 102 at the respective fuel injector 110. In this way, each of the plurality of fuel injectors 110 injects fuel 67 into the combustor 26 through fuel injector flow path 116, as described in further detail below. Fuel injector flow path 116 extends through the radially inner portion of fuel manifold annulus 102, such that fuel injector flow path 116 is positioned radially inside fuel manifold flow path 104. Fuel injector flow path 116 is circular. In some embodiments, fuel injector flow path 116 is elliptical, is a slit, or may include any shape for guiding fuel 67 through it.

[0077] The fuel injector manifold 100 includes a variable fuel flow system 120 disposed within a fuel manifold annulus 102. Specifically, the variable fuel flow system 120 is disposed within a fuel manifold flow path 104 and alters the flow rate of fuel 67 through a plurality of fuel injectors 110, as described in further detail below. The variable fuel flow system 120 includes a piston 122 and an actuation mechanism 124 for moving the piston 122. The piston 122 is annular and extends circumferentially around the fuel manifold annulus 102 within the fuel manifold flow path 104. Specifically, the piston 122 is disposed within the fuel manifold flow path 104 upstream (e.g., axially forward) of the fuel manifold inlet flow path 108. In this way, the piston 122 divides the fuel manifold flow path 104 into an upstream fuel manifold flow path 104a and a downstream fuel manifold flow path 104b. The upstream fuel manifold flow path 104a is located upstream of the piston 122, and the downstream fuel manifold flow path 104b is located downstream of the piston 122. Figure 3A In this configuration, the upstream fuel manifold flow path 104a is located behind the piston 122, and the downstream fuel manifold flow path 104b is located in front of the piston 122. However, the rear-to-front arrangement may be reversed.

[0078] Piston 122 is slidably coupled within fuel manifold ring 102 (e.g., in a fuel manifold flow path) such that piston 122 is generally axially movable within fuel manifold flow path 104. Specifically, piston 122 is axially forward and axially rearward movable between rear end 101 and front end 103. Piston 122 extends substantially radially over the entire radial height of fuel manifold flow path 104, defining a small gap or space between piston 122 and the inner surface of fuel manifold ring 102. In this way, piston 122 is movable relative to fuel manifold ring 102. In some embodiments, one or more seals are disposed within the small gap to seal the small gap between piston 122 and fuel manifold ring 102 and prevent fuel 67 from flowing through the small gap.

[0079] An actuation mechanism 124 is coupled to a piston 122 for moving the piston 122 within a fuel manifold flow path 104. The front end 103 of the fuel manifold ring 102 includes a recess 132. The front end of the actuation mechanism 124 is located within the recess 132. Figure 3A In this configuration, the actuation mechanism 124 is a spring, specifically a wave spring. In this way, the actuation mechanism 124 is a passive actuation mechanism for rearwardly biasing the piston 122. When the piston 122 moves forward, the actuation mechanism 124 contracts and stores potential energy. The actuation mechanism 124 releases the potential energy to cause the piston 122 to move axially rearward. Therefore, the piston 122 can be moved to change the flow rate of fuel 67 through the multiple fuel injectors 110, as described below regarding... Figures 4A to 6BFurther detailed description. The actuation mechanism 124 is annular about the fuel injector manifold 100. In some embodiments, the variable fuel flow system 120 includes a plurality of actuation mechanisms 124 circumferentially spaced about the fuel injector manifold 100. The actuation mechanism 124 can be any actuation mechanism described in detail herein.

[0080] Piston 122 includes one or more piston flow paths 126, 128, and 130, including one or more first piston flow paths 126, one or more second piston flow paths 128, and one or more third piston flow paths 130. The one or more first piston flow paths 126 extend substantially axially through piston 122 from its rear end 101 to its front end 103. In this way, the one or more first piston flow paths 126 provide fluid communication through piston 122 from an upstream fuel manifold flow path 104a to a downstream fuel manifold flow path 104b. The one or more first piston flow paths 126 are located at a radially outward portion of piston 122. The one or more first piston flow paths 126 are circumferentially spaced around piston 122. Although... Figure 3A The diagram shows a first piston flow path 126, but as needed, one or more first piston flow paths 126 may include any number of first piston flow paths 126 for guiding fuel 67 from upstream fuel manifold flow path 104a to downstream fuel manifold flow path 104b.

[0081] One or more second piston flow paths 128 extend substantially axially through piston 122 from its front end 103 toward its rear end 101. One or more second piston flow paths 128 are in fluid communication with downstream fuel manifold flow path 104b. One or more second piston flow paths 128 do not extend through the rear end 101 of piston 122, such that one or more second piston flow paths 128 are not in fluid communication with upstream fuel manifold flow path 104a. One or more second piston flow paths 128 are located at a radially inward portion of piston 122. Figure 3B As shown, one or more second piston flow paths 128 are circumferentially spaced around the piston 122. Figure 3B In this configuration, one or more second piston flow paths 128 include two second piston flow paths 128 for each of the plurality of fuel injectors 110. As needed, one or more second piston flow paths 128 may include any number of second piston flow paths 128 for guiding fuel 67 from a downstream fuel manifold flow path 104b to one or more third piston flow paths 130.

[0082] One or more third piston flow paths 130 extend substantially radially through the piston 122 from one or more second piston flow paths 128 to the radially inner surface of the piston 122. In this way, the one or more third piston flow paths 130 are in fluid communication with one or more second piston flow paths 128 and selectively in fluid communication with the fuel injector flow path 116 of the corresponding fuel injector 110. The one or more third piston flow paths 130 ( Figure 3A and Figure 3C This includes a single third piston flow path 130 that is annular around the piston 122. In some embodiments, one or more third piston flow paths 130 may include discrete flow paths circumferentially spaced around the piston 122. As needed, one or more third piston flow paths 130 may include any number of third piston flow paths 130 for guiding fuel 67 from one or more second piston flow paths 128 to fuel injector flow paths 116 of each of the plurality of fuel injectors 110.

[0083] Figure 4A It is based on this disclosure Figure 3A The schematic cross-sectional view of the fuel injector manifold 100 taken at detail 4A, wherein the variable fuel flow system 120 is in the off state. Figure 5A and Figure 6A Based on this disclosure Figure 4A A schematic cross-sectional view of the fuel injector manifold 100, wherein the variable fuel flow system 120 is in a partially open state. Figure 5A ) and fully open state ( Figure 6A ). Figure 4B Is Figure 3A A schematic cross-sectional view of the fuel injector manifold 100 taken at section line 4B-4B, wherein the variable fuel flow system 120 is in the off state. Figure 5B Is Figure 3A A schematic cross-sectional view of the fuel injector manifold 100 taken at detail 4A, in which the variable fuel flow system 120 is partially open. Figure 6B Based on this disclosure Figure 5B A schematic cross-sectional view of the fuel injector manifold 100, wherein the variable fuel flow system 120 is in the fully open state.

[0084] Now refer to Figure 3A , 4A 4B, 5A, 5B, 6A, and 6B describe the operation of the fuel injector manifold 100. When there is no fuel 67 flow or a very small amount of fuel 67 flow into the fuel injector manifold 100, the variable fuel flow system 120 is in the off state. Figure 4A and Figure 4BThis causes piston 122 to cover fuel injector flow path 116, and no fuel 67 flows through fuel injector flow path 116. Specifically, one or more third piston flow paths 130 are axially offset from fuel injector flow path 116. As described above, in operation, fuel manifold inlet flow path 108 draws fuel 67 from fuel system 80 (… Figure 1 One or more fuel supply pipelines 82 ( Figure 1 Fuel 67 is directed into the fuel manifold flow path 104. Specifically, fuel 67 flows into the upstream fuel manifold flow path 104a. Once fuel 67 fills the upstream fuel manifold flow path 104a into one or more first piston flow paths 126, the one or more first piston flow paths 126 guide fuel 67 from the upstream fuel manifold flow path 104a to the downstream fuel manifold flow path 104b. In this way, fuel 67 fills the downstream fuel manifold flow path 104b.

[0085] As fuel 67 continues to flow into the upstream fuel manifold flow path 104a, the pressure of the fuel 67 in the upstream fuel manifold flow path 104a acts on the piston 122, causing the piston 122 to move toward the front end 103 of the fuel injector manifold 100. The pressure of the fuel 67 in the upstream fuel manifold flow path 104a is greater than the pressure of the fuel 67 in the downstream fuel manifold flow path 104b. In this way, the fuel 67 in the upstream fuel manifold flow path 104a exerts a force on the piston 122, and this force overcomes the actuation mechanism 124. This causes the piston 122 to move toward the front end 103. As the piston 122 moves toward the front end 103, one or more third piston flow paths 130 begin to align with the fuel injector flow path 116, such that the piston 122 partially does not cover the fuel injector flow path 116. When one or more third piston flow paths 130 are partially aligned with the fuel injector flow path 116, the variable fuel flow system 120 is in a partially open state. Figure 5A and Figure 5B And one or more third piston flow paths 130 guide a portion of fuel 67 into fuel injector flow path 116. Fuel injector flow path 116 guides a portion of fuel 67 through it to inject that portion of fuel 67 into combustor 26. Figure 1 Therefore, due to the partial alignment of one or more third piston flow paths 130 and fuel injector flow paths 116, the variable fuel flow system 120 generates a high pressure differential across the fuel injector flow paths 116, even at low fuel 67 flow rates. This helps to atomize the fuel 67 into a fine mist during turbine engine 10 startup, when the fuel 67 is cold (e.g., at high altitudes or low ambient temperatures), and when the fuel 67 has a high viscosity.

[0086] As fuel 67 continues to flow into the upstream fuel manifold flow path 104 (e.g., during higher power operation, when fuel pressure is higher), fuel 67 continues to push piston 122 toward front end 103. This causes one or more third piston flow paths 130 to be fully aligned with fuel injector flow path 116, such that piston 122 is completely uncovered from fuel injector flow path 116. In this way, the variable fuel flow system 120 is in a fully open state. Figure 6A and Figure 6B Furthermore, compared to the partially open state, more fuel 67 is injected through the fuel injector flow path 116. Therefore, the variable fuel flow system 120 provides a variable inlet area for the fuel injector flow path 116 to generate a high pressure differential across the fuel injector flow path 116 under all operating conditions and atomize the fuel 67 into a fine mist.

