Gas turbine engine including fuel injector

Abstract

A gas turbine engine includes a fuel injector having an outer valve body having an inner passage, a wall at least partially surrounding the inner passage, the wall having an inner surface, an outer surface, and one or more passages through the wall between the outer surface of the wall and the inner surface of the wall, and a retractable valve body, a retractable valve body is positioned within the inner passage of the outer valve body. The retractable valve body has one or more slots in fluid communication with the fluid rotating chamber. A retractable valve body is positioned within the internal passage to move along a reciprocating axis at one or more valve positions, including an advanced valve position, a retracted valve position, an open valve position, and a closed valve position.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to a gas turbine engine including a fuel injector, such as a gas turbine engine for an aircraft. BACKGROUND

[0002] A gas turbine engine generally includes a compressor section, a combustor section, and a turbine section. A fuel injector can inject fuel into the combustor section arranged in a turbofan engine to produce combustion gases for driving the turbine section. BRIEF DESCRIPTION OF DRAWINGS

[0003] Features and advantages will be apparent from the following more detailed description, taken in conjunction with the accompanying drawings, in which like reference characters generally refer to like, functionally similar, or analogous elements, and in which:

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

[0005] Figure 2A is a schematic cross-sectional view of a first fuel injector of the turbine engine of Figure 1

[0006] Figure 2B is a schematic cross-sectional view of the first fuel injector of Figure 2A Figure 2A

[0007] Figure 3A is a schematic cross-sectional view of the first fuel injector of

[0008] Figure 3B is a schematic cross-sectional view of the first fuel injector of Figure 3A Figure 3A

[0009] Figure 4A is a schematic cross-sectional view of the first fuel injector of

[0010] Figure 4B is a schematic cross-sectional view of the first fuel injector of Figure 4A Figure 4A

[0011] Figure 5A is a schematic cross-sectional view of the first fuel injector of ​​​​​​​

[0012] Figure 5B It is based on the disclosure of this disclosure. Figure 5A A schematic cross-sectional detail of a portion of the retractable valve body in its partially open valve position, showing... Figure 5A Details 5B.

[0013] Figure 6 This is a schematic cross-sectional view of the second retractable valve body according to this disclosure.

[0014] Figure 7 This is a schematic cross-sectional view of the third retractable valve body according to this disclosure.

[0015] Figure 8 This is a schematic diagram of a portion of the fourth retractable valve body according to this disclosure.

[0016] Figure 9 This is a schematic diagram of a portion of the fifth retractable valve body according to this disclosure.

[0017] Figure 10A This is a schematic diagram of a sixth retractable valve body with three orifices according to the present disclosure.

[0018] Figure 10B This is a schematic diagram of a seventh retractable valve body having three orifices arranged in an alternating and overlapping configuration, according to the present disclosure.

[0019] Figure 11A Based on this disclosure and Figure 1 A schematic cross-sectional view of the second fuel injector isolated by the turbine engine and in the closed valve position.

[0020] Figure 11B This is a schematic cross-sectional view of the second fuel injector in the open valve position according to this disclosure.

[0021] Figure 12A This is a schematic cross-sectional view of a piston-type fuel injector according to the present disclosure, the piston-type fuel injector including a piston in the closed valve position, and... Figure 1 Turbine engine isolation.

[0022] Figure 12B A schematic cross-sectional detail of a piston fuel injector according to this disclosure shows... Figure 12A Details 12B.

[0023] Figure 13A This is a schematic cross-sectional view of a piston-type fuel injector according to the present disclosure, which includes a piston in the open valve position.

[0024] Figure 13B A schematic cross-sectional detail of a piston fuel injector according to this disclosure shows...Figure 13A Details 13B.

[0025] Figure 14 Based on this disclosure Figure 15 A cross-sectional view of the first piston housing of a piston-type fuel injector.

[0026] Figure 16 This is a schematic cross-sectional side view of a portion of the first piston housing according to the present disclosure.

[0027] Figure 17 This is a schematic cross-sectional side view of a portion of a second piston housing having an oval channel according to the present disclosure.

[0028] Figure 18 This is a schematic cross-sectional side view of a portion of a third piston housing having a grooved channel according to the present disclosure.

[0029] Figure 19 This is a schematic cross-sectional side view of a fourth piston housing having angled channels according to the present disclosure.

[0030] Figure 20 This is a cross-sectional view of a fifth piston housing having a tapered channel according to the present disclosure.

[0031] Figure 1 This is a schematic diagram of a method for injecting fuel into the combustion zone according to the present disclosure. Detailed Implementation

[0032] The features, advantages, and embodiments of this disclosure will be set forth or apparent from consideration of the following detailed description, drawings, and claims. Furthermore, the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0033] Various embodiments of this disclosure are discussed in detail below. While specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and configurations can be used without departing from this disclosure.

[0034] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0035] 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.

[0036] The terms "forward" and "aft" refer to relative positions within a turbine engine or vehicle and refer to the normal operating attitude of the turbine engine or vehicle. For example, with respect to a high-bypass turbine engine, forward refers to a position closer to the engine inlet and aft refers to a position closer to the engine nozzle or exhaust. In one example, in a reverse flow turbine engine, forward refers to a position closer to the engine nozzle or exhaust and aft refers to a position closer to the engine inlet.

[0037] Unless otherwise provided herein, the terms "coupled," "fixed," "attached," "connected," and the like, refer to both direct and indirect coupling, fixation, attachment, or connection, through one or more intermediate components or features.

[0038] Unless the context clearly indicates otherwise, the singular forms "a," "an," and "the" include plural referents.

[0039] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to a centerline of the turbine engine. Further, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Further, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends arcuately about the centerline of the turbine engine.

[0040] As used herein, a "closed valve position" of a variable fuel flow system refers to components of the variable fuel flow system covering one or more fuel injector flow paths to prevent fuel flow to the one or more fuel injector flow paths.

[0041] As used herein, a "partially open valve position" of a variable fuel flow system refers to components of the variable fuel flow system partially covering and partially not covering a fuel injector flow path such that fuel flows through the fuel injector flow path that is not partially covered.

[0042] As used herein, a "fully open valve position" of a variable fuel flow system refers to components of the variable fuel flow system fully (e.g., entirely) not covering a fuel injector flow path such that fuel flows through the fuel injector flow path that is not fully covered.

[0043] As used herein throughout the specification and claims, approximate language is used to modify any quantitative representation that can permit variations without changing the basic function to which the representation is directed. Thus, a value modified by one or more terms or phrases such as “about,” “approximately,” “generally,” and “substantially” is not limited to the precise value specified. In at least some instances, the approximate language can correspond to the precision of an instrument used to measure the value, or the precision to which a component or system is constructed or a method or machine is manufactured. For example, the approximate language can refer to being within one percent, two percent, four percent, ten percent, fifteen percent, or twenty percent of a single value, a range of values, or an endpoint of a defined range of values.

[0044] Throughout this specification and claims, range limitations are combined and interchanged, unless the context or language indicates otherwise. Such ranges are identified and include all sub-ranges included therein. For instance, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other. Throughout this specification and claims, plural instances can implement components, operations, or structures described as a single instance. Unless otherwise specified, the instances can be combined with one another, independent of any other instance. Unless otherwise specified, “or” as used herein is inclusive, i.e., the phrase “A or B” means “A or B or both.” Unless otherwise specified, “and” as used herein is both conjunctive and disjunctive, i.e., the phrase “A and / or B” means “A and / or B” and “A and B.” The scope of the specification is not intended to be limited to the specific embodiments described herein. The above specification, examples and data provide essential information for enabling those with ordinary skill in the art to make and use the application. The present specification is well adapted to

[0045] The present disclosure provides a fuel injector having an outer valve body having an inner passage, a wall at least partially surrounding the inner passage, the wall having an inner surface, an outer surface, and one or more passages through the wall between the outer surface of the wall and the inner surface of the wall, and a retractable valve body positioned within the inner passage of the outer valve body. The retractable valve body has one or more slots in fluid communication with a fluid rotation chamber. The retractable valve body is positioned within the inner passage to move along a reciprocating axis at one or more valve positions, including an advanced valve position, a retracted valve position, an open valve position, and a closed valve position.

