Gas turbine engine and fuel injector assembly therefor

Abstract

A gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement wherein the combustion section includes: a combustor liner at least partially defining a combustion chamber; and a fuel injector assembly, the fuel injector assembly including a mixing tube having a mixing tube body defining a mixing channel. The mixing tube body may have a set of fuel passages terminating in fuel orifices fluidly coupled to the mixing channel. A set of air flow channels terminating at the air outlets may be fluidly coupled to the mixing channel. At least some of the air outlets surround corresponding fuel orifices.

Description

Technical Field

[0001] This topic generally relates to fuel injectors for supplying a mixture of fuel and air to a turbine engine, and more specifically, to fuel injectors for supplying the mixture of fuel and air to a combustor for combustion to drive a turbine engine. Background Technology

[0002] A turbine engine is driven by a flow of combustion gases through the engine to rotate multiple turbine blades, which in turn rotates a compressor, thus supplying compressed air to the combustor for combustion. The combustor can be located within the turbine engine and fluidly connected to the turbine through which the combustion gases flow.

[0003] Historically, hydrocarbon fuels have been used in the combustors of turbine engines. Typically, air and fuel are fed into the combustion chamber, mixed, and then the fuel is burned in the presence of air to produce hot gases. These hot gases are then fed into the turbine, where they are cooled and expanded to generate power. Byproducts of fuel combustion often include environmentally undesirable byproducts such as nitrogen oxides and nitrogen dioxide (collectively known as NO). x Carbon monoxide (CO), unburned hydrocarbons (UHC) (e.g., methane and volatile organic compounds that contribute to the formation of atmospheric ozone), and other oxides including sulfur oxides (e.g., SO2 and SO3).

[0004] To reduce unwanted environmental byproducts, other fuels, such as hydrogen, are being explored. Hydrogen, or hydrogen mixed with another element, has a higher flame temperature than conventional hydrocarbon fuels. In other words, hydrogen or hydrogen-blended fuels typically have a wider combustible range and a faster combustion rate than conventional hydrocarbon-based fuels. Attached Figure Description

[0005] In the attached diagram:

[0006] Figure 1 This is a schematic diagram of a turbine engine according to an aspect of the present disclosure, the turbine engine including a compression section, a combustion section and a turbine section.

[0007] Figure 2 Depicting aspects according to this disclosure along Figure 1 A cross-sectional view of the combustion zone taken by line II-II further shows the fuel injector assembly connected to the combustion chamber.

[0008] Figure 3 Is it suitable for Figure 2 A cross-sectional view of a fuel injector assembly used within a set of fuel injector assemblies.

[0009] Figure 4AThis is a schematic diagram showing the fuel passage and air passage of the fuel injector assembly according to various aspects described herein.

[0010] Figure 4B This is a schematic diagram showing the fuel passage and air passage of the fuel injector assembly according to various aspects described herein.

[0011] Figure 4C This is a schematic diagram showing the fuel passage and air passage of the fuel injector assembly according to various aspects described herein.

[0012] Figure 4D This is a schematic diagram showing the fuel passage and air passage of the fuel injector assembly according to various aspects described herein.

[0013] Figure 4E This is a schematic diagram showing the fuel passage and air passage of the fuel injector assembly according to various aspects described herein.

[0014] Figure 5 Is it suitable for Figure 2 A cross-sectional view of an exemplary fuel injector assembly used within this group of fuel injector assemblies.

[0015] Figure 6A This is a schematic diagram showing the fuel orifice, first air outlet, and second air outlet of a fuel injector assembly according to various aspects described herein.

[0016] Figure 6B This is a schematic diagram showing the fuel orifice, first air outlet, and second air outlet of the fuel injector assembly according to various aspects described herein. Detailed Implementation

[0017] The disclosed aspects herein relate to burners and fuel injector assemblies for burners. In some aspects, the disclosed burners and fuel injector assemblies can be used with fuels that may include one or more of liquid or gaseous hydrogen, natural gas, diesel, and Jet-A, and may be combined with one or both of water and steam. For turbine engines, fuel may be stored, used, or both at a lower temperature than the air moving within the turbine engine, creating thermal gradients that can lead to high stress concentrations and thermal variations in portions of the fuel injector assembly. The presence of fuel and air at such different temperatures in the fuel injector assembly (e.g., in the mixing tube body) creates thermal gradients between portions of the fuel injector assembly that are in thermal contact with relatively hot air and relatively cold fuel. These thermal gradients cause portions of the fuel injector assembly (e.g., the inner surface of the mixing tube body) to experience increased thermal stresses, which accelerate wear and degradation of the fuel injector assembly (including tube surfaces), cause flow variations between tubes, reduce overall mixing capacity, and shorten the life of one or both the injector and the mixer.

[0018] With the fuel injector assembly disclosed herein, fuel from a fuel orifice can be introduced together with air supplied from an air outlet surrounding the fuel orifice, thereby providing thermal breakage between the fuel and other surfaces of the fuel injector assembly. Furthermore, a fuel passage for supplying fuel through the body of the fuel injector assembly (e.g., a mixing tube body) can be used to surround a corresponding airflow passage for supplying air to the air outlet. An airflow passage surrounding a portion of the fuel passage (e.g., a portion of the fuel passage that passes through the body of the fuel injector assembly) can also provide thermal breakage between the fuel and other surfaces of the fuel injector assembly beyond the air outlet.

[0019] These thermal fractures can reduce the thermal gradient and decrease thermal stress concentration, thereby improving overall mixing capacity and the lifespan of the fuel injector assembly.

[0020] For illustrative purposes, this disclosure will be described in relation to turbine engines (e.g., gas turbine engines). However, it will be understood that the aspects of the disclosure described herein are not limited thereto. The combustors described herein can be implemented in a variety of engines (including, but not limited to, turbojet engines, turboprop engines, turboshaft engines, and turbofan engines). The aspects of the disclosure discussed herein are generally applicable to non-aircraft engines with combustors, such as in other mobile applications and non-mobile industrial, commercial, and residential applications.

[0021] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior to or advantageous to other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0022] As used herein, the terms “first” and “second” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0023] 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, for a turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine exhaust outlet.