[0087] Figure 7 It is a section taken along the longitudinal centerline axis of the fuel injector manifold 100 according to another embodiment for the fuel injector manifold 100 ( Figure 2 A schematic partial cross-sectional view of a variable fuel flow system 220. The variable fuel flow system 220 is substantially similar to... Figures 3A to 6B The variable fuel flow system 120. The same reference numerals will be used for components of the variable fuel flow system 220 that are the same as or similar to those of the variable fuel flow system 120 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0088] The variable fuel flow system 220 includes a fuel injector 210, which has different characteristics from... Figures 3A to 6B Fuel injector flow path 116 and fuel injector flow path 216. Specifically, fuel injector flow path 216 is set with a circumferential fuel injector flow path angle α relative to the transverse centerline axis 211 of the fuel injector manifold 100 in the circumferential direction C. Specifically, the transverse centerline axis 217 of fuel injector flow path 216 is set with a circumferential fuel injector flow path angle α relative to the transverse centerline axis 211. The circumferential fuel injector flow path angle α is non-zero. For example, the circumferential fuel injector flow path angle α can be greater than or less than zero. In some embodiments, the circumferential fuel injector flow path angle α is in the range of -60 degrees to 60 degrees. In operation, fuel injector flow path 216 injects fuel 67 into burner 26 at a circumferential fuel injector flow path angle α. Figure 1 )middle.

[0089] Figure 8It is a section taken along the transverse centerline axis of the fuel injector manifold 100 according to another embodiment for the fuel injector manifold 100 ( Figure 2 A schematic partial cross-sectional view of a variable fuel flow system 320. The variable fuel flow system 320 is substantially similar to... Figures 3A to 6B The variable fuel flow system 120. The same reference numerals will be used for components of the variable fuel flow system 320 that are the same as or similar to those of the variable fuel flow system 120 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0090] The variable fuel flow system 320 includes a fuel injector 310, which has a different... Figures 3A to 6B Fuel injector flow path 116 and fuel injector flow path 316. Specifically, fuel injector flow path 316 is configured in the axial direction A relative to the transverse centerline axis 311 of the fuel injector manifold 100 with an axial fuel injector flow path angle β. Specifically, the transverse centerline axis 317 of fuel injector flow path 316 is configured relative to the transverse centerline axis 311 with an axial fuel injector flow path angle β. The axial fuel injector flow path angle β is non-zero. For example, the axial fuel injector flow path angle β can be greater than or less than zero. In some embodiments, the axial fuel injector flow path angle β is in the range of -60 degrees to 60 degrees. In operation, fuel injector flow path 216 injects fuel 67 into burner 26 with an axial fuel injector flow path angle β. Figure 1 )middle.

[0091] Figure 9A This is a schematic partial cross-sectional view of the fuel injector manifold 400 taken along the transverse centerline axis of the fuel injector manifold 400 according to another embodiment. Figure 9B It is based on this disclosure Figure 9A A schematic partial cross-sectional view of the fuel injector manifold 400 taken at section line 9B-9B. The fuel injector manifold 400 is basically similar to... Figures 3A to 6B The same or similar reference numerals will be used for components of the same or similar fuel injector manifold 400 as those of the fuel injector manifold 100 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein.

[0092] Fuel injector manifold 400 extends axially between a rear end 401 and a front end 403. Fuel injector manifold 400 includes a fuel manifold ring 402, a fuel manifold flow path 404 having an upstream fuel manifold flow path 404a and a downstream fuel manifold flow path 404b, a fuel manifold inlet 406, a fuel manifold inlet flow path 408, a plurality of fuel injectors 410, a fuel manifold heat shield 412, a plug 414, and a variable fuel flow system 420. The plurality of fuel injectors 410 each include different... Figures 3A to 6B The fuel injector flow path 116 comprises multiple fuel injector flow paths 416, as described in further detail below. The variable fuel flow system 420 includes a piston 422, an actuation mechanism 424, and one or more piston flow paths 426, 428, and 430, including one or more first piston flow paths 426, one or more second piston flow paths 428, and one or more third piston flow paths 430. The multiple fuel injector flow paths 416 include elliptical flow paths. The multiple fuel injector flow paths 416 can be circular, slit-like, or any shape used to guide fuel 67 through them.

[0093] like Figure 9B As shown, the plurality of fuel injector flow paths 416 include a first fuel injector flow path 416a and a second fuel injector flow path 416b. The first fuel injector flow path 416a includes a first fuel injector flow path diameter d1, and the second fuel injector flow path 416b includes a second fuel injector flow path diameter d2. Figure 9BIn this configuration, the diameter d1 of the first fuel injector flow path is equal to that of the second fuel injector flow path 416b. In some embodiments, the diameter d1 of the first fuel injector flow path is greater than or less than the diameter d2 of the second fuel injector flow path. The first fuel injector flow path 416a and the second fuel injector flow path 416b are angled toward each other in the circumferential direction C. In this way, fuel 67 passing through the first fuel injector flow path 416a collides with fuel 67 passing through the second fuel injector flow path 416b to atomize the fuel 67 into a fine mist, and the fine mist of fuel 67 is ejected from each of the plurality of fuel injectors 410. In particular, the fuel 67 ejected from the first fuel injector flow path 416a and the second fuel injector flow path 416b combine to generate a fuel flow from each of the plurality of fuel injectors 410. The first fuel injector flow path 416a is positioned in the circumferential direction C relative to the transverse centerline axis 411 of the fuel injector manifold 400 at a first circumferential fuel injector angle α1. Specifically, the first lateral centerline axis 417a of the first fuel injector flow path 416a is set with a first circumferential fuel injector flow path angle α1 relative to the lateral centerline axis 411. The second fuel injector flow path 416b is set with a second circumferential fuel injector angle α2 relative to the lateral centerline axis 411 of the fuel injector manifold 400 in the circumferential direction C. Specifically, the second lateral centerline axis 417b of the second fuel injector flow path 416b is set with a second circumferential fuel injector flow path angle α2 relative to the lateral centerline axis 411.

[0094] The first circumferential fuel injector flow path angle α1 and the second circumferential fuel injector flow path angle α2 are non-zero (e.g., greater than or less than zero). Both the first circumferential fuel injector flow path angle α1 and the second circumferential fuel injector flow path angle α2 are in the range of ten to sixty degrees. The second circumferential fuel injector flow path angle α2 is opposite to the first circumferential fuel injector flow path angle α1, such that the first fuel injector flow path 416a and the second fuel injector flow path 416b are angled towards each other in the circumferential direction C. The first fuel injector flow path 416a is spaced apart from the second fuel injector flow path 416b in the circumferential direction C, such that the first lateral centerline axis 417a of the first fuel injector flow path 416a and the second lateral centerline axis 417b of the second fuel injector flow path 416b are offset by a circumferential distance δ, where δ can range from 1 / 2 (d1+d2) to 10 (d1+d2). The first circumferential fuel injector flow path angle α1, the second circumferential fuel injector flow path angle α2, and the circumferential distance δ of the fuel injector flow path are selected so that the fuel jets from the fuel injector 410 can collide with each other to enhance atomization, mixing with the airflow, or both atomization and mixing with the airflow.

[0095] Figure 10A Is Figure 9A The schematic cross-sectional view of the fuel injector manifold 400 taken at detail 10A, where the variable fuel flow system 420 is in the off state. Figure 11A and Figure 12A Based on this disclosure Figure 10A A schematic cross-sectional view of the fuel injector manifold 400, wherein the variable fuel flow system 420 is in a partially open state. Figure 11A ) and fully open state ( Figure 12A ). Figure 10B Is Figure 9A A schematic cross-sectional view of the fuel injector manifold 400 taken at section line 10B-10B, wherein the variable fuel flow system 420 is in the off state. Figure 11B and Figure 12B Based on this disclosure Figure 10B A schematic cross-sectional view of the fuel injector manifold 400, wherein the variable fuel flow system 420 is in a partially open state. Figure 11B ) and fully open state ( Figure 12B The operation of the fuel injector manifold 400 is as described in detail above. Figures 3A to 6B The fuel injector manifold 100 is essentially similar. When there is no or very little fuel flow 67, the variable fuel flow system 420 is in the off state ( Figure 10A and Figure 10B Start. Fuel injector manifold 400 ( Figure 9A ) guides fuel 67 through fuel manifold flow path 404 ( Figure 9B The variable fuel flow system 420 is in a partially open state when one or more third piston flow paths 430 are axially aligned with the flow paths 416 of the plurality of fuel injectors. Figure 11A and Figure 11B In this way, one or more third piston flow paths 430 direct a portion of fuel 67 into multiple fuel injector flow paths 416 (e.g., into a first fuel injector flow path 416a and a second fuel injector flow path 416b).

[0096] Multiple fuel injector flow paths 416 guide a portion of fuel 67 through them. Specifically, the first fuel injector flow path 416a has a first circumferential fuel injector flow path angle α1. Figure 9B ) guides a portion of fuel 67, and the second fuel injector flow path 416b is at a second fuel injector flow path angle α2 ( Figure 9BA portion of the fuel 67 is guided. In this way, the fuel 67 from the first fuel injector flow path 416a intersects with the fuel 67 from the second fuel injector flow path 416b to generate a fuel flow from each of the plurality of fuel injectors 410.