[0046] The fuel injector of the present disclosure varies fuel flow through the fuel injector. The fuel injector of the present disclosure can produce a higher delta pressure at or near the injection point during all operating conditions of a turbine engine. For example, the fuel injector can include a retractable valve body and an actuation mechanism coupled to the retractable valve body. The retractable valve body can be disposed within an inner passage of the fuel injector and include slots for directing fuel through the retractable valve body between the inner passage and a fluid rotation chamber of the retractable valve body. The retractable valve body can slide back and forth within the inner passage along a reciprocating axis to open and close an orifice of the fuel injector. As the retractable valve body slides back and forth, the orifice on the retractable valve body aligns partially or completely with passages of an outer valve body in the fuel injector. This alignment produces a variable inlet area of the orifice of the fuel injector for producing a higher delta pressure across the fuel injector compared to a fuel injector without the benefits of the present disclosure.

[0047] In some embodiments, a pressure atomizer is disposed within the fuel injector for assisting 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.) that is controlled to move the piston.

[0048] Accordingly, the fuel injector of the present disclosure provides several advantages over turbine engines that do not benefit from the present disclosure. For example, the fuel injector regulates a pressure differential for increasing atomization of the fuel and air. The increased atomization and mixing of the fuel and air makes the fuel and air mixture easier to ignite and burn compared to turbine engines that do not benefit from the present disclosure. Accordingly, the fuel injector provides improved ignition capability by increasing atomization of the fuel and air, particularly for cold fuel (e.g., at higher altitudes) or high viscosity fuel. The fuel injector results in improved sub-idle efficiency and low power efficiency of the combustor and produces less smoke at high power operation due to the increased atomization compared to turbine engines that do not benefit from the present disclosure.

[0049] Referring now to the drawings, Figure 1 is a schematic cross-sectional view of a turbine engine 10 taken along a longitudinal centerline axis 12 of the turbine engine 10 in accordance with an embodiment of the present disclosure. As shown, Figure 1 The turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 provided for reference) and a radial direction R orthogonal to the axial direction A. Generally, the turbine engine 10 includes a fan section 14 and a turbocharger engine 16 disposed downstream of the fan section 14.

[0050] The turbocharger engine 16 includes a compressor section 21, a combustion section 26, and a turbine section 27 in serial flow relationship. The turbocharger engine 16 is substantially enclosed within a casing 18 that is substantially tubular and defines an annular inlet 20. As shown, Figure 1Illustratively, the compressor section 21 includes a booster or low pressure (LP) compressor 22 followed downstream by a high pressure (HP) compressor 24. A combustion section 26 is located downstream of the compressor section 21. A turbine section 27 is located downstream of the combustion section 26 and includes a high pressure (HP) turbine 28 followed downstream by a low pressure (LP) turbine 30. The turbocharged engine 16 also includes an ejection exhaust nozzle section 32 located downstream of the turbine section 27, a high pressure (HP) shaft 34 or spool, and a low pressure (LP) shaft 36. The HP shaft 34 drivingly connects the HP turbine 28 to the HP compressor 24. The HP turbine 28 and the HP compressor 24 are rotationally uniform via the HP shaft 34. The LP shaft 36 drivingly connects the LP turbine 30 to the LP compressor 22. The LP turbine 30 and the LP compressor 22 are rotationally uniform via the LP shaft 36. The compressor section 21, the combustion section 26, the turbine section 27, and the ejection exhaust nozzle section 32 together define a core air flow path.

[0051] For Figure 1 the illustrated embodiment, the fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 coupled to a disk 42 in a spaced apart manner. As Figure 1 illustrated, the fan blades 40 generally extend outwardly from the disk 42 along a radial direction R. In the case of a variable pitch fan, the plurality of fan blades 40 are rotatable relative to the disk 42 about a pitch axis P by virtue of the fan blades 40 being operably coupled to an actuation member 44 configured to collectively and uniformly change the pitch of the fan blades 40. The fan blades 40, the disk 42, and the actuation member 44 are rotatable together about the longitudinal centerline axis 12 via a fan shaft 45, which is powered across a power gear box (also referred to as a gear box assembly 46) by the LP shaft 36. As such, the fan 38 is drivingly coupled to and powered by the turbocharged engine 16, and the turbine engine 10 is an indirectly driven engine. The gear box assembly 46 is illustratively shown in Figure 1 . The gear box assembly 46 is a reduction gear box assembly for adjusting the rotational speed of the fan shaft 45, and thus the rotational speed of the fan 38 relative to the LP shaft 36, when power is transferred from the LP shaft 36 to the fan shaft 45.

[0052] Still referring to Figure 1In exemplary embodiments of the turbofan engine 10, the disk 42 is covered by a fan hub 48 having an aerodynamic profile to facilitate airflow through the plurality of fan blades 40. Further, the fan section 14 includes an annular fan casing or nacelle 50 that circumferentially surrounds the fan 38 and at least a portion of the turbocharger engine 16. The nacelle 50 is supported relative to the turbocharger engine 16 by a plurality of outlet guide vanes 52 circumferentially spaced about the nacelle 50 and the turbocharger engine 16. Further, a downstream section 54 of the nacelle 50 extends over an outer portion of the turbocharger engine 16 and, together with the outer casing 18, defines a bypass airflow passage 56 therebetween.

[0053] During operation of the turbofan engine 10, a volume of air 58 enters the turbofan engine 10 through an inlet 60 of the nacelle 50 or fan section 14. As the volume of air 58 passes through the fan blades 40, a first portion of the air, also referred to as bypass air 62, is directed into the bypass airflow passage 56 and a second portion of the air, also referred to as core air 64, is directed into an upstream section of the core air flowpath through the annular inlet 20 of the LP compressor 22. The ratio between the bypass air 62 and the core air 64 is commonly referred to as the bypass ratio. The pressure of the core air 64 is then increased, producing compressed air 65. The compressed air 65 is directed through the HP compressor 24 and into the combustion section 26 where it is mixed with fuel and ignited to produce combustion gases 66.

[0054] The combustion gases 66 are directed into and expanded through the HP turbine 28 where a portion of the thermal or kinetic energy from the combustion gases 66 is extracted via one or more stages of HP turbine stator vanes 68 and HP turbine rotor blades 70 coupled to the HP shaft 34. This causes the HP shaft 34 to rotate, thereby supporting operation of the HP compressor 24 (self-sustaining cycle). As such, the combustion gases 66 do work on the PH turbine 28. The combustion gases 66 are then directed into and expanded through the LP turbine 30. Here, a second portion of the thermal or kinetic energy is extracted from the combustion gases 66 via one or more stages of LP turbine stator vanes 72 and LP turbine rotor blades 74 coupled to the LP shaft 36. This causes the LP shaft 36 to rotate, thereby supporting operation of the LP compressor 22 (self-sustaining cycle) and rotation of the fan 38 via the gear box assembly 46. As such, the combustion gases do work on the LP turbine 30.

[0055] The combustion gases 66 are then directed through the injection exhaust nozzle section 32 of the turbocharged engine 16 to provide propulsive thrust. At the same time, the bypass air 62 is directed through the bypass airflow passage 56 before being exhausted from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. The HP turbine 28, the LP turbine 30, and the injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing the combustion gases 66 through the turbocharged engine 16.

[0056] The turbine engine 10 includes a fuel system that provides fuel to the combustion section 26. The fuel is mixed with the compressed air 65 from the HP compressor 24 and ignited in the combustion section 26 to produce the combustion gases 66. The fuel system can include a fuel tank or fuel supply, fuel supply lines, and fuel injectors for storing fuel therein. Fuel is provided from the fuel tank along the fuel supply lines to the fuel injectors, which introduce the fuel into the combustion section 26. The fuel system can include one or more flow control devices or valves along the fuel supply lines for controlling the amount of fuel provided to the combustion section 26. The fuel injectors can be disposed at the forward end of the combustion section 26. Thus, fuel provided along the fuel supply lines is provided at the forward end of the combustion section 26.

[0057] The controller 83 is in communication with the turbine engine 10 for controlling various aspects of the turbine engine 10. For example, the controller 83 is in bi-directional communication with the turbine engine 10 for receiving signals from various sensors and control systems of the turbine engine 10 and for controlling components of the turbine engine 10, as described in further detail below. The controller 83, or components thereof, can be located on the turbine engine 10, on the aircraft, or can be located remotely from each of the turbine engine 10 and the aircraft. The controller 83 can be a full authority digital engine control (FADEC) that controls various aspects of the turbine engine 10.