[0024] As used herein, the term "upstream" refers to the direction opposite to the direction of fluid flow, while the term "downstream" refers to the direction in the same direction as the fluid flow. The terms "forward" or "front" indicate what is in front of something, and "backward" or "rear" indicate what is behind something. For example, when used in relation to fluid flow, forward or front can indicate upstream, and backward or rear can indicate downstream.

[0025] The term "fluid" can refer to a gas, a liquid, or a combination thereof. The term "fluid connection" means that fluids can establish a connection between specified areas.

[0026] Furthermore, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the engine's central longitudinal axis and the engine's outer perimeter.

[0027] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, back, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to aid the reader in understanding this disclosure and do not impose limitations, particularly regarding the location, orientation, or use of the aspects of the disclosure described herein. Connective references (e.g., attachment, coupling, connection, and joining) are to be interpreted broadly and may include intermediate structural elements between sets of elements and relative movement between elements, unless otherwise indicated. Therefore, a connective reference does not necessarily mean that two elements are directly connected and fixed relative to each other. Exemplary figures are for illustrative purposes only, and the dimensions, positions, order, and relative sizes reflected in the accompanying figures may vary.

[0028] The singular forms “a,” “an,” and “the” include plural references unless the context clearly indicates otherwise. Furthermore, as used herein, the term “group” or “set” of elements can be any number of elements, including only one.

[0029] The use of “and” and “or” will be interpreted broadly. For example, but not limited to, the use of “and” does not necessarily require all the elements or features listed, and the use of “or” is inclusive unless the structure is illogical.

[0030] As used herein and throughout the specification and claims, approximate language is applied to modify any quantitative representation that may allow variation without altering its associated essential function. Therefore, values ​​modified by one or more terms such as “approximately,” “substantially,” and “basically” are not limited to the specified precise 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. For example, approximate language may refer to a margin of 1%, 2%, 4%, 5%, 10%, 15%, or 20% of the endpoints of a single value, a range of values, or a range of defined values. Scope limitations are combined and interchanged herein and throughout the specification and claims; such scope is identified and includes all subscopes contained herein, unless otherwise indicated by context or language. For example, all scopes disclosed herein include endpoints, and endpoints can be combined independently of each other.

[0031] Additionally, as used herein, "controller" can include components configured or adapted to provide instructions, control, operation, or any form of communication to an operable component to achieve its operation. A controller can include any known processor, microcontroller, or logic device, including but not limited to: field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), full-authority digital engine control (FADECs), proportional controllers (P), proportional-integral controllers (PI), proportional-derivative controllers (PD), proportional-integral-derivative controllers (PID controllers), proportional-resonant controllers (PR), hardware-accelerated logic controllers (e.g., for encoding, decoding, transcoding, etc.), and combinations thereof. Non-limiting examples of controllers can be configured or adapted to run, operate, or otherwise execute program code to affect operational or functional outcomes, including performing various methods, functions, processing tasks, calculations, comparisons, sensing, or measurement values, etc., to enable or implement the technical operations or actions described herein. Operational or functional outcomes can be based on one or more inputs, stored data values, sensed or measured values, true or false indications, etc. While “program code” is described, non-limiting examples of operable or executable instruction sets may include routines, programs, objects, components, data structures, algorithms, etc., that have the technical effect of performing a specific task or implementing a specific abstract data type. In another non-limiting example, the controller may also include data storage components accessible by the processor, including memory, whether transient, volatile, or non-transient or non-volatile.

[0032] Additional non-limiting examples of memory may include random access memory (RAM), read-only memory (ROM), flash memory, or one or more different types of portable electronic memory, such as discs, DVDs, CD-ROMs, flash drives, universal serial bus (USB) drives, etc., or any suitable combination of these types of memory. In one example, program code may be stored in memory in a machine-readable format accessible to a processor. Furthermore, memory may store various types of data, sensed or measured data values, input, generated or processed data, etc., accessible to a processor when providing instructions, control, or operations to achieve a function or operable result, as described herein. In another non-limiting example, a controller may be configured to compare a first value with a second value and operate and control the operation of additional components based on the satisfaction of that comparison. For example, when a sensed, measured, or provided value is compared with another value (including a stored or predetermined value), the satisfaction of that comparison may result in an action, function, or operation that can be controlled by the controller.

[0033] Figure 1This is a schematic diagram of a turbine engine 10 (e.g., a gas turbine engine). As a non-limiting example, the turbine engine 10 can be used within an aircraft. The turbine engine 10 may include at least a compressor section 12, a combustion section 14, and a turbine section 16. A drive shaft 18 rotatably connects the compressor section 12 and the turbine section 16 such that rotation of one affects rotation of the other, and defines the axis of rotation 20 of the turbine engine 10.

[0034] Compressor section 12 may include a low-pressure (LP) compressor 22 and a high-pressure (HP) compressor 24 that are fluidly connected in series with each other. Turbine section 16 may include an HP turbine 26 and an LP turbine 28 that are fluidly connected in series with each other. Drive shaft 18 may operatively connect the LP compressor 22, HP compressor 24, HP turbine 26, and LP turbine 28 together. Alternatively, drive shaft 18 may include an LP drive shaft (not shown) and an HP drive shaft (not shown). The LP drive shaft may connect the LP compressor 22 to the LP turbine 28, and the HP drive shaft may connect the HP compressor 24 to the HP turbine 26. The LP spool may be defined as a combination of the LP compressor 22, LP turbine 28, and LP drive shaft, such that rotation of the LP turbine 28 may apply a driving force to the LP drive shaft, which in turn may rotate the LP compressor 22. The HP spool may be defined as a combination of the HP compressor 24, HP turbine 26, and HP drive shaft, such that rotation of the HP turbine 26 may apply a driving force to the HP drive shaft, which in turn may rotate the HP compressor 24.

[0035] Compressor section 12 may include multiple axially spaced stages. Each stage includes a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Compressor blades for a stage of compressor section 12 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. Blades of compressor section 12 may be mounted to a housing that may extend circumferentially around one or more sections of turbine engine 10 and shield one or more sections of turbine engine 10. It should be understood that the representation of compressor section 12 is merely illustrative and any number of blades, blades, and stages may be present. Furthermore, it is conceivable that any number of other components may be present within compressor section 12.