[0097] As fuel 67 continues to flow into the upstream fuel manifold flow path 404a ( Figure 9A Piston 422 moves such that one or more third piston flow paths 430 are fully aligned with the flow paths 416 of the multiple fuel injectors. In this way, the variable fuel flow system 420 is in the fully open state. Figure 12A and Figure 12B Furthermore, compared to the partially open state, more fuel 67 is injected through multiple fuel injector flow paths 416. Specifically, the first fuel injector flow path 416a is at a first circumferential fuel injector flow path angle α1. Figure 9B ) guides fuel 67, and the second fuel injector flow path 416b is at the second fuel injector flow path angle α2 ( Figure 9B A portion of the fuel 67 is guided. In this way, the fuel 67 from the first fuel injector flow path 416a intersects with the fuel 67 from the second fuel injector flow path 416b to generate a fuel flow from each of the plurality of fuel injectors 410.

[0098] Figure 13 It is a section taken along the transverse centerline axis of the fuel injector manifold 400 according to another embodiment for the fuel injector manifold 400 ( Figure 9A A schematic partial cross-sectional view of a variable fuel flow system 520. The variable fuel flow system 520 is substantially similar to... Figures 9A to 12B The variable fuel flow system 420. The same reference numerals will be used for components of a variable fuel flow system 520 that are the same as or similar to those of the variable fuel flow system 420 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components are omitted herein.

[0099] The variable fuel flow system 520 includes a fuel injector 510, which has different characteristics from... Figures 9A to 12BMultiple fuel injector flow paths 416 and multiple fuel injector flow paths 516. Specifically, each of the multiple fuel injector flow paths 516 is arranged in the axial direction A relative to the transverse centerline axis 511 of the fuel injector manifold 400 with an axial fuel injector flow path angle β. Specifically, the transverse centerline axis 517 of each of the multiple fuel injector flow paths 516 is arranged relative to the transverse centerline axis 511 with an axial fuel injector flow path angle β. The axial fuel injector flow path angle β is non-zero. For example, the axial fuel injector flow path angle β can be greater than or less than zero. In some embodiments, the axial fuel injector flow path angle β is in the range of -60 degrees to 60 degrees. In operation, each of the multiple fuel injector flow paths 516 injects fuel 67 into the burner 26 with an axial fuel injector flow path angle β. Figure 1 )middle.

[0100] Figure 14A This is a schematic partial cross-sectional view of the fuel injector manifold 600 taken along the transverse centerline axis of the fuel injector manifold 600 according to another embodiment. Figure 14B It is based on this disclosure Figure 14A A schematic partial cross-sectional view of the fuel injector manifold 600 taken at detail 14B. Figure 14C It is based on this disclosure Figure 14A A schematic partial cross-sectional view of the fuel injector manifold 600 taken at section line 14C-14C. The fuel injector manifold 600 is essentially similar to... Figures 3A to 6B The same or similar reference figures will be used with respect to the fuel injector manifold 100 described above. Figure 2 The components of the fuel injector manifold 600 are the same as or similar to those of the components described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted here.

[0101] Fuel injector manifold 600 extends axially between a rear end 601 and a front end 603. Fuel injector manifold 600 includes a fuel manifold ring 602, a fuel manifold flow path 604 having an upstream fuel manifold flow path 604a and a downstream fuel manifold flow path 604b, a fuel manifold inlet 606, a fuel manifold inlet flow path 608, a plurality of fuel injectors 610, a fuel manifold heat shield 612, a plug 614, and a variable fuel flow system 620. The plurality of fuel injectors 610 each include different... Figures 3A to 6BThe fuel injector flow path 616 of the fuel injector flow path 116 is described in further detail below. The variable fuel flow system 620 includes a piston 622, an actuation mechanism 624, and one or more piston flow paths 626, 628, and 630, including one or more first piston flow paths 626, one or more second piston flow paths 628, and one or more third piston flow paths 630. The fuel injector manifold 600 also includes a pressure atomizer 640, which atomizes fuel 67 into a fine mist and passes it through the fuel injector flow path 616.

[0102] like Figure 14B As shown, a pressure atomizer 640 is disposed within the atomizer chamber 641 of the fuel injector 610. The atomizer chamber 641 is radially disposed between the piston 622 and the fuel injector flow path 616. The fuel injector flow path 616 is a convergent-divergent flow path. Specifically, as the fuel injector flow path 616 extends from the radially outer end of the fuel injector 610 (e.g., closer to the end of the pressure atomizer 640) to the radially inner end (e.g., closer to the burner 26), the flow path 640 is further defined. Figure 1 At the end of the fuel injector, the flow path 616 is both converging and diverging.

[0103] like Figure 14B and Figure 14C As shown, the pressure atomizer 640 includes a plurality of atomizer flow paths 642 in fluid communication with one or more third piston flow paths 630 and fuel injector flow paths 616. The plurality of atomizer flow paths 642 include elliptical flow paths. The plurality of atomizer flow paths 642 can be circular, slit, or any shape used to guide fuel 67 through them.

[0104] Multiple atomizer flow paths 642 include a first atomizer flow path 642a and a second atomizer flow path 642b. The first atomizer flow path 642a is circumferentially spaced from the second atomizer flow path 642b in the circumferential direction C. The first atomizer flow path 642a is axially aligned with the second atomizer flow path 642b at the radially outer end of the pressure atomizer 640 (e.g., closer to the end of one or more third piston flow paths 630) in the axial direction A. The first atomizer flow path 642a and the second atomizer flow path 642b are angled away from each other in the axial direction A. Specifically, as the first atomizer flow path 642a extends from the radially outer end of the pressure atomizer 640 to the radially inner end of the pressure atomizer 640 (e.g., closer to the end of the fuel injector flow path 616), the first atomizer flow path 642a is axially angled rearward. As the second atomizer flow path 642b extends from the radially outer end to the radially inner end of the pressure atomizer 640, the second atomizer flow path 642b is angled forward axially. In this way, the first atomizer flow path 642a is axially spaced from the second atomizer flow path 642b in the axial direction A at the radially inner end of the pressure atomizer 640. An atomizer plug 644 is disposed within the atomizer cavity 641 and contacts the pressure atomizer 640 to prevent the pressure atomizer 640 from rotating during operation.

[0105] Figure 15A , 16A 17A is in accordance with this disclosure. Figure 14B A schematic cross-sectional view of the fuel injector manifold 600, wherein the variable fuel flow system 620 is in the off state. Figure 15A ), partially open state ( Figure 16A ) and fully open state ( Figure 17A ). Figure 15B , 16B 17B is pursuant to this disclosure. Figure 14C A schematic cross-sectional view of the fuel injector manifold 600, wherein the variable fuel flow system 620 is in the off state. Figure 15B ), partially open state ( Figure 16B ) and fully open state ( Figure 17B The operation of the fuel injector manifold 600 is as described in detail above. Figures 3A to 6B The fuel injector manifold 100 is essentially similar. When there is no or very little fuel flow 67, the variable fuel flow system 620 is in the off state ( Figure 15A and Figure 15BThe fuel injector manifold 600 directs fuel 67 through fuel manifold flow path 604 to push piston 622, and the variable fuel flow system 620 is in a partially open state when one or more third piston flow paths 630 are partially axially aligned with multiple atomizer flow paths 642. Figure 16A and Figure 16B In this manner, one or more third piston flow paths 430 guide a portion of fuel 67 into multiple atomizer flow paths 642 (e.g., into a first atomizer flow path 642a and a second atomizer flow path 642b). The multiple atomizer flow paths 642 guide fuel 67 into a fuel injector flow path 616. Fuel 67 is forced through the multiple atomizer flow paths 642 under high pressure to atomize it into a fine mist. The first atomizer flow path 642a guides fuel 67 axially rearward into the fuel injector flow path 616. The second atomizer flow path 642b guides fuel 67 axially forward into the fuel injector flow path 616. The fuel injector flow path 616 guides the fine mist of fuel 67 through it and into the burner 26. Figure 1 The convergent-divergent flow path of the fuel injector flow path 616 helps to generate high pressure for the fuel 67 to promote atomization of the fuel 67 as it flows through multiple atomizer flow paths 642.

[0106] As fuel 67 continues to flow into the upstream fuel manifold flow path 604a, piston 622 moves, causing one or more third piston flow paths 630 to fully align with multiple atomizer flow paths 642. In this way, the variable fuel flow system 620 is in a fully open state. Figure 17A and Figure 17B Compared to the partially open state, more fuel 67 is injected through multiple atomizer flow paths 642. Specifically, the first atomizer flow path 642a guides the fuel 67 axially rearward, and the second atomizer flow path 642b guides the fuel 67 axially forward into the fuel injector flow path 616. In this way, the pressure atomizer 640 atomizes the fuel 67 into a fine mist, and the fuel injector flow path 616 injects the fine mist into the burner 26. Figure 1 )middle.

[0107] Figure 18A This is a schematic partial cross-sectional view of the fuel injector manifold 700 taken along the transverse centerline axis of the fuel injector manifold 700 according to another embodiment. Figure 18B It is in accordance with this disclosure along Figure 18A A schematic partial cross-sectional view of the fuel injector manifold 700 taken from section line 18B-18B. Figure 18C It is in accordance with this disclosure along Figure 18AA schematic partial cross-sectional view of the fuel injector manifold 700, taken from section line 18C-18C. The fuel injector manifold 700 is essentially similar to... Figures 3A to 6B The same or similar reference numerals will be used for components of the same or similar fuel injector manifold 700 as those of the fuel injector manifold 100 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein.

[0108] Fuel injector manifold 700 extends axially between a rear end 701 and a front end 703. Fuel injector manifold 700 includes a fuel manifold ring 702, a fuel manifold flow path 704 having an upstream fuel manifold flow path 704a and one or more downstream fuel manifold flow paths 704b, a fuel manifold inlet 706, a fuel manifold inlet flow path 708, a plurality of fuel injectors 710, a fuel manifold heat shield 712, a plug 714, and a variable fuel flow system 720. The upstream fuel manifold flow path 704a is annular around the fuel manifold ring 702. The one or more downstream fuel manifold flow paths 704b are discrete flow paths and are in fluid communication with the upstream fuel manifold flow path 704a, and extend axially from the upstream fuel manifold flow path 704a toward the front end 703 of the fuel manifold ring 702. Figure 18B As shown, one or more downstream fuel manifold flow paths 704b include three downstream fuel manifold flow paths 704b circumferentially spaced around the piston 722. However, the one or more downstream fuel manifold flow paths 704b may include any number of downstream fuel manifold flow paths 704b. Multiple fuel injectors 710 each include a fuel injector flow path 716. The variable fuel flow system 720 differs from... Figures 3A to 6B Variable fuel flow system 120.