[0058] The controller 83 can be a stand-alone controller or can be part of an engine controller to operate various systems of the turbine engine 10. In this embodiment, the controller 83 is a computing device having one or more processors and memory. The one or more processors can be any suitable processing device, including but not limited to a microprocessor, microcontroller, integrated circuit, logic device, programmable logic controller (PLC), application specific integrated circuit (ASIC), or field programmable gate array (FPGA). The memory can include one or more computer-readable media, including, but not limited to, non-transitory computer-readable media, computer-readable non-volatile media (e.g., flash memory), RAM, ROM, hard drives, flash drives, or other memory devices.

[0059] The memory can store information accessible to the one or more processors, including computer-readable instructions that can be executed by the one or more processors. The instructions can be any set of instructions, or sequence of instructions, that, when executed by the one or more processors, cause the one or more processors and controller 83 to perform operations. Controller 83, and more specifically the one or more processors, are programmed or configured to execute these operations, such as the operations discussed further below. In some embodiments, the instructions can be executed by the one or more processors to cause the one or more processors to complete any of the operations and functions for which controller 83 is configured, as will be further described below. The instructions can be software written in any suitable programming language or can be implemented in hardware. Additionally, or alternatively, the instructions can be executed in logically and virtually independent threads on processor(s). Memory can also store data that can be accessed by the one or more processors.

[0060] The technology discussed herein makes reference to computer-based systems and actions performed by and information sent to and from computer-based systems. The patentable scope of the present disclosure is defined by the claims.

[0061] Figure 2A The turbine engine 10 shown is by way of example only. In other example embodiments, the turbine engine 10 can have any other suitable configuration. For example, in other example embodiments, the fan 38 can be configured in any other suitable manner (e.g., as a fixed-pitch fan) and can also be supported using any other suitable fan frame configuration. The turbine engine 10 can also be a direct drive engine that does not have a power gear box. The fan speed is the same as the LP shaft speed of the direct drive engine. Further, in other example embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof can be provided. In still other example embodiments, various aspects of the present disclosure can be incorporated into any other suitable turbine engine, such as a turbofan engine, a propfan engine, a turbojet engine, a turboprop engine, or a turboshaft engine.

[0062] Figure 1 is a schematic cross-sectional view of a turbine engine isolated first fuel injector in accordance with the present disclosure Figure 2B is a schematic cross-sectional view of a turbine engine isolated first fuel injector in accordance with the present disclosure Figure 2A is a schematic cross-sectional view of a turbine engine isolated first fuel injector in accordance with the present disclosure Figure 2Aa schematic cross-sectional detail view of a portion of the first fuel injector, showing Figure 1 Details 2B in the first fuel injector 100 includes a fuel nozzle housing 106, a fuel nozzle tip 120, and an outer valve body 110. The outer valve body 110 includes a wall 116 that at least partially encloses an inner passage 118. The wall 116 has an inner surface 112 facing the inner passage 118, an outer surface 114 on an opposite side of the wall 116 from the inner passage 118, and one or more passages 128 through the wall 116 between the outer surface 114 and the inner surface 112.

[0063] A retractable valve body 108 is positioned within the inner passage 118. The retractable valve body 108 is movable within the inner passage 118 along a reciprocating axis 101 between an advanced valve position and a retracted valve position. The advanced valve position is a valve position such that the retractable valve body 108 is positioned closest to the secondary fuel nozzle 124 along the reciprocating axis 101, and the retracted valve position is a valve position such that the retractable valve body 108 is positioned furthest from the secondary fuel nozzle 124 along the reciprocating axis 101. In other configurations, the secondary fuel nozzle can be a primary or separate fuel nozzle within the first fuel injector 100. For example, the first fuel injector 100 provides a higher pressure drop at the tip such that the secondary fuel nozzle can be the only nozzle in the first fuel injector 100.

[0064] The retractable valve body 108 has a fluid rotation chamber 122 and one or more slots 130 that fluidly connect the fluid rotation chamber 122 to respective orifices 126 positioned to face the inner passage 118. Movement of the retractable valve body 108 along the reciprocating axis 101 between the advanced valve position and the retracted valve position results in the retractable valve body 108 being positioned at one or more valve positions including the advanced valve position, the retracted valve position, an open valve position in which at least one of the one or more slots 130 is at least partially aligned with at least one of the one or more passages 128 to allow fluid communication between the fluid rotation chamber 122 of the retractable valve body 108 and the at least one of the one or more passages 128, and a closed valve position in which fluid communication of the fluid rotation chamber 122 of the retractable valve body 108 with the one or more passages 128 is closed.

[0065] In some embodiments, the advanced valve position is an open valve position. In some embodiments, the advanced valve position is a closed valve position. In some embodiments, the retracted valve position is an open valve position. In some embodiments, the retracted valve position is a closed valve position. In some embodiments, the retracted valve position is a closed valve position and the advanced valve position is a closed valve position, wherein an open valve position is between the advanced valve position and the closed valve position. In some embodiments, the retracted valve position is a closed valve position and the advanced valve position is an open valve position.

[0066] The first fuel injector 100 also includes a spring housing 102 having a spring chamber 133 that includes a spring 132 and a spring retainer 104. Fuel is introduced into the spring housing 102 and passes along an internal passage 118 between the telescoping valve body 108 and the outer valve body 110 to the side passage 115. When the telescoping valve body 108 is in the closed valve position, the fuel in the side passage 115 accumulates in the one or more passages 128. When the fuel is sufficiently pressurized to lengthen the spring 132 and transition the telescoping valve body 108 from the closed valve position to the open valve position, the fuel flows from the one or more passages 128 into the one or more slots 130. The one or more slots 130 impart rotational motion (e.g., swirl motion about the reciprocation axis 101) on the fuel as the fuel passes into the fluid swirler chamber 122 of the telescoping valve body 108. The rotational motion can be beneficial to the performance of the first fuel injector 100 because the rotational motion reduces coking on the surfaces that the fuel contacts. Once in the fluid swirler chamber 122 of the telescoping valve body 108, the fuel flows out of the secondary fuel nozzle 124 and into the combustion section 26, where the fuel is combusted to produce thrust.

[0067] In some embodiments, the first fuel injector 100 also includes a primary fuel nozzle 125. Some fuel can pass from the side passage 115 to the primary fuel nozzle 125 and into the combustion section 26 Figure 3A ) even when the telescoping valve body 108 is in the closed valve position, where the fuel is combusted to produce thrust.

[0068] Figure 3B is a schematic cross-sectional view of a first fuel injector in a closed valve position according to the present disclosure. Figure 3A is a schematic cross-sectional view of a first fuel injector in an Figure 3A advanced valve position according to the present disclosure. Figure 3A is a schematic cross-sectional detail view of a portion of the first fuel injector of Figure 3B , showing details 3B. Figure 3B , depicting the telescoping valve body 108 in the closed valve position. As Figure 2AAs shown, the slot 130 is not aligned with the passage 128 through the wall 116 of the outer valve body 110. Accumulated fuel in the side passage 115 and the passage 128 is prevented from entering the slot 130 of the telescoping valve body 108. However, some fuel can leak through the tight gap between the inner diameter of the inner passage 118( Figure 4A ) and the outer diameter of the telescoping valve body 108.

[0069] Figure 4B is a schematic cross-sectional view of a telescoping valve body in an open valve position according to the present disclosure. Figure 4A is a cross-sectional detail view of a telescoping valve body in an open valve position according to the present disclosure, showing Figure 4A detail 4B in Figure 4A . Figure 4B wherein Figure 2A shows detail 4B, depicting the telescoping valve body 108 in an open valve position. As described above with respect to Figure 2B and Figure 4B , pressurized fuel is used to transition the telescoping valve body 108 from a closed valve position to an open valve position. In the open valve position shown in Figure 2A , the orifice 126 of the slot 130 is aligned with the passage 128 through the wall 116 of the outer valve body 110. Thus, fuel follows the fuel path 134 from the side passage 115 to the passage 128, from the passage 128 into the slot 130, from the slot 130 into the fluid swirler 122, from the fluid swirler 122 to the secondary fuel nozzle 124( Figure 1 ), and out of the secondary fuel nozzle 124 into the combustion section 26( Figure 5A ), where the fuel is combusted to produce thrust.