[0036] Similar to compressor section 12, turbine section 16 may include multiple axially spaced stages, each stage having a set of circumferentially spaced rotating blades and a set of circumferentially spaced stationary blades. Turbine blades for one stage of turbine section 16 may be mounted to a disc, which is mounted to drive shaft 18. Each set of blades for a given stage may have its own disc. The blades of turbine section 16 may be circumferentially mounted to the housing. It should be noted that any number of blades, blades, and turbine stages are possible, as the illustrated turbine section 16 is merely schematic. Furthermore, it is conceivable that any number of other components may be present within turbine section 16.

[0037] Combustion section 14 may be arranged in series between compressor section 12 and turbine section 16. Combustion section 14 may be fluidly coupled to at least a portion of compressor section 12 and turbine section 16, such that combustion section 14 at least partially fluidly couples compressor section 12 to turbine section 16. As a non-limiting example, combustion section 14 may be fluidly coupled to HP compressor 24 at its upstream end and to HP turbine 26 at its downstream end.

[0038] During operation of the turbine engine 10, ambient air or atmospheric air is drawn into the compressor section 12 via a fan (not shown) upstream of the compressor section 12, where it is compressed to define pressurized air. This pressurized air can then flow into the combustion section 14, where it mixes with fuel and is ignited to generate combustion gases. The HP turbine 26 extracts some work from these combustion gases, driving the HP compressor 24. The combustion gases are discharged into the LP turbine 28, which extracts additional work to drive the LP compressor 22, and the exhaust gas is ultimately discharged from the turbine engine 10 via an exhaust section (not shown) downstream of the turbine section 16. The drive of the LP turbine 28 drives the LP spool, causing the fan and LP compressor 22 to rotate. The pressurized airflow and combustion gases together define the working airflow flowing through the fan, compressor section 12, combustion section 14, and turbine section 16 of the turbine engine 10.

[0039] Figure 2 Depicting along Figure 1 A cross-sectional view of combustion section 14 along line II-II. The centerline 33 of combustion section 14 may be collinear with the axis of rotation 20. Combustion section 14 may include a combustor 30, which has a surrounding structure around the turbine engine 10. Figure 1The combustor portions 31 are arranged in an annular arrangement (e.g., circumferentially spaced apart from each other in an annular configuration) along the centerline 33 or axis of rotation 20 of the engine. In some configurations, the combustor portions 31 may include or be configured as a combustor cup, fuel cup, or injector cup. A fuel injector assembly 48 may be fluidly coupled to each combustor portion 31. Depending on the type of engine in which the combustor 30 is located, the combustor 30 may have a canister-shaped, canister-annular, or annular arrangement. In a non-limiting example, the combustor 30 may have an arrangement similar to that of the turbine engine 10. Figure 1 The protective cover or housing 29 is positioned together with the protective cover or housing 29. The protective cover or housing 29 can shield or cover at least a portion of the combustion section 14.

[0040] The burner 30 may be at least partially defined by a burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 and an inner bushing 42 arranged concentrically relative to each other and in a ring-like manner about a centerline 33 or an axis of rotation 20. In some examples, the burner bushing 40 may have a ring-like structure around the burner 30. In some examples, the burner bushing 40 may include multiple segments or portions that together form the burner bushing 40. In some examples, the burner bushing 40 may include an outer bushing 41 radially spaced from the inner bushing 42. In some examples, the burner bushing 40 may include a single bushing.

[0041] The burner bushing 40 may at least partially define a combustion chamber 50 arranged annularly about the axis of rotation 20. For example, the wall 46 may be substantially perpendicular to the axis of rotation 20 and may cooperate with the outer liner 41, the inner liner 42, or both to at least partially define the combustion chamber 50. The compressed air passage 32 may be at least partially defined by both the burner bushing 40 and the housing 29.

[0042] Combustor 30 may include or be fluidly coupled to fuel source 34 (e.g., fuel manifold or duct), air source 36 (e.g., air manifold or duct), or both. Fuel source 34 may supply fuel (F), which may include any suitable liquid or gaseous fuel (including one or more of hydrogen, natural gas, diesel, or Jet-A), and may combine one or both of water and steam. In a non-limiting example, hydrogen fuel may include 100% H2 (e.g., without diluent). For example, fuel injector assembly 48 may be a gaseous fuel injector assembly, such as a gaseous hydrogen fuel injector assembly, a liquid fuel injector assembly, or a fuel injector assembly configured to inject a combination of gas and liquid. Air source 36 may supply air (A), such as compressed air, to fuel injector assembly 48. For example, air source 36 may include or be fluidly coupled to compressor section 12 ( Figure 1 ).

[0043] Fuel injector assembly 48 may be coupled to wall 46. Fuel injector assembly 48 fluidly connects fuel source 34 and air source 36 to one of burner sections 31 and combustion chamber 50. Burner section 31 may be individually coupled to wall 46. For example, but not limited to, burner section 31 may be configured to be coupled to wall 46 at circumferential intervals. Burner section 31 may be configured to be radially distanced from centerline 33, which is greater than the radial distance of inner liner 42 and less than the radial distance of outer liner 41.

[0044] The fuel injector assembly 48 may include a mixing tube 38 (e.g., a mixing tube body). For example, the mixing tube 38 may be a gas mixing tube (such as a gaseous hydrogen mixing tube), a liquid fuel mixing tube, or a mixing tube configured to mix a combination of gaseous and liquid fuels with air (A). The air (A) supplied by the air source 36 may include flow from the compressor section 12 to the combustor 30 during operation. Figure 1 The pressurized air is mixed with the fuel (F) and air (A) in a fluid connection to the combustor 30, such that the fuel (F) and air (A) are mixed together at least to some extent before flowing out of the fuel injector assembly 48 and into the combustion chamber 50 to form a fuel-air mixture (FA).

[0045] The controller 60 may be connected to the fuel source 34, the air source 36, the fuel injector assembly 48, or a combination thereof, and at least partially control their operation. The controller 60 may include a processor 62 and a memory 64.