[0109] The variable fuel flow system 720 includes a plurality of pistons 722 and a plurality of piston chambers 723. The plurality of piston chambers 723 include discrete chambers defined in a fuel manifold ring 702 and are circumferentially spaced around the fuel manifold ring 702. The plurality of pistons 722 include discrete pistons (rather than annular pistons) and are circumferentially spaced around a fuel manifold flow path 704. Specifically, a corresponding one of the plurality of pistons 722 is associated with a corresponding one of the plurality of fuel injectors 710. The plurality of pistons 722 are disposed within the plurality of piston chambers 723. Specifically, a corresponding one of the plurality of pistons 722 is disposed within a corresponding one of the plurality of piston chambers 723.

[0110] The plurality of pistons 722 include one or more actuation mechanisms 724 and one or more piston flow paths 726. The actuation mechanism 724 is a spring, particularly a compression or tension spring. In this way, the actuation mechanism 724 is a passive actuation mechanism that rearwardly biases the corresponding piston 722. As the piston 722 moves forward, the actuation mechanism 724 contracts (e.g., compresses) and stores potential energy. The actuation mechanism 724 releases the potential energy to cause the corresponding piston 722 to move axially rearward. Thus, each of the plurality of pistons 722 can be moved to change the flow rate of fuel 67 through the plurality of fuel injectors 710. In some embodiments, the one or more actuation mechanisms 724 include one actuation mechanism 724 that is annular about the fuel injector manifold 700 and coupled to each of the plurality of pistons 722. In some embodiments, the one or more actuation mechanisms 724 include a plurality of actuation mechanisms 724, and a corresponding one of the actuation mechanisms 724 is coupled to a corresponding one of the plurality of pistons 722. Each of the plurality of actuation mechanisms 724 may have a different spring constant, or may move each of the plurality of pistons 722 at different rates. In this way, each of the plurality of pistons 722 may move at different rates to alter the circumferential delivery of fuel 67 around the fuel manifold ring 702 under different power conditions. The actuation mechanism 724 may be any actuation mechanism described in detail herein.

[0111] like Figure 18B As shown, one or more piston flow paths 726 are annular around a corresponding piston 722. One or more piston flow paths 726 are in fluid communication with one or more fuel manifold flow paths 704b. When the corresponding piston 722 moves and one or more piston flow paths 726 are partially or fully aligned with a fuel injector flow path 716, the one or more piston flow paths 726 are in fluid communication with the fuel injector flow path 716.

[0112] like Figure 18C As shown, the variable fuel flow system 720 also includes one or more seals 750 for sealing the space between the sides of the respective piston 722 and the fuel manifold ring 702. Specifically, the one or more seals 750 seal the respective piston chamber 723. The one or more seals 750 prevent fuel 67 from flowing through the space between the sides of the respective piston 722 and the fuel manifold ring 702 across the respective piston 722. In this way, the one or more seals 750 prevent fuel 67 from flowing into the respective piston chamber 723.

[0113] Figure 19 and Figure 20 This is a schematic cross-sectional view of the fuel injector manifold 700 according to the present disclosure, wherein the variable fuel flow system 720 is in a partially open state. Figure 19 ) and fully open state ( Figure 20 ). Figure 18A The variable fuel flow system 720 in the off state is shown. The operation of the fuel injector manifold 700 is as described in detail above. Figures 3A to 6B The fuel injector manifold 100 is essentially similar. When there is no or very little fuel flow 67, the variable fuel flow system 720 is in the off state ( Figure 18A The fuel injector manifold 700 directs fuel 67 through fuel manifold flow path 704 to actuate each of the plurality of pistons 722, and the variable fuel flow system 720 is in a partially open state when one or more piston flow paths 726 are partially axially aligned with fuel injector flow path 716. Figure 19 Specifically, one or more downstream fuel manifold flow paths 704b guide fuel 67 into one or more piston flow paths 726. The one or more piston flow paths 726 circumferentially guide fuel 67 around the one or more piston flow paths 726 and into the fuel injector flow path 716. In this way, the one or more piston flow paths 726 guide a portion of fuel 67 into the fuel injector flow path 716. The fuel injector flow path 716 guides a portion of fuel 67 through it to inject a portion of fuel 67 into the combustor 26. Figure 1 )middle.

[0114] As fuel 67 continues to flow into the upstream fuel manifold flow path 704a, each of the plurality of pistons 722 moves such that one or more piston flow paths 726 are fully aligned with the fuel injector flow path 716. In this way, the variable fuel flow system 720 is in the fully open state. Figure 20 Furthermore, compared to the partially open state, more fuel 67 is injected through the fuel injector flow path 716.

[0115] Figure 21 This is a schematic partial cross-sectional top view of the fuel injector manifold 800 taken along its longitudinal axis according to another embodiment. The fuel injector manifold 800 is substantially similar to... Figures 18A to 20 The fuel injector manifold 700. The same or similar reference numerals will be used for components of the same or similar fuel injector manifold 800 as those of the fuel injector manifold 700 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein. The fuel injector manifold 800 includes components different from... Figures 18A to 20The variable fuel flow system 720 includes a variable fuel flow system 820. The variable fuel flow system 820 includes a plurality of pistons 822, and each of the plurality of pistons 822 includes one or more actuating mechanisms 824. Actuating mechanism 824 differs from actuating mechanism 724. Actuating mechanism 824 is a wave spring, similar to... Figures 3A to 6B Actuating mechanism 124. Regarding... Figure 21 The variations described herein can be applied to any fuel injector manifold described herein.

[0116] Figure 22 This is a schematic partial cross-sectional top view of the fuel injector manifold 900 taken along its longitudinal axis according to another embodiment. The fuel injector manifold 900 is substantially similar to... Figures 18A to 20 The fuel injector manifold 700. The same or similar reference numerals will be used for components of the same or similar fuel injector manifold 900 as those of the fuel injector manifold 700 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein. The fuel injector manifold 900 includes components different from... Figures 18A to 20 The variable fuel flow system 720 includes a variable fuel flow system 920. The variable fuel flow system 920 includes a plurality of pistons 922 disposed within a plurality of piston chambers 923 and sealed by one or more seals 950. The plurality of pistons 922 includes one or more actuation mechanisms 924. The actuation mechanism 924 differs from the actuation mechanism 724. The actuation mechanism 924 is a leaf spring that compresses and expands to actuate the corresponding piston 922. In some embodiments, the actuation mechanism 924 includes a memory material (e.g., a temperature-sensitive material) that compresses and expands through thermal energy (e.g., as the temperature of the actuation mechanism 924 rises or falls). Regarding... Figure 22 The variations described herein can be applied to any fuel injector manifold described herein.

[0117] Figure 23 This is a schematic partial cross-sectional top view of the fuel injector manifold 1000 taken along its longitudinal axis according to another embodiment. The fuel injector manifold 1000 is substantially similar to... Figures 18A to 20The fuel injector manifold 700 includes many of the same or similar components as the fuel injector manifold 700, even though some components are not explicitly described in detail with respect to the fuel injector manifold 1000. The same or similar reference numerals will be used for components of the fuel injector manifold 1000 that are the same or similar to those of the fuel injector manifold 700 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein. The fuel injector manifold 1000 extends between a rear end 1001 and a front end 1003. The fuel injector manifold 1000 includes a fuel manifold ring 1002, a fuel manifold flow path 1004 including an upstream fuel manifold flow path 1004a, a plug 1014, and other components different from those described above. Figures 18A to 20 The variable fuel flow system 720 includes a variable fuel flow system 1020. The variable fuel flow system 1020 includes a plurality of pistons 1022 disposed within a plurality of piston chambers 1023 and sealed by one or more seals 1050. (Regarding...) Figure 23 The variations described herein can be applied to any fuel injector manifold described herein.

[0118] Multiple pistons 1022 include one or more actuation mechanisms 1024, different from actuation mechanism 724. Actuation mechanism 1024 includes an active actuation mechanism. Specifically, actuation mechanism 1024 is a fluid actuation mechanism (e.g., hydraulic or pneumatic actuation). Actuation mechanism 1024 includes pressurized fluid (e.g., hydraulic fluid, air, or gas) stored within pressurized fluid tank 1060. Actuation mechanism 1024 includes one or more fuel manifold actuation mechanism flow paths 1062 and one or more piston actuation mechanism flow paths 1064. One or more fuel manifold actuation mechanism flow paths 1062 extend through fuel manifold ring 1002 and provide fluid communication from pressurized fluid tank 1060 to one or more piston actuation mechanism flow paths 1064. Piston actuation mechanism flow paths 1064 extend through corresponding pistons 1022. Actuation mechanism seal 1070 is disposed around fuel manifold actuation mechanism flow path 1062 to seal fuel manifold actuation mechanism flow path 1062.

[0119] In operation, the actuation mechanism 1024 is controlled (e.g., by a controller) to move a plurality of pistons 1022 from a closed state to a partially open state and to a fully open state. Specifically, the controller controls the actuation mechanism 1024 to supply pressurized fluid from a pressurized fluid tank 1060 to one or more piston actuation mechanism flow paths 1064 via one or more fuel manifold actuation mechanism flow paths 1062, thereby pushing the plurality of pistons 1022 to the closed state. As fuel 67 flows through fuel manifold flow path 1004, the controller controls the actuation mechanism 1024 to retract pressurized fluid from one or more piston actuation mechanism flow paths 1064 back to pressurized fluid tank 1060. The pressure difference between the fuel 67 in the upstream fuel manifold flow path 1004a and the one or more piston actuation mechanism flow paths 1064 causes the plurality of pistons 1022 to move to the partially open state. As fuel 67 continues to flow through fuel manifold flow path 1004, the controller controls actuation mechanism 1024 to continue drawing pressurized fluid from one or more piston actuation mechanism flow paths 1064 back to pressurized fluid tank 1060. The pressure difference between the upstream fuel manifold flow path 1004a and the fuel 67 in one or more piston actuation mechanism flow paths 1064 causes multiple pistons 1022 to continue moving to the fully open state. Therefore, actuation mechanism 1024 is controlled to actively move multiple pistons 1022.