[0070] Figure 5B is a schematic cross-sectional view of a telescoping valve body in a partially open valve position according to the present disclosure. Figure 5A is a cross-sectional detail view of a portion of a telescoping valve body in a partially open valve position according to the present disclosure, showing Figure 5A detail 5B in Figure 5A . Figure 5B wherein Figure 5B shows detail 5B, depicting the telescoping valve body 108 in a partially open valve position. The telescoping valve body 108 enters the partially open valve position when the telescoping valve body 108 is transitioning between the open valve position and the closed valve position. In the partially open valve position shown in Figure 4A , the orifice 126 of the slot 130 is partially aligned with the passage 128 through the wall 116 of the outer valve body 110. Thus, as discussed with respect to Figure 4B and Figure 1 , fuel follows the fuel path 134 to the combustion section 26( Figure 5Acombustion. The partially open valve position can provide a high pressure drop near the fuel nozzle tip 120, and the high pressure drop can provide good atomization and mixing of the fuel. Figure 5B and Figure 4A The partially open valve position provides a narrow fluid passage at lower flow rates, such that the high pressure drop also aids in ignition. At the fully open valve position of Figure 4B and Figure 2A the wider fluid passage provides higher fluid flow rates, which can minimize fuel supply pressure, fuel pump size, and associated weight. The partially open valve position also provides a smooth and continuous transition from the closed valve position to the open valve position to stabilize fluid flow through the first fuel injector 100 and to stabilize the spring 132 Figure 2A ), while also maintaining a relatively high pressure drop at the fuel nozzle tip 120 Figure 2A ) under all flow conditions.

[0071] While Figure 2B , Figure 3A , Figure 3B , Figure 4A , Figure 4B , Figure 5A , Figure 5B and Figure 2A depict specific embodiments of the first fuel injector 100, several additional variations and configurations of each of the above-mentioned features are possible and within the scope of the disclosure. The following figures depict some additional non-limiting variations and configurations, which are shown and labeled with reference numbers in the 600 series, 700 series, 800 series, 900 series, 1000 series, 1100 series, 1200 series, 1600 series, 1700 series, 1800 series, and 1900 series, but are not explicitly described herein. The elements with reference numbers in the 600 series, 700 series, 800 series, 900 series, 1000 series, 1100 series, 1200 series, 1600 series, 1700 series, 1800 series, and 1900 series, but not described below, are the same as those in the 100 series with the same reference numbers. Figure 6

[0072] Figure 7 ​is a schematic cross-sectional view of a second retractable valve body 608 embodiment. The cross-section is taken along a plane that includes the reciprocating axis 601 and a through-axis 636 that passes through the orifice 626 along the slot 630 to the fluid rotation chamber 622. The through-axis 636 defines an angle a with the reciprocating axis 601. As fuel passes from the slot 630 to the fluid rotation chamber 622, the fuel has a momentum with components parallel and perpendicular to the reciprocating axis 601. The angle a ranges from twenty degrees to ninety degrees. When the angle a is near twenty degrees, the momentum of the fuel is more aligned in the direction of the reciprocating axis 601 than when a is near ninety degrees. When a is near ninety degrees, the momentum of the fuel is more perpendicular to the reciprocating axis 601 than when a is near twenty degrees. When the momentum of the fuel has a component perpendicular to the reciprocating axis 601, the fuel produces rotational motion about the reciprocating axis 601, turbulence increases, or both. The increased rotational motion about the reciprocating axis 601 and the increased turbulence can affect, for example, the rate of coke accumulation on surfaces that the fuel contacts.

[0073] Figure 8 is a schematic cross-sectional view of a third retractable valve body 708 embodiment. The third retractable valve body 708 has a fluid rotation chamber 722 with an inner radius 738 that extends from the reciprocating axis 701. The third retractable valve body 708 has one or more slots including a first slot 730a and a nearest-neighbor slot 730b. Each of the one or more slots has an orifice 726 with an orifice width 742. Each of the one or more slots (e.g., 730a) is spaced apart from each respective nearest-neighbor slot (e.g., 730b) by a slot spacing 740. By varying the inner radius 738, the orifice width 742, and the slot spacing 740, the fuel flow into the fluid rotation chamber 722 is controlled. For example, a smaller orifice width 742 with a larger slot spacing 740 can provide a lower fuel flow rate (and / or a higher pressure differential) when the third retractable valve body 708 is in a fully open valve position compared to a larger orifice width 742 with a smaller slot spacing 740. Similarly, a smaller inner radius 738 can provide a lower fuel flow rate (and / or a higher pressure differential) when the third retractable valve body 708 is in a fully open valve position compared to a larger inner radius 738. In some embodiments, the slot spacing 740 ranges from zero to an amount equal to the inner radius 738 minus one-half of the orifice width 742.

[0074] Figure 2AA portion of the fourth retractable valve body 808 is shown having a slanted orifice 826. The slanted orifice 826 has a long axis 844 and a short axis 845. The long axis 844 defines an angle β (β) with the reciprocating axis 801. The magnitude of the angle β (β) ranges from zero degrees to ninety degrees (e.g., negative forty-five degrees to forty-five degrees, such as zero degrees to forty-five degrees). The angle β (β) affects the change in fuel flow as the fourth retractable valve body 808 changes position along the reciprocating axis 801. For example, as the fourth retractable valve body 808 advances along the reciprocating axis 801, the angle β (β) affects the degree of alignment between the slanted orifice 826 and the passage (e.g., Figure 2A of the outer valve body 110) (e.g., Figure 1 of the outer valve body 110). The angle β (β) can be used to control the relationship between the increase in fuel flow through the first fuel injector 100 Figure 1 ) and the fuel spray angle at the fuel nozzle outlet, such that the fuel spray angle can remain constant, the fuel spray angle can decrease, or the fuel spray angle can increase with increasing flow. For example, a smaller spray angle in combination with a low fuel flow rate can locally enrich and prevent lean blowout in the combustion section 26, while a wider spray angle in combination with a higher fuel flow rate can provide uniform combustion and higher efficiency. In some embodiments, the gas turbine engine 10 Figure 9 ) includes two or more fuel injectors having different β angles, such that some of the two or more fuel injectors change the spray angle under different fluid flow conditions, while others of the two or more fuel injectors have a constant spray angle.

[0075] Figure 2A A portion of the fifth retractable valve body 908 is shown having a tapered orifice 926. The tapered orifice 926 has an elliptical cross-sectional area and has a long axis 944 of length L that extends from a semicircular portion of diameter D1 to a semicircular portion of diameter D2. The shape of the tapered orifice 926 affects the change in fuel flow as the fifth retractable valve body 908 changes its position along the reciprocating axis 901. For example, as the fifth retractable valve body 908 advances along the reciprocating axis 901, the ratio D2 / D1 affects the degree of alignment between the tapered orifice 926 and the passage (e.g., Figure 2A of the outer valve body 110) (e.g., Figure 2A of the outer valve body 110). More fuel flows from the passage (e.g., Figure 2A of the outer valve body 110) when the passage (e.g., Figure 2A of the outer valve body 110) is more aligned with the D2 end of the tapered orifice 926 than when the passage (e.g., Figure 2AThe fuel flows out through channel 128 and then through tapered orifice 926. Since D2 is greater than D1, more fuel flows out. In some embodiments, D2 / D1 ranges from 0.25 to 4. Furthermore, for example, the length L affects the flow from the channel (e.g., Figure 2A The channel 128) is aligned with the larger D2 end of the tapered orifice 926 to provide more open valve positions to the channel (e.g., Figure 10A The transition of the less open valve position (channel 128) aligned with the smaller D1 end of the tapered orifice 926. The ratio L / D1 provides a measure of the transition from the more open valve position to the less open valve position. In some embodiments, L / D1 ranges from one to twenty-five. The ratio D2 / D1 can be used to control the relationship between an increase in fuel flow rate and the fuel spray angle at the fuel nozzle outlet, such that the fuel spray angle can remain constant, decrease, or increase with an increase in fuel flow rate.