[0046] Figure 3 Depicting suitable for use as Figure 2 A cross-sectional view of the fuel injector assembly 100 and the fuel injector assembly 48. The fuel injector assembly 100 can be fluidly connected to a fuel source 34 and an air source 36. Figure 2 For example, the fuel injector assembly 100 may include a fuel supply section 102 fluidly connected to a fuel source 34, and may include an air supply section 104 fluidly connected to an air source 36. The fuel injector assembly 100 is coupled to a wall 46, a burner bushing 40, or a combination thereof, and is fluidly connected to a combustion chamber 50. The rear end of the fuel injector assembly 100 may be directly coupled to the burner bushing 40, or indirectly (e.g., via the wall 46) coupled to the burner bushing 40.

[0047] The fuel injector assembly 100 includes a mixing tube 110 having a mixing tube body 112 defining a mixing channel 114. The front end of the mixing tube body 112 defines an inlet 116 of the mixing channel 114. The inlet 116 may be part of an air supply section 104 and may be fluidly connected to an air source 36. Figure 2An air (A) is supplied to the mixing channel 114. The rear end of the mixing tube body 112 defines an outlet 118 of the mixing channel 114, which is fluidly coupled to the combustion chamber 50 to discharge fluids (such as a fuel-air mixture (FA)) from the fuel injector assembly 100 into the combustion chamber 50. The outlet 118 and inlet 116 are arranged in series along the mixing tube 110 such that at least some of the air (A) received in the inlet 116 can flow toward the outlet 118 through the mixing tube 110 (e.g., along centerline 35) and into the combustion chamber 50. One or more of the mixing tube body 112, inlet 116, or outlet 118 may have a circular cross-sectional shape. The inner surface 120 of the mixing tube body 112 extends from the inlet 116 to the outlet 118 and at least partially defines the mixing channel 114.

[0048] The mixing tube 110 may include a centerline 35, which is parallel to and radially offset from the centerline 33. The centerline 35 of the mixing tube 110 may define a radial direction (Rd), an axial direction (Ad), and a circumferential direction (Cd). The centerline 35 may be collinear with the centerline of the burner portion 31 to which the fuel injector assembly 100 is connected.

[0049] Fuel supply unit 102 may include fluid connection to fuel source 34 ( Figure 2 The fuel manifold 130 and a set of fuel passages 132 fluidly connecting the fuel manifold 130 to a mixing channel 114 to supply fuel (F) to the mixing channel 114. In some examples, the fuel manifold 130 may be at least partially defined in the mixing pipe body 112 and arranged concentrically around the mixing channel 114. For example, the fuel manifold 130 may have an annular configuration around the mixing channel 114.

[0050] The set of fuel passages 132 may be at least partially defined in the mixing tube body 112 and may extend from the fuel manifold 130 to the mixing channel 114 to discharge fuel (F) from the fuel manifold 130 into the mixing channel 114. For example, the set of fuel passages 132 may extend radially inward at least to some extent toward the centerline 35. In a non-limiting example, the set of fuel passages 132 includes a plurality of fuel passages 132 circumferentially spaced from each other in an annular configuration relative to the centerline 35. The set of fuel passages 132 may include a set of fuel tips 134 that fluidly connect the set of fuel passages 132 to the mixing channel 114. The set of fuel tips 134 may extend into a set of fuel orifices 136 defined in the inner surface 120 of the mixing tube body 112 to discharge fuel (F) into the mixing channel 114. The set of fuel orifices 136 may be arranged circumferentially along the inner surface 120 of the mixing tube body 112.

[0051] The set of fuel channels 132 may include a fuel channel inner dimension 146 (e.g., hydraulic diameter), and the set of fuel tips 134 may include a fuel tip inner dimension 148 (e.g., hydraulic diameter). A fuel channel centerline 149 may be defined in each channel of the set of fuel channels 132. In some examples, the fuel channel inner dimension 146 and the fuel tip inner dimension 148 may be measured perpendicular to the fuel channel centerline 149.

[0052] As shown in the figure, the fuel tips in the set of fuel tips 134 gradually taper from the corresponding fuel channels in the set of fuel channels 132, such that the inner dimension 148 of the fuel tip, or at least its minimum value, is smaller than the inner dimension 146 of the corresponding fuel channel. This configuration can simplify manufacturing by having tighter manufacturing tolerances on the set of fuel tips 134, allowing for relatively looser tolerances on the set of fuel channels 132. For example, the set of fuel tips 134 can more tightly control the flow of fuel (F) entering the mixing channel 114 from the corresponding set of fuel orifices 136 and reduce variations in the flow of fuel (F) entering the mixing channel 114 from the set of fuel orifices 136, which can improve the overall mixing capability of the fuel injector assembly 100.

[0053] Although the set of fuel passages 132 is shown as including the set of fuel tips 134, at least some of the fuel passages in the set of fuel passages 132 may extend directly into the corresponding fuel orifices in the set of fuel orifices 136. The set of fuel passages 132 may have an internal fuel passage dimension 146 that increases, decreases, or remains constant between the fuel manifold 130 and the set of fuel orifices 136.

[0054] Air source 36 ( Figure 2 The air supply section 104, fluidly connected to the fuel injector assembly 100, may include a set of airflow passages 142 at least partially defined in the mixing tube body 112. This set of airflow passages 142 may include a set of air outlets 144 defined along the inner surface 120 of the mixing tube body 112 to deliver air (A) from the air source 36 ( Figure 2Air is supplied to the mixing channel 114. This set of airflow channels 142 may extend at least partially through the mixing tube body 112. Air outlets 144 may be circumferentially spaced along the inner surface 120 in an annular configuration relative to the centerline 35, thereby supplying air (A) to the mixing channel 114. At least some of the air outlets 144 surround corresponding fuel orifices in the set of fuel orifices 136, such that the air outlets 144 at least partially discharge air (A) around fuel (F) discharged from the corresponding fuel orifice. In some examples, the corresponding fuel orifices in the set of fuel orifices 136 may be centered within the air outlets in the set of air outlets 144. The fuel injector assembly 100 may include a corresponding air outlet in the set of air outlets 144 for each fuel orifice in the set of fuel orifices 136. In some examples, at least some of the airflow channels in the set of airflow channels 142 may include portions 143 that surround the corresponding fuel channels in the set of fuel channels 132 along the extension direction of the fuel channels through the mixing tube body 112 (e.g., axially rearward and radially inward toward the centerline 35). For example, the ratio of the mass flow rate of air (A) supplied from the set of air outlets 144 to the mass flow rate of fuel (F) supplied from the set of fuel orifices 136 to the mixing channel 114 may be greater than or equal to 0 and less than or equal to 100.