[0120] Figure 24 This is a schematic partial cross-sectional top view of the fuel injector manifold 1100 taken along its longitudinal axis according to another embodiment. The fuel injector manifold 1100 is substantially similar to... Figures 18A to 20 The fuel injector manifold 700 includes many of the same or similar components as described above, even if some components are not explicitly described in detail with respect to the fuel injector manifold 1100. The same or similar reference numerals will be used for components of the fuel injector manifold 1100 that are the same or similar to those of the fuel injector manifold 700 described above. The above description of these components also applies to this embodiment, and detailed descriptions of these components and their functions are omitted herein. The fuel injector manifold 1100 extends between a rear end 1101 and a front end 1103. The fuel injector manifold 1100 includes a fuel manifold ring 1102, a fuel manifold flow path 1104 including an upstream fuel manifold flow path 1104a, a plug 1114, and other components different from those described above. Figures 18A to 20 The variable fuel flow system 720 includes a variable fuel flow system 1120. The variable fuel flow system 1120 includes a plurality of pistons 1122 disposed within a plurality of piston chambers 1123 and sealed by one or more seals 1150. (Regarding...) Figure 24 The variations described herein can be applied to any fuel injector manifold described herein.

[0121] Multiple pistons 1122 include one or more actuation mechanisms 1124 different from actuation mechanism 724. Actuation mechanism 1124 includes an active actuation mechanism. Specifically, actuation mechanism 1124 is a mechanical actuation mechanism. Actuation mechanism 1124 includes an actuator 1160 having an actuator shaft 1162. Actuator 1160 can be any type of mechanical actuator, such as a solenoid actuator, hydraulic cylinder, etc., for providing linear actuation to actuator shaft 1162. Actuator shaft 1162 is coupled to a corresponding piston 1122. Actuator shaft 1162 includes an actuator shaft seal 1170 that seals piston chamber 1123 to prevent fuel 67 from flowing out of piston chamber 1123 around actuator shaft 1162.

[0122] In operation, the actuation mechanism 1124 is controlled (e.g., by a controller) to move a plurality of pistons 1122 from a closed state to a partially open state and to a fully open state. Specifically, the controller controls the actuator 1160 to move the actuator shaft 1162 axially, thereby pushing the plurality of pistons 1122 to the closed state. As fuel 67 flows through the fuel manifold flow path 1104, the controller controls the actuator 1160 to retract (e.g., pull) the actuator shaft 1162 and move the pistons 1122 to the partially open state. As fuel 67 continues to flow through the fuel manifold flow path 1104, the controller controls the actuator 1160 to continue retracting the actuator shaft 1162 and continue moving the pistons 1122 to the fully open state. Thus, the actuation mechanism 1124 is controlled to actively move the plurality of pistons 1122.

[0123] Therefore, compared to turbine engines without the benefits of this disclosure, the variable fuel flow system of this invention regulates the pressure differential between the fuel manifold rings and multiple fuel injectors to ensure a high pressure differential for increased fuel and air atomization. This increases the momentum of the fuel jet from the fuel injectors to improve fuel and air atomization and mixing, thereby making the fuel and air mixture easier to ignite and burn compared to turbine engines without the benefits of this disclosure. In this way, the variable fuel flow system provides improved ignition capability by increasing fuel and air atomization, particularly for cold fuels (e.g., at higher altitudes) or high-viscosity fuels. Compared to turbine engines without the benefits of this disclosure, this results in improved sub-idle and low-power efficiency of the combustor due to the increased atomization, and less smoke is produced during high-power operation.

[0124] Further aspects of this disclosure are provided by the subject matter of the following clauses.

[0125] A fuel injector manifold for a turbine engine includes: a fuel manifold ring defining a fuel manifold flow path within the fuel manifold ring, wherein the fuel manifold flow path receives fuel therein; a plurality of fuel injectors in fluid communication with the fuel manifold flow path, each of the plurality of fuel injectors having one or more fuel injector flow paths; and a variable fuel flow system disposed within the fuel manifold flow path, the variable fuel flow system including the closed state, the partially open state, and the fully open state, for changing the flow rate of fuel from the fuel manifold flow path to each of the plurality of fuel injectors via the one or more fuel injector flow paths.

[0126] According to the fuel injector manifold described in the foregoing clause, wherein the one or more fuel injector flow paths are configured with a circumferential fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the circumferential fuel injector flow path angle is non-zero.

[0127] According to any of the preceding clauses, the fuel injector manifold wherein the one or more fuel injector flow paths are configured with an axial fuel injector flow path angle relative to the lateral centerline axis, the axial fuel injector flow path angle being non-zero.

[0128] According to any of the preceding clauses, the fuel injector manifold, wherein the plurality of fuel injectors are oriented to inject fuel substantially radially from the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0129] According to any of the preceding clauses, the fuel injector manifold, wherein the variable fuel flow system includes one or more pistons disposed within the fuel manifold flow path, the one or more pistons moving between the closed state, the partially open state, and the fully open state to change the flow rate of the fuel in the one or more fuel injector flow paths to each of the plurality of fuel injectors.

[0130] According to any of the preceding clauses, each of the one or more pistons includes one or more piston flow paths in fluid communication with the fuel manifold flow path and the one or more fuel injector flow paths of each of the plurality of fuel injectors, the one or more piston flow paths guiding the fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0131] According to any of the preceding clauses, in a fuel injector manifold, wherein the one or more pistons divide the fuel manifold flow path into an upstream fuel manifold flow path and a downstream fuel manifold flow path, and the fuel flows from the upstream fuel manifold flow path into the downstream fuel manifold flow path, and through the one or more piston flow paths into the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0132] According to any of the preceding clauses, the fuel injector manifold, wherein the variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.

[0133] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuating mechanisms are passive actuating mechanisms.

[0134] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuating mechanisms are active actuating mechanisms.

[0135] According to any of the preceding clauses, the fuel injector manifold, wherein the turbine engine defines an axial direction, a radial direction, and a circumferential direction.

[0136] The fuel injector manifold according to any of the foregoing clauses further includes a fuel manifold inlet having a fuel manifold inlet flow path in fluid communication with the fuel manifold flow path, the fuel manifold inlet flow path supplying fuel to the fuel manifold flow path.

[0137] According to any of the preceding clauses, the fuel injector manifold, wherein the turbine engine includes a fuel system in fluid communication with the fuel manifold inlet flow path, and the fuel system supplies fuel from the fuel system to the fuel manifold flow path via the fuel manifold inlet flow path.

[0138] According to any of the preceding clauses, the fuel injector manifold, wherein the plurality of fuel injectors are circumferentially spaced around the fuel manifold.

[0139] The fuel injector manifold according to any of the foregoing clauses further includes a fuel manifold heat shield covering at least a portion of the fuel manifold ring.

[0140] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more piston flow paths include one or more first piston flow paths, one or more second piston flow paths, and one or more third piston flow paths.

[0141] According to any of the preceding clauses, in a fuel injector manifold, wherein the one or more first piston flow paths are in fluid communication with the upstream fuel manifold flow path and the downstream fuel manifold flow path, and the one or more first piston flow paths guide the fuel from the upstream fuel manifold flow path to the downstream fuel manifold flow path.

[0142] According to any of the preceding clauses, in a fuel injector manifold, wherein the one or more second piston flow paths are in fluid communication with the downstream fuel manifold flow path and the one or more third piston flow paths, the one or more second piston flow paths guiding the fuel from the downstream fuel manifold flow path to the one or more third piston flow paths.

[0143] According to any of the preceding clauses, in a fuel injector manifold, wherein the one or more third piston flow paths are in fluid communication with the one or more second piston flow paths and the one or more fuel injector flow paths, and the one or more third piston flow paths guide the fuel from the one or more second piston flow paths to the one or more fuel injector flow paths.

[0144] According to any of the preceding clauses, the fuel injector manifold wherein, when the variable fuel flow system is in the closed state, the flow path of the one or more third pistons is not aligned with the flow path of the one or more fuel injectors.

[0145] According to any of the preceding clauses, the fuel injector manifold wherein, when the variable fuel flow system is in the partially open state, the one or more third piston flow paths are partially aligned with the one or more fuel injector flow paths.

[0146] According to any of the preceding clauses, the fuel injector manifold wherein, when the variable fuel flow system is in the fully open state, the one or more third piston flow paths are fully aligned with the one or more fuel injector flow paths.

[0147] According to any of the preceding clauses, the fuel injector manifold includes one or more pistons that are annular around the fuel manifold ring within the fuel manifold flow path.

[0148] According to any of the preceding clauses, the fuel injector manifold, wherein the upstream fuel manifold flow path is located upstream of the one or more pistons.

[0149] According to any of the preceding clauses, the fuel injector manifold, wherein the downstream fuel manifold flow path is located downstream of the one or more pistons.

[0150] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more fuel injector flow paths of each of the plurality of fuel injectors comprise a single fuel injector flow path.

[0151] According to any of the preceding clauses, the fuel injector manifold, wherein the flow path of the one or more fuel injectors is circular.

[0152] According to any of the preceding clauses, the fuel injector manifold wherein one or more pistons move axially forward and axially backward within the fuel manifold flow path.

[0153] According to any of the preceding clauses, the fuel injector manifold, wherein the circumferential fuel injector flow path angle is in the range of -60 degrees to 60 degrees.