[0076] Figure 2A A portion of a sixth retractable valve body 1008A with three orifices 1026a, 1026b, and 1026c is shown. Each orifice 1026a, 1026b, and 1026c has a circular cross-sectional area with diameters D1, D2, and D3, respectively. Orifice 1026a is positioned at a distance L1 from its nearest neighbor orifice 1026b. Orifice 1026b is positioned at a distance L2 from its nearest neighbor orifice 1026c. Diameters D1, D2, and D3 are designed to allow for different open valve positions and partially open valve positions. For example, when the orifice (e.g., 1026c) is connected to the channel (e.g., ... Figure 2A When the channels 128) are aligned, the larger diameter allows for more valve opening positions. Lengths L1 and L2 are designed to control the transition from one valve state to another as the sixth telescopic valve body 1008A moves along the reciprocating axis 1001A to align or partially align the orifices 1026a, 1026b, and 1026c. For example, for some combinations of L1 and D2, when the sixth telescopic valve body 1008A moves along the reciprocating axis 1001A, at least two of the orifices 1026a, 1026b, and 1026c are at least partially aligned, such that when the channels (e.g., Figure 10Bthe flow of fluid is not interrupted as the passage 128 aligns with, partially aligns with, and does not align with each of the orifices 1026a, 1026b, and 1026c, respectively. In some embodiments, each distance LI and L2 is independently in a range from negative two times a diameter Dl or D2 of an orifice of a slot and an average of the diameter Dl or D2 of the orifice of the respective nearest adjacent slot to two times the diameter Dl or D2 of an orifice (e.g., 1026a, 1026b, or 1026c) and an average of the diameter Dl or D2 of the respective nearest adjacent orifice (e.g., 1026a, 1026b, or 1026c), where a distance less than zero represents an interleaved and overlapping configuration (e.g., see Figure 10B ). Dl, D2, D3, LI, L2 can be used to control the relationship between fuel flow increase and fuel spray angle at the outlet of the fuel nozzle such that the fuel spray angle can remain constant, the fuel spray angle can decrease, or the fuel spray angle can increase with an increase in fuel flow. However, three rows of orifices are provided for reference only, and thus there can be more or less than three rows of orifices.

[0077] Figure 11A is a schematic illustration of a seventh retractable valve body 1008B having three orifices 1027a, 1027b, and 1027c in an interleaved and overlapping configuration. Each orifice 1027a, 1027b, and 1027c has a circular cross-sectional area with a diameter Dl, D2, and D3, respectively. Orifice 1027a is positioned at a distance LI from its nearest adjacent orifice 1027b in the interleaved and overlapping configuration. Orifice 1027b is positioned at a distance L2 from its nearest adjacent orifice 1027c in the interleaved and overlapping configuration. When the orifices (e.g., 1027a, 1027b, and 1027c) are positioned in the interleaved and overlapping configuration, lengths LI and L2 are defined as negative values. In some embodiments, the retractable valve body has three or more slots, each slot having orifices with circular cross-sectional areas with diameters Dl, D2, and D3, respectively, the orifices in each slot are positioned at distances LI and L2 from the orifices of the respective nearest adjacent slot, and each distance LI and L2 is in a range from negative two times a diameter Dl, D2, or D3 of an orifice of a slot and an average of the diameter Dl, D2, or D3 of the orifice of the respective nearest adjacent slot to zero, such that the three or more slots are in an interleaved and overlapping configuration. Having orifices positioned in the interleaved and overlapping configuration allows for a smooth and continuous transition from a closed valve position to an open valve position as the seventh retractable valve body 1008B is moved along the reciprocating axis 1001B.

[0078] Figure 11B and Figure 11A is a schematic cross-sectional view of a portion of a second fuel injector 1100 embodiment. Figure 11B and Figure 2A the second fuel injector 1100 embodiment shown inFigure 2B and Figure 11A The first fuel injector 100 embodiment shown in Figure 11B and Figure 11A The conical interior passage 1118 has a circular cross-sectional area perpendicular to the reciprocating axis 1101. The circular cross-sectional area has a diameter D, and D decreases along the direction of the reciprocating axis 1101 over a portion of the distance. The conical interior passage 1118 is tapered to accommodate the conical telescoping valve body 1108. The conical telescoping valve body 1108 has a cross-sectional area perpendicular to the reciprocating axis 1101. The cross-sectional area has a diameter D’, and D’ decreases along the reciprocating axis 1101. The diameter D of the conical interior passage 1118 tapers and the diameter D’ of the conical telescoping valve body 1108 tapers, allowing a variable cross-sectional area flow path for fuel to pass through the conical interior passage 1118 and around the conical telescoping valve body 1108. For example, Figure 11B The closed valve position is shown, in which the conical interior passage 1118 is blocked by the conical telescoping valve body 1108. Figure 6 The open valve position is shown, in which fuel passes through the narrow fluid passage 1147 between the conical interior passage 1118 and the conical telescoping valve body 1108. Figure 7 、 Figure 8 、 Figure 9 、 Figure 10A 、 Figure 10B and Figure 11A The embodiments of Figure 11B and Figure 12A may be used in conjunction with the second fuel injector 1100 embodiment shown in

[0079] Figure 12B 、 Figure 13A 、 Figure 13B and Figure 2A are schematic views of a piston fuel injector 1200. Similar to the first fuel injector 100 shown in Figure 2B and Figure 12A , the piston fuel injector 1200 includes an outer valve body 1210 having an interior passage 1218 and a wall 1216 at least partially surrounding the interior passage 1218. In the piston fuel injector 1200, the outer valve body 1210 is a piston housing. The wall 1216 has an inner surface 1212, an outer surface 1214, and one or more passages 1228 through the wall 1216 between the outer surface 1214 of the wall 1216 and the inner surface 1212 of the wall 1216.

[0080] The piston fuel injector 1200 has a retractable valve body 1208 positioned within an internal passage 1218 of a piston housing (i.e., an outer valve body 1210). In the piston fuel injector 1200, the retractable valve body 1208 is a piston. The piston (i.e., the retractable valve body 1208) has one or more slots 1230 in fluid communication with a fluid swirler chamber 1222. Each of the one or more slots 1230 has an orifice 1226 positioned in the internal passage 1218 of the piston housing (i.e., the outer valve body 1210), and the piston (i.e., the retractable valve body 1208) at least partially encloses the fluid swirler chamber 1222.

[0081] In the piston fuel injector 1200, when the retractable valve body 1208 is in the open valve position, the fluid swirler chamber 1222 is positioned to pass fuel from within the piston (i.e., the retractable valve body 1208) to outside of the piston housing (i.e., the outer valve body 1210).

[0082] The piston fuel injector 1200 also includes a spring housing 1202 having a piston head chamber 1233 that includes a piston head 1248, a spring 1232, and a seal 1250, such as an O-ring or gasket, to retain fuel in the piston head chamber 1233. When pressurized fuel is provided to the piston head chamber 1233, the pressure forces the spring 1232 to compress toward the seal 1250, allowing the piston (i.e., the retractable valve body 1208) to move along a reciprocating axis 1201 from the closed valve position to the open valve position. Figure 13A and Figure 1 In the piston fuel injector 1200, when the retractable valve body 1208 is in the open valve position, the fluid swirler chamber 1222 is positioned to pass fuel from within the piston (i.e., the retractable valve body 1208) to outside of the piston housing (i.e., the outer valve body 1210). Figure 12A ) into the combustion section 26, the one or more channels 1228 impart a rotational motion (e.g., a swirl motion about the reciprocating axis 1201) on the fuel, which burns in the combustion section 26 to produce thrust. The rotational motion can be advantageous to the performance of the piston fuel injector 1200 because the rotational motion reduces coking on the surfaces that the fuel contacts.

[0083] Figure 1 is a schematic cross-sectional view of a piston fuel injector according to the present disclosure, including a piston in a closed valve position, isolated from Figure 12B a turbine engine of FIG. 1. Figure 12Ais a schematic cross-sectional detail view of a piston fuel injector according to the present disclosure, showing Figure 12A detail 12B. Figure 12A is shown in a closed valve position. As shown in Figure 12B and Figure 13A the orifices 1226 of the slots 1230 are not aligned with the injection orifices 1229 in the wall 1216 of the outer valve body 1210. Thus, fuel does not pass from within the piston (i.e., the retractable valve body 1208) to outside of the piston housing (i.e., the outer valve body 1210).

[0084] Figure 13B is a schematic cross-sectional view of a piston fuel injector according to the present disclosure, including a piston in an open valve position. Figure 13A is a schematic cross-sectional detail view of a piston fuel injector according to the present disclosure, showing Figure 13A detail 13B. Figure 13A is shown in an open valve position. As shown in Figure 13B and Figure 14 the orifices 1226 of the slots 1230 are aligned with the passages 1228 in the wall 1216 of the outer valve body 1210. Thus, fuel passes from within the piston (i.e., the retractable valve body 1208) to outside of the piston housing (i.e., the outer valve body 1210) along the fuel path 1234.