[0055] During operation of the fuel injector assembly 100, the fuel manifold 130 supplies fuel (F) to the set of fuel passages 132, and the fuel (F) flows through the set of fuel passages 132 and through the set of fuel orifices 136, such that the set of fuel orifices 136 discharges the fuel (F) into a mixing channel 114, in which the fuel (F) can be mixed at least partially with air (A) received from the inlet 116 of the mixing channel 114 and flowing toward the outlet 118 through the mixing tube 110 (e.g., along the centerline 35). Furthermore, the set of air outlets 144 discharges air (A) at least partially around the corresponding fuel orifices in the set of fuel orifices 136, such that the air (A) from the set of air outlets 144 promotes the movement of fuel (F) from the set of fuel orifices 136 toward the central portion of the mixing channel 114 (e.g., toward the centerline 35). This configuration increases fuel (F) penetration into the air (A) flowing from inlet 116 in mixing channel 114, which promotes mixing of fuel (F) and air (A) to form a more homogeneous fuel-air mixture (FA). A more homogeneous fuel-air mixture (FA) can provide better flame stability and lower flame temperature, for example, by limiting a richer fuel (F) pocket. Furthermore, this configuration promotes the movement of fuel (F) away from the inner surface 120, thereby reducing or preventing fuel (F) from lingering or remaining along the inner surface 120 of the mixing tube body 112, which could otherwise contribute to one or both flashback and flame sustaining within the mixing tube body 112.

[0056] For example, a fuel-air mixture (FA) may have a fuel-to-air mass ratio greater than or equal to 0.005 and less than or equal to 0.060. As a further non-limiting example, for at least some fuels, it is desirable for a fuel-air mixture to have a fuel-to-air mass ratio greater than or equal to 0.005 and less than or equal to 0.030.

[0057] The mixing length 150 of the mixing channel 114 may be defined for a portion of the mixing tube 110 in which air (A) and fuel (F) are mixed. The mixing length 150 may be measured in the axial direction (Ad) from the set of fuel orifices 136 to the outlet 118. The set of fuel orifices 136 may include an internal fuel orifice dimension 152 (e.g., hydraulic diameter). In some examples, the internal fuel orifice dimension 152 may be measured in the axial direction (Ad) between the upstream and downstream edges of the fuel orifice 136. It is contemplated that the internal fuel orifice dimension 152 may be the average of the internal dimensions measured between the upstream and downstream edges of the fuel orifice 136. The ratio of the mixing length 150 to the internal fuel orifice dimension 152 may range from 0 (e.g., at the outlet 118) to 200, including the endpoints.

[0058] The fuel injector assembly 100 (e.g., the mixing tube body 112) may include one or more turbulence generators 160, which may be at least partially disposed upstream of the set of fuel orifices 136. For example, the fuel injector assembly 100 may include a corresponding turbulence generator among the turbulence generators 160 for each fuel orifice in the set of fuel orifices 136. The turbulence generator 160 may include protrusions extending from the inner surface 120 into the mixing channel 114 to generate turbulence in the air (A) in the mixing channel 114. The turbulence can promote mixing of the air (A) entering the mixing channel 114 via inlet 116 with the air (A) and fuel (F) entering the mixing channel 114 via the set of air outlets 144 and the set of fuel orifices 136, respectively. For example, the turbulence generator 160 may be located directly upstream of the set of fuel orifices 136. In some examples, one or more of the turbulence generators 160 are configured as vortex generators. Vortex generators can include one or more of various configurations, such as counter-rotating, delta wing, double-sided wedge, wheel type, airfoil type, winglet type, Kuethe type, fork bone type, hairpin type, leaf type, wave type, or any combination thereof.

[0059] Although the fuel injector assembly 100 is shown without a central body tip, the fuel injector assembly 100 may optionally include a central body that is at least partially surrounded by the mixing tube body 112, extends in the axial direction (Ad) along the centerline 35, and is at least partially disposed in the mixing channel 114. The central body tip may include one or more channels for fuel (F), air (A), or combinations thereof.

[0060] Figures 4A-4E Is it along the direction perpendicular to the mixing pipe 110 ( Figure 3 This is a schematic diagram of an example configuration of the fuel orifices in the group of fuel orifices 136 and the air outlets in the group of air outlets 144, when viewed in a plane along the centerline 35. The middle portion 170 of the inner surface 120 is defined between the fuel orifices 136 and the air outlets 144. The group of fuel orifices 136 and the group of air outlets 144 may be concentric. Figure 4A ), or it can be offset ( Figure 4B Although in Figure 3 , Figure 4A and Figure 4B The air outlets 144 are shown as circular, but this group of air outlets 144 may include other suitable cross-sectional shapes, such as triangular shapes. Figure 4C ), oval shape ( Figure 4D ), sector shape ( Figure 4EOther shapes or combinations thereof. Some shapes of air outlets in this group of air outlets 144 can improve the amount of shielding or preventing movement of a portion of the fuel (F) leaving the corresponding fuel orifice in this group of fuel orifices 136. Increased shielding can increase fuel penetration, which can increase fuel-air mixing. Some shapes can induce turbulence in the discharged air (A) to varying degrees, thereby promoting mixing of air (A) and fuel (F) entering the mixing channel 114, which can reduce the richer fuel (F) pockets at one or both of the inner surfaces 120 of the mixing channel 114 and the mixing tube body 112, which can in turn provide lower flame temperatures and lower flashback or flame sustaining capabilities. Some shapes can be manufactured less complexly via drilling, such as circular shapes. Additionally or alternatively, some shapes can be manufactured less complexly via additive manufacturing, such as triangular shapes.