[0154] According to any of the preceding clauses, the fuel injector manifold, wherein the axial fuel injector flow path angle is in the range of -60 degrees to 60 degrees.

[0155] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more fuel injector flow paths of each of the plurality of fuel injectors include a first fuel injector flow path and a second fuel injector flow path.

[0156] According to any of the preceding clauses, the first fuel injector flow path includes a first fuel injector flow path diameter, and the second fuel injector flow path includes a second fuel injector flow path diameter.

[0157] According to any of the preceding clauses, the fuel injector manifold wherein the diameter of the first fuel injector flow path is equal to the diameter of the second fuel injector flow path.

[0158] According to any of the preceding clauses, the fuel injector manifold wherein the diameter of the first fuel injector flow path is greater than or less than the diameter of the second fuel injector flow path.

[0159] According to any of the preceding clauses, the first fuel injector flow path and the second fuel injector flow path are angled toward each other in the circumferential direction such that the fuel passing through the first fuel injector flow path impinges on the fuel from the second fuel injector flow path to atomize the fuel.

[0160] According to any of the preceding clauses, the first fuel injector flow path is arranged with a first circumferential fuel injector angle relative to the transverse centerline axis in the circumferential direction.

[0161] According to any of the preceding clauses, the second fuel injector flow path is arranged at a second circumferential fuel injector angle relative to the transverse centerline axis in the circumferential direction.

[0162] According to any of the preceding clauses, the fuel injector manifold, wherein the first circumferential fuel injector flow path angle and the second circumferential fuel injector flow path angle are non-zero.

[0163] According to any of the preceding clauses, the fuel injector manifold, wherein each of the first circumferential fuel injector flow path angle and the second circumferential fuel injector flow path angle is in the range of 10 degrees to 60 degrees.

[0164] According to any of the preceding clauses, the second circumferential fuel injector flow path angle is opposite to the first circumferential fuel injector flow path angle, such that the first circumferential fuel injector flow path and the second circumferential fuel injector flow path are angled toward each other in the circumferential direction.

[0165] According to any of the preceding clauses, the first fuel injector flow path is spaced apart from the second fuel injector flow path in the circumferential direction such that the first transverse centerline axis of the first fuel injector flow path is offset from the second transverse centerline axis of the second fuel injector flow path by a circumferential distance.

[0166] According to any of the preceding clauses, the first fuel injector flow path and the second fuel injector flow path are configured with an axial fuel injector flow path angle relative to the axial direction, and the axial fuel injector flow path angle is non-zero.

[0167] According to any of the preceding clauses, the fuel injector manifold, wherein the flow path of the one or more fuel injectors is elliptical.

[0168] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more fuel injector flow paths are slits.

[0169] The fuel injector manifold according to any of the foregoing clauses further includes a pressure atomizer disposed within an atomizer chamber, the atomizer chamber being radially located between the one or more pistons and the one or more fuel injector flow paths, the pressure atomizer atomizing the fuel as it flows from the one or more piston flow paths to the one or more fuel injector flow paths.

[0170] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more fuel injector flow paths are convergent-divergent flow paths.

[0171] According to any of the preceding clauses, the fuel injector manifold, wherein the flow paths of the one or more fuel injectors converge and diverge from the radially outer end to the radially inner end of the plurality of fuel injectors.

[0172] According to any of the preceding clauses, the fuel injector manifold, wherein the pressure atomizer includes a plurality of atomizer flow paths in fluid communication with the one or more piston flow paths and the one or more fuel injector flow paths, the plurality of atomizer flow paths guiding the fuel from the one or more piston flow paths to the one or more fuel injector flow paths to atomize the fuel.

[0173] According to any of the preceding clauses, the fuel injector manifold, wherein the plurality of atomizer flow paths includes a first atomizer flow path and a second atomizer flow path.

[0174] According to the fuel injector manifold described in the foregoing clause, the first atomizer flow path is circumferentially spaced from the second atomizer flow path.

[0175] According to any of the preceding clauses, the first atomizer flow path is axially aligned with the second atomizer flow path at the radially outer end of the pressure atomizer.

[0176] According to any of the preceding clauses, the first atomizer flow path and the second atomizer flow path are angled away from each other in the axial direction.

[0177] According to any of the preceding clauses, the fuel injector manifold wherein the first atomizer flow path is angled axially backward as it extends from the radially outer end to the radially inner end of the pressure atomizer.

[0178] According to any of the preceding clauses, the fuel injector manifold wherein the second atomizer flow path is angled forward axially as it extends from the radially outer end to the radially inner end of the pressure atomizer.

[0179] The fuel injector manifold according to any of the foregoing clauses further includes an atomizer plug disposed within the atomizer chamber and in contact with the pressure atomizer to prevent the pressure atomizer from rotating.

[0180] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more pistons comprise a plurality of pistons circumferentially spaced around the fuel manifold.

[0181] According to any of the preceding clauses, a respective one of the plurality of pistons is located within the fuel manifold ring at a respective one of the plurality of fuel injectors.

[0182] According to any of the preceding clauses, the fuel injector manifold, wherein the plurality of pistons are disposed within a plurality of piston chambers defined by the fuel manifold ring.

[0183] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms comprise a single actuation mechanism that is annular about the fuel manifold ring and coupled to each of the plurality of pistons.

[0184] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms comprise a plurality of actuation mechanisms, and a respective one of the plurality of actuation mechanisms is coupled to a respective one of the plurality of pistons.

[0185] According to any of the preceding clauses, in a fuel injector manifold, each of the plurality of actuation mechanisms moves the plurality of pistons at different rates to alter the circumferential delivery of fuel around the fuel manifold rings.

[0186] According to any of the preceding clauses, the fuel injector manifold wherein the flow path of the one or more pistons is annular around the one or more pistons.

[0187] The fuel injector manifold according to any of the foregoing clauses further includes one or more seals that seal the plurality of piston chambers to prevent fuel from flowing into the piston chambers.

[0188] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms are wave springs.

[0189] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms are compression springs or tension springs.

[0190] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuating mechanisms are leaf springs.

[0191] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms include a memory material that expands and contracts by thermal energy.

[0192] According to any of the preceding clauses, the fuel injector manifold wherein the one or more actuating mechanisms are fluid actuating mechanisms that supply a flow of pressurized fluid to move the one or more pistons.

[0193] According to any of the preceding clauses, the fuel injector manifold, wherein the fluid actuation mechanism includes hydraulic actuation, and the pressurized fluid is a hydraulic fluid.

[0194] According to any of the preceding clauses, the fuel injector manifold, wherein the fluid actuation mechanism includes pneumatic actuation, and the pressurized fluid is air or gas.

[0195] According to any of the preceding clauses, the fuel injector manifold, wherein the fluid actuation mechanism includes a pressurized fluid tank in which the pressurized fluid is stored, one or more fuel manifold actuation mechanism flow paths, and one or more piston actuation mechanism flow paths.

[0196] According to any of the preceding clauses, the fuel injector manifold, wherein the fluid actuation mechanism supplies pressurized fluid from the pressurization tank to the one or more piston actuation mechanism flow paths via the one or more fuel manifold actuation mechanism flow paths to push the one or more pistons to the closed state.

[0197] According to any of the preceding clauses, the fuel injector manifold wherein the fluid actuation mechanism retracts the pressurized fluid from the flow path of one or more piston actuation mechanisms back to the pressurization chamber to pull the one or more pistons to the fully open state.

[0198] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuating mechanisms are mechanical actuating mechanisms.

[0199] According to any of the preceding clauses, the fuel injector manifold, wherein the one or more actuation mechanisms include an actuator having an actuator shaft coupled to the one or more pistons, and the actuator pushes and pulls the actuator shaft to move the one or more pistons between the closed state, the partially open state, and the fully open state.

[0200] A turbine engine includes: a combustor and a fuel injector manifold. The fuel injector manifold includes: a fuel manifold ring surrounding the combustor, the fuel manifold ring defining a fuel manifold flow path within the fuel manifold ring, and the fuel manifold flow path receiving fuel therein; a plurality of fuel injectors in fluid communication with the fuel manifold flow path and the combustor, each of the plurality of fuel injectors having one or more fuel injector flow paths; and a variable fuel flow system disposed within the fuel manifold flow path, the variable fuel flow system including the closed state, the partially open state, and the fully open state to change the flow rate of fuel from the fuel manifold flow path to each of the one or more fuel injector flow paths for injecting the fuel into the combustor.

[0201] According to the turbine engine described in the foregoing clause, the one or more fuel injector flow paths are configured with a circumferential fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the circumferential fuel injector flow path angle is non-zero.

[0202] According to any of the preceding clauses, the turbine engine wherein the flow paths of one or more fuel injectors are configured with an axial fuel injector flow path angle relative to the transverse centerline axis, the axial fuel injector flow path angle being non-zero.

[0203] According to any of the preceding clauses, the turbine engine wherein the plurality of fuel injectors are oriented to inject fuel substantially radially from the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0204] According to any of the preceding clauses, the turbine engine, wherein the variable fuel flow system includes one or more pistons disposed within the fuel manifold flow path, the one or more pistons moving between the closed state, the partially open state, and the fully open state to change the flow rate of the fuel to each of the plurality of fuel injectors in the flow path of the one or more fuel injectors.

[0205] According to any of the preceding clauses, in a turbine engine, each of the one or more pistons includes one or more piston flow paths in fluid communication with the fuel manifold flow path and the one or more fuel injector flow paths of each of the plurality of fuel injectors, the one or more piston flow paths guiding the fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0206] According to any of the preceding clauses, in a turbine engine, wherein the one or more pistons divide the fuel manifold flow path into an upstream fuel manifold flow path and a downstream fuel manifold flow path, and the fuel flows from the upstream fuel manifold flow path into the downstream fuel manifold flow path, and through the one or more piston flow paths into the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0207] According to any of the foregoing clauses, the turbine engine, wherein the variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.