[0085] Figure 15 is a cross-sectional view of the outer valve body 1210 of the piston fuel injector 1200. The one or more passages include a first passage 1228a and a second passage 1228b. The first passage 1228a has a through-axis 1236 that passes through from the outer surface 1214 of the wall 1216 to the inner surface 1212 of the wall 1216, and the through-axis 1236 forms an angle φ (φ) with a radial direction 1252 of the annular cross-section. By varying the angle φ (φ), the fuel has a component of momentum along the through-axis 1236, perpendicular to the through-axis 1236, or both. The angle φ (φ) affects the turbulence of the fuel as it flows out of the inner passage 1218, for example, which can affect the rate of coke buildup on surfaces that the fuel contacts. When φ (φ) is closer to zero degrees, the momentum of the fuel is more aligned in a direction perpendicular to the reciprocating axis 1201 than when φ (φ) is closer to sixty degrees. When the momentum of the fuel has a component perpendicular to the reciprocating axis 1201, the fuel produces rotational motion around the reciprocating axis 1201. In some embodiments, φ (φ) ranges from zero degrees to sixty degrees.

[0086] The annular cross-section has an inner radius 1238 of length R. The cross-sectional area of the first passage 1228a has a width measured from the through-axis to the side axis 1237 of length dS The shortest distance from the through-axis 1236 to the center point of the annular cross-section is the orifice offset 1254. The orifice offset 1254 can range from zero to R - d S / 2. By varying the orifice offset 1254, the inner radius 1238 of length R, and d S , the flow rate of fuel transferred between the injection orifice 1229 and the fluid rotation chamber 1222 is controlled. For example, when the orifice offset 1254 is R - d S / 2, the first channel 1228a will impart more rotational motion about the reciprocating axis 1201 to the fuel as it is transferred between the first channel 1228a and the fluid rotation chamber 1222 than when the orifice offset 1254 is zero. The rotational motion about the reciprocating axis 1201 increases as φ (phi) increases toward sixty degrees, for example, which can affect the rate of coke accumulation on the surfaces the fuel contacts.

[0087] Figure 15 is a schematic cross-sectional side view of a portion of a first piston housing according to the present disclosure. Figure 16 A side view of a portion of the piston housing (i.e., the outer valve body 1210) is shown, showing the injection orifice 1229. The injection orifice 1229 has a circular cross-sectional area with a diameter D” that is measured at the outer surface 1214 of the wall 1216. The diameter D” of the injection orifice 1229 is adjusted to vary the fuel flow rate of fuel that flows out of the fluid rotation chamber 1222 through the injection orifice 1229. For example, a larger diameter D” allows more fuel to be transferred through the injection orifice 1229 when the piston (i.e., the retractable valve body 1208) is in the open valve position.

[0088] Figure 16 is a schematic cross-sectional side view of a portion of a second piston housing having an oval injection orifice according to the present disclosure. Figure 17 A side view of a portion of the second piston housing (i.e., the second outer valve body 1610) having an oval injection orifice 1629 embodiment is shown. The oval injection orifice 1629 passes through the wall 1616 of the second piston housing (i.e., the second outer valve body 1610), and the oval injection orifice 1629 has an elliptical cross-sectional area with a major diameter D 1’ and a minor diameter D 2’ . The major diameter D 1’ and the minor diameter D 2’ are measured at the outer surface 1614 of the wall 1616. Adjusting the major diameter D 1’ and the minor diameter D 2’ varies the flow profile of fuel that exits the oval injection orifice 1629. For example, a larger D2 will lengthen the flow profile during a transition from the closed valve position to the open valve position, while a larger D1’ This will increase the maximum flow rate at the open valve position. (D) 2’ / D 1’ The ratio can be used to control the relationship between the increase in fuel flow rate and the fuel spray angle at the fuel nozzle outlet, so that the fuel spray angle can remain constant, decrease, or increase with the increase in fuel flow rate.

[0089] Figure 17 This is a schematic cross-sectional side view of a portion of a third piston housing having a slotted injection orifice according to the present disclosure. Figure 18 A side view of a portion of the third piston housing (i.e., the third outer valve body 1710) is shown, which has a slotted injection orifice 1729 in its outer surface 1714. The slotted injection orifice 1729 is used to achieve a short transition from the closed valve position to the open valve position, in which the fuel flow rate transmitted through the slotted injection orifice 1729 rapidly increases from zero in the closed valve position to the maximum flow rate in the open valve position. The slotted injection orifice 1729 can be used to deliver rapid pulses of fuel to the combustion zone 26.

[0090] Figure 18 This is a schematic cross-sectional side view of a fourth piston housing having angled injection orifices according to the present disclosure. Figure 19 A side view of a portion of a fourth piston housing (i.e., the fourth outer valve body 1810) is shown, which has angled injection orifices 1829 in its outer surface 1814. The angled injection orifices 1829 have a major axis 1844 that defines an angle β' (β') with the reciprocating axis 1801. Different angle β' (β') values ​​can be used to generate different flow profiles for fuel delivered through the angled injection orifices 1829. For example, when the angle β' (β') is close to zero degrees, the open valve position of the flow profile is longer than when the angle β' (β') is close to ninety degrees because the major axis of the angled injection orifices 1829 is more aligned with the reciprocating axis 1801 when the angle β' (β') is close to zero degrees. Different flow profiles can be used to improve fuel combustion in combustion zone 26.

[0091] Figure 20is a cross-sectional view of a portion of a fifth piston housing (i.e., a fifth outer valve body 1911) having a tapered passage 1928 and a lumen 1918. The tapered passage 1928 passes through the wall 1916 along the through-axis 1956. The tapered passage 1928 has a longer diameter 1958 and a shorter diameter 1960. The longer diameter 1958 is positioned closer to the outer surface 1914 of the wall 1916, while the shorter diameter 1960 is positioned closer to the inner surface 1912 of the wall 1916. The tapered passage 1928 is used to regulate the flow of fuel passing through the tapered passage 1928, for example, by atomizing the fuel as it passes through the tapered passage 1928.

[0092] Figure 2A A method 2000 of injecting fuel into a combustion section 26 is shown. The method 2000 can be used with any of the disclosed fuel injectors, including, for example, the first fuel injector 100 Figures 12A-13B ) and the piston fuel injector 1200 Figure 1 ). Thus, in describing the method, exemplary reference numerals are provided for the first fuel injector 100 and the piston fuel injector 1200. For example, the method 2000 includes (2003) applying a fluid pressure to a spring (e.g., 132 or 1232) of a fuel injector (e.g., 100 or 1200) such that the fluid pressure compresses the spring (e.g., 132 or 1232) causing a telescoping valve body (e.g., 108 or 1208) to move along a reciprocating axis (e.g., 101 or 1201) from at least one closed valve position to at least one open valve position, (2005) passing fuel between a fluid swivel chamber (e.g., 122 or 1222) of the telescoping valve body (e.g., 108 or 1208) and an outer valve body (e.g., 110 or 1210), and (2007) injecting the fuel into a combustion section 26 ​ ). In some embodiments, the fluid pressure compresses the spring (e.g., 132 or 1232) causing the telescoping valve body (e.g., 108 or 1208) to move along the reciprocating axis (e.g., 101 or 1201) from the closed valve position to a partially open valve position and then to the open valve position. In some embodiments, passing the fuel between the fluid swivel chamber (e.g., 122 or 1222) of the telescoping valve body (e.g., 108 or 1208) and the outer valve body (e.g., 110 or 1210) imparts rotational motion to the fuel. In some embodiments, the telescoping valve body (e.g., 1208) is a piston, the outer valve body is a piston housing (e.g., 1210), and the fuel passes from inside the piston to outside the piston housing. In some embodiments, the fuel passes around the telescoping valve body (e.g., 108) before passing into the fluid swivel chamber (e.g., 122).

[0093] Accordingly, as fuel is transferred between the passages (e.g., 128 and 1228) and the fluid rotation chamber (e.g., 122 and 1222), the fuel injector (e.g., 100 and 1200) adjusts the pressure differential and imparts rotational momentum to the fuel. The high pressure differential can increase atomization of the fuel and air compared to the turbine engine 10 without the benefit of the present disclosure. The rotational momentum can improve the fluid dynamics of the fuel flow and, for example, reduce coke buildup on surfaces that the fuel contacts. The increased momentum of the fuel jets from the fuel injector (e.g., 100 and 1200) can improve atomization and mixing of the fuel and air, making the fuel and air mixture easier to ignite and burn compared to the turbine engine 10 without the benefit of the present disclosure. Accordingly, the fuel injector (e.g., 100 and 1200) provides improved ignition capability by increasing atomization of the fuel and air, particularly for cold fuel (e.g., at higher altitudes) or high viscosity fuel. The injector (e.g., 100 and 1200) results in improved sub-idle and low power efficiency of the combustion section 26 and produces less smoke at high power operation due to the increased atomization compared to the turbine engine 10 without the benefit of the present disclosure.