[0061] In some examples, such as from compressor section 12 ( Figure 1 ) provided to fuel injector assembly 100 ( Figure 3 The air (A) supplied to the fuel injector assembly 100 can be at a relatively high temperature (such as 1200°F or higher), while the fuel (F) supplied to the fuel injector assembly 100 can have a relatively low temperature (such as 500°F or lower, or 100°F or lower). In the fuel injector assembly 100 (such as the mixing tube body 112...), Figure 3 The presence of fuel (F) and air (A) at these different temperatures in the fuel injector assembly 100 can create a thermal gradient between the portions of the fuel injector assembly 100 that are in thermal contact with the relatively hot air (A) and the relatively cold fuel (F). These thermal gradients cause portions of the fuel injector assembly 100 to experience increased thermal stress, which can wear and degrade portions of the fuel injector assembly 100 (e.g., the inner surface 120 of the mixing tube body 112). An airflow passage 142 is provided around the fuel passage 132 in a circumferential arrangement. Figure 3 This can reduce the thermal gradient in the portion of the mixing tube body 112 adjacent to or in thermal contact with the fuel (F), which can limit thermal stress and reduce wear and degradation of the fuel injector assembly 100.

[0062] refer to Figure 5 It provides suitable use as Figure 2 The fuel injector assembly 48 in the fuel injector assembly 200. Figure 5 The fuel injector assembly 200 can be with Figure 3 The fuel injector assembly 100 is substantially similar; therefore, similar parts will be identified by similar numbers increasing to the 200 series. It should be understood that, unless otherwise stated, the fuel injector assembly 100 ( Figure 3 The description can be applied to fuel injector assembly 200.

[0063] For example, the fuel injector assembly 200 may include: a mixing tube 210 having a mixing tube body 212 defining a mixing channel 214; an air supply section 204 supplying air (A) to the mixing channel 214; and a fuel supply section 202 supplying fuel (F) to the mixing channel 214. The air supply section 204 may include an inlet 216 of the mixing channel 214 and a set of airflow passages 242. These airflow passages 242 may be at least partially defined within the mixing tube body 212. The fuel supply section 202 may include a fuel manifold 230 and a set of fuel passages 232 terminating at a set of fuel tips 234 having a set of fuel orifices 236 defined in an inner surface 220 of the mixing tube body 212. The rear end of the mixing tube body 212 defines an outlet 218 of the mixing channel 214, which is fluidly connected to the combustion chamber 50 to discharge fluids (such as fuel-air mixture (FA)) from the fuel injector assembly 200 into the combustion chamber 50.

[0064] Some or each of the airflow channels 242 may include a set of first air outlets 244 defined by the inner surface 220 of the mixing tube body 212, which supply air (A) to the mixing channel 214. At least some of the first air outlets 244 surround corresponding fuel orifices in the set of fuel orifices 236, such that the first air outlets 244 at least partially discharge air (A) around fuel (F) discharged from the corresponding fuel orifice in the set of fuel orifices 236, such as to... Figure 3 The group of air outlets 144 and the group of fuel orifices 136 are similar in manner. The group of air flow channels 242 may include a group of second air outlets 246 along a portion of the inner surface 220 of the mixing tube body 212, which supply air (A) to the mixing channel 214. In some examples, the fuel injector assembly 200 may include at least some air flow channels 242 having portions 243 that surround corresponding fuel channels in the group of fuel channels 232 along the extension direction of the fuel channels through the mixing tube body 212.

[0065] like Figure 6AAs shown, one or more first air outlets in the group of first air outlets 244 may surround a corresponding fuel orifice in the group of fuel orifices 236 to define a middle portion 270 of the inner surface 220 between the fuel orifice 236 and the first air outlets 244, and one or more second air outlets in the group of second air outlets 246 may at least partially overlap with a corresponding first air outlet in the group of first air outlets 244 to have an overlapping configuration. Area overlap may be defined as a percentage of the area of ​​the second air outlet 246 defined in the inner surface 220 that overlaps or covers the first air outlet 244 relative to the area of ​​the first air outlet 244 defined in the inner surface 220. For example, area overlap may range from 10% to 50%.

[0066] like Figure 6B As shown, one or more first air outlets in the group of first air outlets 244 may surround the corresponding fuel orifice in the group of fuel orifices 236 to define a middle portion 270 of the inner surface 220 between the fuel orifice 236 and the first air outlet 244, wherein one or more second air outlets in the group of second air outlets 246 may be different from and adjacent to the corresponding first air outlet in the group of first air outlets 244 to define an offset configuration (e.g., 0% area overlap). For example, the second air outlet 246 may be defined in the inner surface 220 and may be set at a distance D from the corresponding first air outlet. The distance D may be measured along the inner surface 220 from the first air outlet 244 to the second air outlet 246. In some examples, the distance D may be within 10% of the inner dimension (e.g., hydraulic diameter) of the first air outlet 244 defined in the inner surface 220. The group of second air outlets 246 may be at least partially upstream of the corresponding first air outlet in the group of first air outlets 244. In some examples, some of the first air outlets in the set of first air outlets 244, which are offset, and the corresponding second air outlets in the set of second air outlets 246, can be fluidly connected to different air flow channels in the set of air flow channels 242.

[0067] In some examples, the group of second air outlets 246 may include a combination of one or more pairs of second air outlets and corresponding first air outlets in an overlapping configuration, and a combination of one or more pairs of second air outlets and corresponding first air outlets in an offset configuration. Furthermore, although the first air outlet 244 is... Figure 5 , Figure 6A and Figure 6B The center is shown as circular, but the first air outlet 244 may include other shapes, such as Figure 4B-E shows the configuration, other shapes, or combinations thereof for the air outlet 144 of this group. In some aspects, the disclosed burner and fuel injector assemblies can be used with gaseous fuels (such as hydrogen), and with conventional fuels (such as kerosene (e.g., Jet A), diesel, natural gas, methane, ammonia, combinations of conventional fuels, or combinations of hydrogen and one or more conventional fuels). Gaseous fuels, including hydrogen, diffuse or disperse at a faster rate than atomized conventional fuels. This can involve a shorter mixing time for the gaseous fuel, a shorter fuel mixing tube length, and a flame from the gaseous fuel is more likely to spread further and faster. This increases the risk of blowouts and enhances the control of the flame and limits its spread by controlling the dispersion of the gaseous fuel.