[0208] In any of the preceding clauses, the turbine engine wherein the one or more actuating mechanisms are passive actuating mechanisms.

[0209] In any of the preceding clauses, the turbine engine wherein the one or more actuating mechanisms are active actuating mechanisms.

[0210] The turbine engine according to any of the foregoing clauses further includes a fuel system in fluid communication with the fuel manifold inlet flow path, and the fuel system supplies fuel from the fuel system to the fuel manifold flow path through the fuel manifold inlet flow path.

[0211] The turbine engine according to any of the foregoing clauses, wherein the fuel injector manifold is a fuel injector manifold according to any of the foregoing clauses.

[0212] A method of operating a fuel injector manifold according to any of the preceding clauses, the method comprising supplying fuel through the fuel manifold flow path; moving the variable fuel flow system between a closed state, a partially open state, and a fully open state to change the flow rate of the fuel from the fuel manifold flow path to each of the plurality of fuel injectors via the one or more fuel injector flow paths.

[0213] The method according to the foregoing clause further includes guiding the fuel through the one or more fuel injector flow paths with a circumferential fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, wherein the circumferential fuel injector flow path angle is non-zero.

[0214] The method according to any of the foregoing clauses further includes guiding the fuel through the one or more fuel injector flow paths with an axial fuel injector flow path angle relative to the lateral centerline axis, the axial fuel injector flow path angle being non-zero.

[0215] The method according to any of the foregoing clauses further includes injecting the fuel substantially radially from the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0216] According to any of the foregoing clauses, the variable fuel flow system includes one or more pistons disposed within the fuel manifold flow path, and the method further includes moving the one or more pistons in the closed state, the partially open state, and the fully open state to change the flow rate of the fuel in the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0217] According to any of the foregoing clauses of the method, each of the one or more pistons includes one or more piston flow paths in fluid communication with the fuel manifold flow path and the one or more fuel injector flow paths of each of the plurality of fuel injectors, and the method further includes guiding the fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors through the one or more piston flow paths.

[0218] According to any of the foregoing clauses of the method, wherein the one or more pistons divide the fuel manifold flow path into an upstream fuel manifold flow path and a downstream fuel manifold flow path, and the method further includes guiding the fuel from the upstream fuel manifold flow path into the downstream fuel manifold flow path, and flowing through the one or more piston flow paths into the one or more fuel injector flow paths of each of the plurality of fuel injectors.

[0219] According to any of the foregoing clauses, the variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, and the method further includes moving the one or more pistons using the one or more actuation mechanisms.

[0220] According to any of the preceding clauses of the method, the one or more actuating mechanisms are passive actuating mechanisms.

[0221] According to any of the preceding clauses of the method, the one or more actuating mechanisms are active actuating mechanisms.

[0222] According to any of the preceding clauses, the turbine engine defines an axial direction, a radial direction, and a circumferential direction.

[0223] The method according to any of the foregoing clauses further includes a fuel manifold inlet having a fuel manifold inlet flow path in fluid communication with the fuel manifold flow path, and the method further includes supplying fuel from the fuel manifold inlet flow path to the fuel manifold flow path.

[0224] According to any of the foregoing clauses, the turbine engine includes a fuel system in fluid communication with the fuel manifold inlet flow path, and the method further includes supplying fuel from the fuel system to the fuel manifold flow path via the fuel manifold inlet flow path.

[0225] According to any of the preceding descriptions of the method, the plurality of fuel injectors are circumferentially spaced around the fuel manifold.

[0226] The method according to any of the foregoing clauses further includes a fuel manifold heat shield covering at least a portion of the fuel manifold ring.

[0227] According to any of the preceding clauses of the method, the one or more piston flow paths include one or more first piston flow paths, one or more second piston flow paths, and one or more third piston flow paths.

[0228] According to any of the foregoing clauses of the method, wherein the one or more first piston flow paths are in fluid communication with the upstream fuel manifold flow path and the downstream fuel manifold flow path, and the method further includes guiding the fuel from the upstream fuel manifold flow path to the downstream fuel manifold flow path through the one or more first piston flow paths.

[0229] According to any of the foregoing clauses of the method, wherein the one or more second piston flow paths are in fluid communication with the downstream fuel manifold flow path and the one or more third piston flow paths, and the method further includes guiding the fuel from the downstream fuel manifold flow path to the one or more third piston flow paths through the one or more second piston flow paths.

[0230] According to any of the foregoing clauses of the method, wherein the one or more third piston flow paths are in fluid communication with the one or more second piston flow paths and the one or more fuel injector flow paths, and the method further includes guiding the fuel from the one or more second piston flow paths to the one or more fuel injector flow paths through the one or more third piston flow paths.

[0231] According to any of the foregoing clauses of the method, wherein when the variable fuel flow system is in the off state, the flow paths of the one or more third pistons are not aligned with the flow paths of the one or more fuel injectors.

[0232] According to any of the foregoing provisions of the method, wherein when the variable fuel flow system is in the partially open state, the flow path of the one or more third pistons is partially aligned with the flow path of the one or more fuel injectors.

[0233] According to any of the foregoing provisions of the method, wherein when the variable fuel flow system is in the fully open state, the flow paths of the one or more third pistons are fully aligned with the flow paths of the one or more fuel injectors.

[0234] According to any of the preceding clauses of the method, the one or more pistons include a piston that is annular around the fuel manifold ring within the fuel manifold flow path.

[0235] According to any of the preceding clauses of the method, the upstream fuel manifold flow path is located upstream of the one or more pistons.

[0236] According to any of the foregoing descriptions of the method, the downstream fuel manifold flow path is located downstream of the one or more pistons.

[0237] According to any of the foregoing provisions of the method, the one or more fuel injector flow paths of each of the plurality of fuel injectors comprise a single fuel injector flow path.

[0238] According to any of the preceding clauses of the method, the flow path of the one or more fuel injectors is circular.

[0239] According to any of the foregoing descriptions of the method, the one or more pistons move axially forward and axially backward within the fuel manifold flow path.

[0240] According to any of the preceding clauses of the method, the circumferential fuel injector flow path angle is in the range of -60 degrees to 60 degrees.

[0241] According to any of the preceding clauses, the axial fuel injector flow path angle is in the range of -60 degrees to 60 degrees.

[0242] According to the method described in any of the foregoing clauses, the one or more fuel injector flow paths of each of the plurality of fuel injectors include a first fuel injector flow path and a second fuel injector flow path.

[0243] According to any of the foregoing provisions of the method, the first fuel injector flow path includes a first fuel injector flow path diameter, and the second fuel injector flow path includes a second fuel injector flow path diameter.

[0244] According to any of the preceding clauses of the method, the diameter of the first fuel injector flow path is equal to the diameter of the second fuel injector flow path.

[0245] According to any of the preceding clauses of the method, the diameter of the first fuel injector flow path is greater than or less than the diameter of the second fuel injector flow path.

[0246] The method according to any of the foregoing clauses further includes guiding the fuel through the first fuel injector flow path and the second fuel injector flow path at an angle toward each other in the circumferential direction, such that the fuel passing through the first fuel injector flow path impinges on the fuel from the second fuel injector flow path to atomize the fuel.

[0247] The method according to any of the foregoing clauses further includes guiding the fuel through the first fuel injector flow path at a first circumferential fuel injector angle relative to the transverse centerline axis in the circumferential direction.

[0248] The method according to any of the foregoing clauses further includes guiding the fuel through the second fuel injector flow path at a second circumferential fuel injector angle relative to the transverse centerline axis in the circumferential direction.

[0249] According to any of the preceding clauses, the fuel injector manifold, wherein the first circumferential fuel injector flow path angle and the second circumferential fuel injector flow path angle are non-zero.

[0250] According to any of the preceding clauses of the method, each of the first circumferential fuel injector flow path angle and the second circumferential fuel injector flow path angle is in the range of ten to sixty degrees.

[0251] According to any of the foregoing provisions of the method, wherein the second circumferential fuel injector flow path angle is opposite to the first circumferential fuel injector flow path angle, such that the first circumferential fuel injector flow path and the second circumferential fuel injector flow path are angled toward each other in the circumferential direction.

[0252] According to any of the foregoing provisions of the method, wherein the first fuel injector flow path is spaced apart from the second fuel injector flow path in the circumferential direction, such that the first transverse centerline axis of the first fuel injector flow path is offset from the second transverse centerline axis of the second fuel injector flow path by a circumferential distance of the fuel injector flow path.

[0253] The method according to any of the foregoing clauses further includes guiding the fuel through the first fuel injector flow path and the second fuel injector flow path with an axial fuel injector flow path angle relative to the axial direction, wherein the axial fuel injector flow path angle is non-zero.

[0254] According to any of the preceding clauses of the method, the flow path of the one or more fuel injectors is elliptical.

[0255] According to any of the preceding clauses of the method, the flow path of the one or more fuel injectors is a slit.

[0256] The method according to any of the foregoing clauses further includes a pressure atomizer disposed within an atomizer chamber radially located between the one or more pistons and the one or more fuel injector flow paths, and the method further includes using the pressure atomizer to atomize the fuel as the fuel flows from the one or more piston flow paths to the one or more fuel injector flow paths.

[0257] According to any of the foregoing descriptions, the one or more fuel injector flow paths are convergent-divergent flow paths.

[0258] According to any of the preceding clauses of the method, the flow paths of the one or more fuel injectors converge and diverge from the radially outer end to the radially inner end of the plurality of fuel injectors.

[0259] According to any of the foregoing clauses of the method, wherein the pressure atomizer includes a plurality of atomizer flow paths in fluid communication with the one or more piston flow paths and the one or more fuel injector flow paths, and the method further includes guiding the fuel from the one or more piston flow paths to the one or more fuel injector flow paths through the plurality of atomizer flow paths to atomize the fuel.

[0260] According to any of the foregoing descriptions of the method, the plurality of atomizer flow paths include a first atomizer flow path and a second atomizer flow path.