[0094] Further aspects of the present disclosure are provided by the subject matter of the following clauses.

[0095] A gas turbine engine includes a fuel injector having a retractable valve body. The fuel injector has an outer valve body having an internal passage and a wall at least partially surrounding the internal passage. The wall has an inner surface, an outer surface, and one or more passages through the wall between the outer surface of the wall and the inner surface of the wall. The retractable valve body is positioned within the internal passage of the outer valve body. The retractable valve body has one or more slots in fluid communication with a fluid rotation chamber, each of the one or more slots having an orifice positioned in the internal passage of the outer valve body, wherein the retractable valve body at least partially surrounds a fluid rotation chamber. The retractable valve body is positioned within the internal passage to move along a reciprocating axis at one or more valve positions, the one or more valve positions including an advanced valve position, a retracted valve position, an open valve position, and a closed valve position, the open valve position at least partially aligning at least one of the one or more slots with at least one of the one or more passages to allow fluid communication between the fluid rotation chamber of the retractable valve body and the at least one of the one or more passages, wherein fluid communication of the fluid rotation chamber of the retractable valve body with the one or more passages is closed.

[0096] The gas turbine engine of any of the preceding clauses, such that the one or more slots, the one or more passages, or the one or more slots and the one or more passages impart rotational motion about the reciprocating axis to fluid transferred between the one or more passages and the fluid rotary chamber.

[0097] The gas turbine engine of any of the preceding clauses, such that each of the one or more slots has a through-axis from the orifice to the fluid rotary chamber, and the through-axis forms an angle a with the reciprocating axis, and a ranges from twenty degrees to ninety degrees.

[0098] The gas turbine engine of any of the preceding clauses, such that each of the one or more slots, each of the one or more passages, or each of the one or more slots and each of the one or more passages has a cross-sectional area measured in a plane parallel to the reciprocating axis, wherein the cross-sectional area has a major axis and a minor axis, and the major axis defines an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to ninety degrees.

[0099] The gas turbine engine of any of the preceding clauses, such that the orifice of each of the one or more slots has a major axis and a minor axis, and the major axis forms an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to forty-five degrees.

[0100] The gas turbine engine of any of the preceding clauses, such that the orifice of each of the one or more slots has a circular, elliptical cross-sectional area, or has a major axis of length L and a minor axis, wherein the major axis extends from a semicircular portion of diameter D1 to a semicircular portion of diameter D2, and D2 / D1 ranges from 0.25 to 4, and L / D1 ranges from 1 to 25.

[0101] The gas turbine engine of any of the preceding clauses, such that the retractable valve body has three or more slots, the orifice of each slot has a circular cross-sectional area of diameter D, the orifice of each slot is positioned a distance L from the orifice of a respective nearest-neighbor slot, and each distance L ranges from negative twice to twice an average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest-neighbor slot, wherein a distance less than zero indicates a staggered and overlapping configuration.

[0102] The gas turbine engine of any of the preceding clauses, such that the telescoping valve body has three or more slots, the orifice of each slot has a circular cross-sectional area with a diameter D, the orifice of each slot is positioned a distance L from the orifice of a respective nearest-neighbor slot, and each distance L ranges from negative twice the average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest-neighbor slot to zero, such that the three or more slots are in a staggered and overlapping configuration.

[0103] The gas turbine engine of any of the preceding clauses, such that the internal passage has a circular cross-sectional area perpendicular to the reciprocation axis, the circular cross-sectional area having a diameter D, and D decreases over a portion of the distance along the direction of the reciprocation axis.

[0104] The gas turbine engine of any of the preceding clauses, such that each of the one or more passages has a cross-sectional area measured at the outer surface of the wall, and the cross-sectional area is circular or elliptical.

[0105] The gas turbine engine of any of the preceding clauses, such that each of the one or more passages has a cross-section taken along the reciprocation axis, the cross-section having a longer diameter and a shorter diameter, the longer diameter being positioned closer to the outer surface of the wall, and the shorter diameter being positioned closer to the inner surface of the wall.

[0106] The gas turbine engine of any of the preceding clauses, such that the telescoping valve body is a piston, the outer valve body is a piston housing, and the fluid rotation chamber is positioned to pass fluid from inside the piston to outside the piston housing.

[0107] The gas turbine engine of any of the preceding clauses, such that the telescoping valve body is in contact with a spring, and the spring exerts a force on the telescoping valve body toward a retracted valve position, and closes the retracted valve position.

[0108] The gas turbine engine of any of the preceding clauses, such that the fuel injector includes a primary fuel nozzle and a secondary fuel nozzle, and the fluid rotation chamber of the telescoping valve body is in fluid communication with the secondary fuel nozzle.

[0109] The gas turbine engine of any of the preceding clauses, such that the valve positions include at least one fully open valve position that fully aligns at least one of the one or more slots with at least one of the one or more passages to allow fluid communication between the fluid rotation chamber of the telescoping valve body and the at least one of the one or more passages.

[0110] The gas turbine engine of any of the preceding clauses, such that the outer valve body has an annular cross-section in a plane perpendicular to the reciprocating axis.

[0111] The gas turbine engine of any of the preceding clauses, such that each of the one or more passages has a through-axis from the outer surface of the wall to the inner surface of the wall, the through-axis forming an angle φ with a radial direction of the annular cross-section, and φ ranges from zero degrees to sixty degrees.

[0112] The gas turbine engine of any of the preceding clauses, such that each of the one or more passages has an inner radius of length R, each of the one or more passages has a cross-sectional area in a plane perpendicular to the through-axis, the cross-sectional area having a major axis of length d S , and a shortest distance from the through-axis to a center point of the annular cross-section ranges from zero to R - d S / 2.

[0113] The gas turbine engine of any of the preceding clauses, further comprising a fuel nozzle tip in fluid communication with the fluid rotation chamber of the retractable valve body, a fuel supply in fluid communication with the fuel injector, and a combustion section. The fuel injector is positioned to pass fluid through the fuel nozzle tip into the combustion section.

[0114] An aircraft comprising the gas turbine engine of any of the preceding clauses.

[0115] A method of operating the gas turbine engine of any of the preceding clauses, the method comprising moving the retractable valve body along the reciprocating axis from the closed valve position to the open valve position, and passing fuel between the fluid rotation chamber of the retractable valve body and at least one of the one or more passages.

[0116] The method of any of the preceding clauses, such that passing the fuel between the fluid rotation chamber of the retractable valve body and the at least one of the one or more passages comprises passing the fuel from the fluid rotation chamber of the retractable valve body to the at least one of the one or more passages.

[0117] The method of any of the preceding clauses, such that passing the fuel between the fluid rotation chamber of the retractable valve body and the at least one of the one or more passages comprises passing the fuel from the at least one of the one or more passages to the fluid rotation chamber of the retractable valve body.

[0118] The method of any of the preceding clauses, such that the one or more slots, the one or more channels, or the one or more slots and the one or more channels impart rotational motion about the reciprocating axis to fluid transferred between the one or more channels and the fluid rotation chamber.

[0119] The method of any of the preceding clauses, such that each of the one or more slots has a through-axis from the orifice to the fluid rotation chamber, the through-axis forms an angle a with the reciprocating axis, and a ranges from twenty degrees to ninety degrees, and the one or more slots impart rotational motion about the reciprocating axis to fluid transferred between the one or more channels and the fluid rotation chamber.

[0120] The method of any of the preceding clauses, such that each of the one or more slots, each of the one or more channels, or each of the one or more slots and each of the one or more channels has a cross-sectional area measured in a plane parallel to the reciprocating axis, wherein the cross-sectional area has a major axis and a minor axis, and the major axis defines an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to ninety degrees, such that the one or more slots, the one or more channels, or the one or more slots and the one or more channels impart rotational motion about the reciprocating axis to fluid transferred between the one or more channels and the fluid rotation chamber.