[0068] In addition to those shown in the accompanying drawings, this disclosure envisions many other possible aspects and configurations. For example, compared to other designs, the disclosed fuel injector assembly can provide better flame stability, lower flame temperature, and lower NO₂. x emission.

[0069] The fuel injector assembly disclosed herein may include at least a number of air outlets surrounding a corresponding fuel orifice and at least partially surrounding the air (A) discharged from the corresponding fuel orifice. This can limit thermal stress and reduce wear and degradation of the portions of the fuel injector assembly in thermal contact with both air and fuel due to these thermal stresses. Additionally or alternatively, this surrounding configuration of the air outlets around the fuel orifice can increase fuel permeation into the air to promote mixing and produce a more homogeneous fuel-air mixture, thereby reducing NO. x Emissions. Turbulence generators extending into the mixing channels of the fuel injector assembly can generate turbulence to improve fuel and air mixing.

[0070] Although a turbine engine has been described, it should be understood that the combustor described herein can be used in any engine having a combustor. It should also be understood that the application of the disclosed aspects discussed herein also applies to engines having a propeller section or a fan and supercharger section, as well as turbojet engines and turbocharged engines.

[0071] Within the scope not yet described, different features and structures of various embodiments may be combined or substituted for each other as needed. The fact that a feature is not shown in all embodiments does not mean that it cannot be shown so, but rather that it is done for the sake of brevity. Therefore, various features of different embodiments may be mixed and matched as needed to form new embodiments, regardless of whether the new embodiments are explicitly described. All combinations or permutations of the features described herein are covered by this disclosure. For example, but not limited to, a burner may include various combinations of fuel injector assemblies. In some examples, the same burner may include having… Figure 3 , Figure 4A -E、 Figure 5 , Figures 6A-6B Fuel injector components of any combination as shown.

[0072] This written description uses examples to illustrate aspects of the disclosure described herein, including best practices, and also enables any person skilled in the art to practice aspects of this disclosure, including making and using any apparatus or system and methods of making any combinations. The patentable scope of aspects of this disclosure is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

[0073] Further details are provided by the following topics:

[0074] A gas turbine engine includes: a compressor section, a combustion section, and a turbine section arranged in a series flow configuration, wherein the combustion section includes: a combustor bushing that at least partially defines a combustion chamber; and a fuel injector assembly including: a mixing tube having a mixing tube body having an inner surface that at least partially defines a mixing channel having an outlet fluidly connected to the combustion chamber; a set of fuel passages having a set of fuel orifices arranged circumferentially along the inner surface; and a set of air flow passages having a set of air outlets arranged on the inner surface, wherein at least one of the set of air outlets surrounds a corresponding fuel orifice in the set of fuel orifices.

[0075] According to any of the foregoing clauses, the gas turbine engine wherein the at least one air outlet is annular.

[0076] In any of the preceding clauses, the gas turbine engine wherein the corresponding fuel orifice is centered within the at least one air outlet.

[0077] The gas turbine engine according to any of the foregoing clauses, wherein the set of air outlets includes an air outlet for each fuel orifice.

[0078] According to any of the foregoing clauses, in a gas turbine engine, at least one of the airflow passages in the set of airflow passages includes a portion surrounding a corresponding fuel passage in the set of fuel passages along the extension direction of the fuel passage through the mixing tube body.

[0079] A gas turbine engine according to any of the foregoing clauses, wherein the fuel injector assembly includes a fuel manifold at least partially defined by the mixing pipe body; and wherein a set of fuel passages extends from the fuel manifold to the mixing channel.

[0080] The gas turbine engine according to any of the foregoing clauses, wherein the fuel manifold has an annular configuration around the mixing channel.

[0081] According to any of the foregoing clauses, in a gas turbine engine, the set of fuel passages further includes a set of fuel tips; and wherein the set of fuel tips extends to the set of fuel orifices.

[0082] The gas turbine engine according to any of the foregoing clauses further includes one or more turbulence generators having protrusions extending into the mixing channel.

[0083] A gas turbine engine according to any of the foregoing clauses, wherein the one or more turbulence generators are upstream of the set of fuel orifices.

[0084] According to any of the foregoing clauses, a gas turbine engine is provided with a corresponding turbulence generator for each fuel orifice.

[0085] According to any of the preceding clauses, in a gas turbine engine, the cross-sectional shape of at least one of the group of air outlets can include a circular shape, a triangular shape, an elliptical shape, or a fan shape.

[0086] According to any of the preceding clauses, in a gas turbine engine, the ratio of the mass flow rate of air supplied from the set of air outlets to the mass flow rate of fuel supplied from the set of fuel orifices to the mixing channel is greater than or equal to 0 and less than or equal to 100.

[0087] According to any of the preceding clauses, the gas turbine engine wherein the fuel-air mixture stream supplied from the outlet to the combustion chamber has a fuel-to-air mass ratio greater than or equal to 0.005 and less than or equal to 0.060.

[0088] According to any of the preceding clauses, the gas turbine engine has a mixing channel having a mixing length measured from the set of fuel orifices to the outlet, the set of fuel orifices having an in-orifice dimension measured between the upstream and downstream edges of each fuel orifice in the set of fuel orifices, and the ratio of the mixing length to the in-orifice dimension is in the range of 0 to 200, including the endpoints.

[0089] According to any of the preceding clauses, the gas turbine engine wherein the set of air outlets is a set of first air outlets and the fuel injector assembly includes a set of second air outlets, the set of second air outlets being at least partially upstream of the set of first air outlets.

[0090] According to any of the foregoing clauses, in a gas turbine engine, at least one of the second air outlets in the set of second air outlets is offset from the corresponding first air outlet in the set of first air outlets.

[0091] According to any of the foregoing clauses, in a gas turbine engine, at least one of the second air outlets in the set of second air outlets is configured to overlap with a corresponding first air outlet in the set of first air outlets.

[0092] According to any of the preceding clauses, the gas turbine engine, wherein the set of second air outlets includes at least one second air outlet configured to be offset from a corresponding first air outlet in the set of first air outlets and at least one second air outlet configured to overlap with a corresponding first air outlet in the set of first air outlets.