[0261] According to any of the preceding descriptions of the method, the first atomizer flow path is circumferentially spaced from the second atomizer flow path.

[0262] According to any of the foregoing descriptions of the method, wherein the first atomizer flow path is axially aligned with the second atomizer flow path at the radially outer end of the pressure atomizer.

[0263] According to any of the foregoing provisions of the method, the first atomizer flow path and the second atomizer flow path are angled away from each other in the axial direction.

[0264] The method according to any of the foregoing clauses further includes guiding the fuel through the first atomizer flow path at an axially rearward angle as the first atomizer flow path extends from the radially outer end to the radially inner end of the pressure atomizer.

[0265] The method according to any of the foregoing clauses further includes guiding the fuel through the second atomizer flow path at an axially forward angle as the second atomizer flow path extends from the radially outer end to the radially inner end of the pressure atomizer.

[0266] The method according to any of the foregoing clauses further includes using an atomizer plug disposed within the atomizer cavity and in contact with the pressure atomizer to prevent the pressure atomizer from rotating.

[0267] According to any of the preceding clauses of the method, the one or more pistons comprise a plurality of pistons circumferentially spaced around the fuel manifold ring.

[0268] According to any of the foregoing clauses of the method, a respective one of the plurality of pistons is positioned within the fuel manifold ring at a respective one of the plurality of fuel injectors.

[0269] According to any of the foregoing clauses of the method, the plurality of pistons are disposed within a plurality of piston chambers defined by the fuel manifold ring.

[0270] According to any of the preceding clauses of the method, wherein the one or more actuation mechanisms comprise a single actuation mechanism that is annular around the fuel manifold ring and coupled to each of the plurality of pistons.

[0271] According to any of the preceding clauses of the method, wherein the one or more actuating mechanisms comprise a plurality of actuating mechanisms, and a respective one of the plurality of actuating mechanisms is coupled to a respective one of the plurality of pistons.

[0272] The method according to any of the foregoing clauses further includes using each of the plurality of actuating mechanisms to move the plurality of pistons at different rates to alter the circumferential delivery of the fuel around the fuel manifold ring.

[0273] According to any of the preceding clauses of the method, the one or more piston flow paths are annular around the one or more pistons.

[0274] The method according to any of the foregoing clauses further includes using one or more seals that seal the plurality of piston chambers to prevent the fuel from flowing into the plurality of piston chambers.

[0275] According to any of the preceding clauses, the one or more actuating mechanisms are wave springs.

[0276] According to any of the preceding clauses, the one or more actuating mechanisms are compression springs or tension springs.

[0277] According to any of the preceding clauses, the one or more actuating mechanisms are leaf springs.

[0278] According to any of the foregoing descriptions, the one or more actuating mechanisms include a memory material that expands and contracts by thermal energy.

[0279] According to any of the foregoing clauses of the method, wherein the one or more actuating mechanisms are fluid actuating mechanisms, and the method further includes supplying a flow of pressurized fluid to move the one or more pistons.

[0280] According to any of the preceding clauses of the method, the fluid actuation mechanism includes hydraulic actuation, and the pressurized fluid is a hydraulic fluid.

[0281] According to any of the preceding clauses, the fluid actuation mechanism includes pneumatic actuation, and the pressurized fluid is air or gas.

[0282] According to any of the preceding clauses, the fluid actuation mechanism includes a pressurized fluid tank in which the pressurized fluid is stored, one or more fuel manifold actuation mechanism flow paths, and one or more piston actuation mechanism flow paths.

[0283] The method according to any of the foregoing clauses further includes using the fluid actuation mechanism to supply pressurized fluid from the pressurization tank to the one or more piston actuation mechanism flow paths through the one or more fuel manifold actuation mechanism flow paths to push the one or more pistons to the closed state.

[0284] The method according to any of the foregoing clauses further includes using the fluid actuation mechanism to retract the pressurized fluid from the flow path of one or more piston actuation mechanisms back to the pressurization chamber to pull the one or more pistons toward the fully open state.

[0285] According to any of the preceding clauses of the method, the one or more actuating mechanisms are mechanical actuating mechanisms.

[0286] According to any of the foregoing clauses, the one or more actuating mechanisms include an actuator having an actuator shaft coupled to the one or more pistons, and the method further includes using the actuator to push and pull the actuator shaft to move the one or more pistons between the closed state, the partially open state, and the fully open state.

[0287] While the foregoing description is directed to preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the present disclosure. Furthermore, even if not explicitly stated above, features described in connection with one embodiment of the present disclosure can be used in conjunction with other embodiments.

Claims

1. A fuel injector manifold for a turbine engine, characterized in that, The fuel injector manifold includes: A fuel manifold ring, wherein the fuel manifold ring defines a fuel manifold flow path within the fuel manifold ring, the fuel manifold flow path being annular around the fuel manifold ring and receiving fuel therein; A plurality of fuel injectors, wherein the plurality of fuel injectors are in fluid communication with the fuel manifold flow path, each of the plurality of fuel injectors having one or more fuel injector flow paths; and A variable fuel flow system, wherein the variable fuel flow system is disposed within the fuel manifold flow path, the variable fuel flow system comprising one or more pistons disposed within the fuel manifold flow path and moving substantially perpendicular to the fuel manifold flow path between a closed state, a partially open state, and a fully open state, to change the flow rate of fuel from the fuel manifold flow path to each of the plurality of fuel injectors in the one or more fuel injector flow paths.

2. The fuel injector manifold according to claim 1, characterized in that, The one or more fuel injector flow paths are set with a circumferential fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the circumferential fuel injector flow path angle is non-zero.

3. The fuel injector manifold according to claim 1, characterized in that, The one or more fuel injector flow paths are set with an axial fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the axial fuel injector flow path angle is non-zero.

4. The fuel injector manifold according to claim 1, characterized in that, The plurality of fuel injectors are oriented to inject fuel substantially radially from the one or more fuel injector flow paths of each of the plurality of fuel injectors.

5. The fuel injector manifold according to claim 1, characterized in that, Each of the one or more pistons includes one or more piston flow paths that are in fluid communication with the fuel manifold flow path and the one or more fuel injector flow paths of each of the plurality of fuel injectors, the one or more piston flow paths guiding the fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors.

6. The fuel injector manifold according to claim 5, characterized in that, The one or more pistons divide the fuel manifold flow path into an upstream fuel manifold flow path and a downstream fuel manifold flow path, and the fuel flows from the upstream fuel manifold flow path into the downstream fuel manifold flow path, and through the one or more piston flow paths into the one or more fuel injector flow paths of each of the plurality of fuel injectors.

7. The fuel injector manifold according to claim 1, characterized in that, The variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.

8. The fuel injector manifold according to claim 7, characterized in that, The one or more actuating mechanisms mentioned above are passive actuating mechanisms.

9. The fuel injector manifold according to claim 7, characterized in that, The one or more actuating mechanisms mentioned therein are active actuating mechanisms.

10. The fuel injector manifold according to claim 1, characterized in that, The fuel manifold flow path extends circumferentially around the fuel manifold, and the one or more pistons move generally axially within the fuel manifold flow path.

11. A turbine engine, characterized in that, include: Burner; and A fuel injector manifold, the fuel injector manifold comprising: A fuel manifold ring, wherein the fuel manifold is disposed around the burner, the fuel manifold ring defines a fuel manifold flow path within the fuel manifold ring, and the fuel manifold flow path is annular around the fuel manifold ring and receives fuel therein; A plurality of fuel injectors, wherein the plurality of fuel injectors are in fluid communication with the fuel manifold flow path and the burner, each of the plurality of fuel injectors having one or more fuel injector flow paths; and A variable fuel flow system, disposed within the fuel manifold flow path, comprising one or more pistons disposed within the fuel manifold flow path and moving substantially perpendicular to the fuel manifold flow path between a closed state, a partially open state, and a fully open state, to change the flow rate of fuel from the fuel manifold flow path to each of the plurality of fuel injectors in the flow path of the one or more fuel injectors, for injecting the fuel into the burner.

12. The turbine engine according to claim 11, characterized in that, The one or more fuel injector flow paths are set with a circumferential fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the circumferential fuel injector flow path angle is non-zero.

13. The turbine engine according to claim 11, characterized in that, The one or more fuel injector flow paths are set with an axial fuel injector flow path angle relative to the lateral centerline axis of the fuel injector manifold, and the axial fuel injector flow path angle is non-zero.

14. The turbine engine according to claim 11, characterized in that, The plurality of fuel injectors are oriented to inject fuel substantially radially from the one or more fuel injector flow paths of each of the plurality of fuel injectors.

15. The turbine engine according to claim 11, characterized in that, Each of the one or more pistons includes one or more piston flow paths that are in fluid communication with the fuel manifold flow path and the one or more fuel injector flow paths of each of the plurality of fuel injectors, the one or more piston flow paths guiding the fuel from the fuel manifold flow path to the one or more fuel injector flow paths of each of the plurality of fuel injectors.

16. The turbine engine according to claim 15, characterized in that, The one or more pistons divide the fuel manifold flow path into an upstream fuel manifold flow path and a downstream fuel manifold flow path, and the fuel flows from the upstream fuel manifold flow path into the downstream fuel manifold flow path, and through the one or more piston flow paths into the one or more fuel injector flow paths of each of the plurality of fuel injectors.

17. The turbine engine according to claim 11, characterized in that, The variable fuel flow system includes one or more actuation mechanisms coupled to the one or more pistons, the one or more actuation mechanisms moving the one or more pistons.

18. The turbine engine according to claim 17, characterized in that, The one or more actuating mechanisms mentioned above are passive actuating mechanisms.

19. The turbine engine according to claim 17, characterized in that, The one or more actuating mechanisms mentioned therein are active actuating mechanisms.

20. The turbine engine according to claim 11, characterized in that, The fuel manifold flow path extends circumferentially around the fuel manifold, and the one or more pistons move generally axially within the fuel manifold flow path.

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