[0093] A fuel injector assembly for a gas turbine engine includes: a mixing tube having a mixing tube body having an inner surface that at least partially defines a mixing channel having an outlet fluidly connected to a combustion chamber; a set of fuel passages having a set of fuel orifices arranged circumferentially along the inner surface; and a set of airflow passages having a set of air outlets arranged on the inner surface, wherein at least one of the air outlets surrounds a corresponding fuel orifice in the set of fuel orifices.

[0094] According to any of the foregoing clauses, the fuel injector assembly wherein the at least one air outlet is annular.

[0095] According to any of the preceding clauses, the fuel injector assembly wherein the corresponding fuel orifice is centered within the at least one air outlet.

[0096] According to any of the preceding clauses, the fuel injector assembly wherein at least one of the set of airflow channels has a portion surrounding a corresponding fuel channel in the set of fuel channels along the extension direction of the fuel channel through the mixing tube body.

[0097] According to any of the preceding clauses, the cross-sectional shape of at least one of the group of air outlets can include a circular shape, a triangular shape, an elliptical shape, or a fan shape.

[0098] According to any of the preceding clauses, the ratio of the mass flow rate of air supplied from the set of air outlets to the mass flow rate of fuel supplied from the set of fuel orifices to the mixing channel is greater than or equal to 0 and less than or equal to 100.

[0099] According to any of the preceding clauses, the fuel injector assembly wherein the fuel-air mixture stream supplied from the outlet to the combustion chamber has a fuel-to-air mass ratio greater than or equal to 0.005 and less than or equal to 0.060.

[0100] According to any of the preceding clauses, the fuel injector assembly wherein the mixing channel has a mixing length measured from the set of fuel orifices to the outlet, the set of fuel orifices has an in-orifice dimension measured between the upstream and downstream edges of each of the set of fuel orifices, and the ratio of the mixing length to the in-orifice dimension is in the range of 0 to 200, including the endpoints.

[0101] According to any of the preceding clauses, the set of air outlets is a set of first air outlets, and the fuel injector assembly includes a set of second air outlets, the set of second air outlets being at least partially upstream of the set of first air outlets, the set of second air outlets including at least one of: a second air outlet offset from a corresponding first air outlet in the set of first air outlets, or a second air outlet overlapping a corresponding first air outlet in the set of first air outlets.

[0102] According to any of the foregoing clauses, the fuel injector assembly wherein the set of air outlets includes an air outlet for each fuel orifice.

[0103] A fuel injector assembly according to any of the foregoing clauses, wherein the fuel injector assembly includes a fuel manifold at least partially defined by the mixing tube body; and wherein a set of fuel passages extends from the fuel manifold to the mixing channel.

[0104] The fuel injector assembly according to any of the foregoing clauses, wherein the fuel manifold has an annular configuration around the mixing channel.

[0105] According to any of the preceding clauses, the fuel injector assembly wherein the set of fuel channels further includes a set of fuel tips; and wherein the set of fuel tips extends to the set of fuel orifices.

[0106] The fuel injector assembly according to any of the foregoing clauses further includes one or more turbulence generators having protrusions extending into the mixing channel.

[0107] The fuel injector assembly according to any of the foregoing clauses, wherein the one or more turbulence generators are upstream of the set of fuel orifices.

[0108] According to any of the foregoing clauses, the fuel injector assembly has a corresponding turbulence generator for each fuel orifice.

[0109] According to any of the preceding clauses, the set of air outlets is a set of first air outlets, and the fuel injector assembly includes a set of second air outlets, the set of second air outlets being at least partially upstream of the set of first air outlets.

[0110] According to any of the foregoing clauses, the fuel injector assembly wherein at least one of the set of second air outlets is offset from the corresponding first air outlet of the set of first air outlets.

[0111] According to any of the preceding clauses, the fuel injector assembly wherein at least one of the set of second air outlets is configured to overlap with a corresponding first air outlet of the set of first air outlets.

[0112] According to any of the preceding clauses, the set of second air outlets includes at least one second air outlet configured to be offset from a corresponding first air outlet in the set of first air outlets and at least one second air outlet configured to overlap with a corresponding first air outlet in the set of first air outlets.

Claims

1. A gas turbine engine, characterized in that, include: A compressor section, a combustion section, and a turbine section are arranged in a series flow configuration, wherein the combustion section includes: A burner bushing, the burner bushing at least partially defining a combustion chamber; and Fuel injector assembly, the fuel injector assembly comprising: A mixing tube having a mixing tube body having an inner surface that at least partially defines a mixing channel having an outlet fluidly connected to the combustion chamber; A set of fuel channels, the set of fuel channels having a set of fuel orifices arranged circumferentially along the inner surface; and A set of airflow channels having a set of air outlets arranged on the inner surface, wherein at least one of the air outlets surrounds a corresponding fuel orifice in the set of fuel orifices.

2. The gas turbine engine according to claim 1, characterized in that, in, The at least one air outlet is annular.

3. The gas turbine engine according to claim 2, characterized in that, in, The corresponding fuel orifice is centered within at least one air outlet.

4. The gas turbine engine according to claim 3, characterized in that, in, The set of air outlets includes an air outlet for each fuel orifice.

5. The gas turbine engine according to claim 1, characterized in that, in, At least one of the set of airflow channels includes a portion surrounding the corresponding fuel channel in the set of fuel channels along the extension direction of the fuel channel through the mixing tube body.

6. The gas turbine engine according to claim 1, characterized in that, in, The fuel injector assembly includes a fuel manifold at least partially defined by the mixing tube body; and The set of fuel passages extends from the fuel manifold to the mixing channel.

7. The gas turbine engine according to claim 6, characterized in that, in, The fuel manifold has an annular structure surrounding the mixing channel.

8. The gas turbine engine according to claim 1, characterized in that, in, The set of fuel channels further includes a set of fuel tips; and The set of fuel tips extends into the set of fuel orifices.

9. The gas turbine engine according to claim 1, characterized in that, It further includes one or more turbulence generators having protrusions extending into the mixing channel.

10. The gas turbine engine according to claim 9, characterized in that, in, The one or more turbulence generators are upstream of the set of fuel orifices.

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