[0121] The method of any of the preceding clauses, such that the orifice of each of the one or more slots has a major axis and a minor axis, and the major axis forms an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to forty-five degrees, such that the one or more slots impart rotational motion about the reciprocating axis to fluid transferred between the one or more channels and the fluid rotation chamber.

[0122] The method of any of the preceding clauses, such that the orifice of each of the one or more slots has a circular, elliptical cross-sectional area, or has a major axis of length L and a minor axis, wherein the major axis extends from a semicircular portion of diameter D1 to a semicircular portion of diameter D2, and D2 / D1 ranges from 0.25 to 4, and L / D1 ranges from 1 to 25, such that the one or more slots impart rotational motion about the reciprocating axis to fluid transferred between the one or more channels and the fluid rotation chamber.

[0123] The method of any of the preceding clauses, such that the telescoping valve body has three or more slots, the orifice of each slot has a circular cross-sectional area with a diameter D, the orifice of each slot is positioned a distance L from the orifice of a respective nearest-neighbor slot, and each distance L ranges from negative twice to twice an average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest-neighbor slot, and such that moving the telescoping valve body along the reciprocation axis from the closed valve position to the open valve position sequentially aligns each slot with at least one of the one or more passages.

[0124] The method of any of the preceding clauses, such that the telescoping valve body has three or more slots, the orifice of each slot has a circular cross-sectional area with a diameter D, the orifice of each slot is positioned a distance L from the orifice of a respective nearest-neighbor slot, and each distance L ranges from negative twice to zero an average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest-neighbor slot, such that the three or more slots are in a staggered and overlapping configuration, and such that moving the telescoping valve body along the reciprocation axis from the closed valve position to the open valve position sequentially aligns each slot with at least one of the one or more passages.

[0125] The method of any of the preceding clauses, such that the internal passage has a circular cross-sectional area perpendicular to the reciprocation axis, the circular cross-sectional area having a diameter D, and D decreases along a direction of the reciprocation axis over a portion of a distance, such that moving the telescoping valve body along the reciprocation axis from the closed valve position to the open valve position widens a fluid passage between the outer valve body and the telescoping valve body.

[0126] The method of any of the preceding clauses, such that each of the one or more passages has a cross-sectional area measured at the outer surface of the wall, the cross-sectional area being circular or elliptical, and such that the one or more passages impart rotational motion about the reciprocation axis to fluid communicated between the one or more passages and the fluid rotation chamber.

[0127] The method of any of the preceding clauses, such that each of the one or more passages has a cross-section taken along the reciprocation axis, the cross-section having a longer diameter and a shorter diameter, the longer diameter being positioned closer to the outer surface of the wall, and the shorter diameter being positioned closer to the inner surface of the wall, such that communicating the fuel between the fluid rotation chamber of the telescoping valve body and at least one of the one or more passages includes atomizing the fuel.

[0128] The method of any of the preceding clauses, such that the retractable valve body is a piston, the outer valve body is a piston housing, and the fluid swivel chamber is positioned to pass fluid from within the piston to outside of the piston housing, and passing the fuel between the fluid swivel chamber of the retractable valve body and at least one of the one or more passages comprises passing the fuel from within the piston to outside of the piston housing.

[0129] The method of any of the preceding clauses, such that the retractable valve body is in contact with a spring, and the spring exerts a force on the retractable valve body toward a retracted valve position, closes the retracted valve position, and exerts fluid pressure on the spring of the gas turbine engine of any of the preceding clauses, and such that passing the fuel between the fluid swivel chamber of the retractable valve body and at least one of the one or more passages comprises exerting fluid pressure on the spring such that the fluid pressure compresses the spring, moves the retractable valve body along the reciprocating axis from the closed valve position to the open valve position.

[0130] The method of any of the preceding clauses, such that the fuel injector comprises a primary fuel nozzle and a secondary fuel nozzle, and the fluid swivel chamber of the retractable valve body is in fluid communication with the primary fuel nozzle, and such that the fuel passed between the fluid swivel chamber of the retractable valve body and at least one of the one or more passages then exits from the primary fuel nozzle.

[0131] The method of any of the preceding clauses, such that each of the one or more passages has a through-axis that passes through from the outer surface of the wall to the inner surface of the wall, wherein the through-axis forms an angle φ with a radial direction of the annular cross-section, and φ ranges from zero degrees to sixty degrees, and such that the one or more passages impart rotational motion about the reciprocating axis to fluid passed between the one or more passages and the fluid swivel chamber.

[0132] The method of any of the preceding clauses, such that each of the one or more passages has an inner radius of length R, each of the one or more passages has a cross-sectional area in a plane perpendicular to the through-axis, the cross-sectional area has a major axis of length dS, and a shortest distance from the through-axis to a center point of the annular cross-section ranges from zero to R - dS / 2, and such that the one or more passages impart rotational motion about the reciprocating axis to fluid passed between the one or more passages and the fluid swivel chamber. S

[0133] ​The method of any of the preceding clauses, such that the fuel injector includes a fuel nozzle tip in fluid communication with the fluid rotary chamber of the retractable valve body, a fuel supply in fluid communication with the fuel injector, and a combustion section, and the fuel transfer between the fluid rotary chamber of the retractable valve body and at least one of the one or more passages passes through the fuel nozzle tip into the combustion section.

[0134] A method of injecting fuel into a combustion section, the method including applying a fluid pressure to a spring of a gas turbine engine according to any of the preceding clauses, wherein the fluid pressure compresses the spring, moves the retractable valve body along the reciprocating axis from the closed valve position to the open valve position, transfers fuel between the fluid rotary chamber of the retractable valve body and the outer valve body, and injects the fuel into the combustion section.

[0135] The method of any of the preceding clauses, such that the fluid pressure compresses the spring, moves the retractable valve body along the reciprocating axis from the closed valve position to a partially open valve position, and then to the open valve position.

[0136] The method of any of the preceding clauses, such that the transfer of fuel between the fluid rotary chamber of the retractable valve body and the outer valve body imparts a rotary motion to the fuel.

[0137] The method of any of the preceding clauses, such that the retractable valve body is a piston, the outer valve body is a piston housing, and fuel is transferred from inside the piston to outside the piston housing.

[0138] The method of any of the preceding clauses, such that fuel is transferred around the retractable valve body before being transferred into the fluid rotary chamber.

[0139] While the foregoing description has been directed to the preferred embodiments of the present disclosure, other variations and modifications will be apparent to those skilled in the art from this disclosure, and can be made without departing from the scope of the present disclosure. Furthermore, features described in conjunction with one embodiment can also be used in conjunction with other embodiments.

Claims

1. A gas turbine engine characterized by, Comprising: a fuel injector, the fuel injector comprising: an outer valve body having: an inner passage; and a wall at least partially surrounding the inner passage, the wall having an inner surface, an outer surface, and one or more passages through the wall between the outer surface of the wall and the inner surface of the wall; and a retractable valve body positioned within the inner passage of the outer valve body, the retractable valve body having one or more slots in fluid communication with a fluid swivel chamber, each of the one or more slots having an orifice positioned in the inner passage of the outer valve body, wherein the retractable valve body at least partially surrounds the fluid swivel chamber, wherein the retractable valve body is positioned within the inner passage to move along a reciprocating axis at one or more valve positions, the one or more valve positions comprising an advanced valve position, a retracted valve position, an open valve position, and a closed valve position, the open valve position at least partially aligning at least one of the one or more slots with at least one of the one or more passages to allow fluid communication between the fluid swivel chamber of the retractable valve body and the at least one of the one or more passages, wherein fluid communication of the fluid swivel chamber of the retractable valve body with the one or more passages is closed.

2. The gas turbine engine of claim 1, wherein, wherein, the one or more slots, the one or more passages, or the one or more slots and the one or more passages impart rotational motion about the reciprocating axis to fluid communicated between the one or more passages and the fluid swivel chamber.

3. The gas turbine engine of claim 1, wherein, wherein, each of the one or more slots has a through-axis from the orifice to the fluid swivel chamber, and the through-axis forms an angle a with the reciprocating axis, and a ranges from twenty degrees to ninety degrees.

4. The gas turbine engine of claim 1, wherein, wherein, each of the one or more slots, each of the one or more passages, or each of the one or more slots and each of the one or more passages has a cross-sectional area measured in a plane parallel to the reciprocating axis, wherein the cross-sectional area has a major axis and a minor axis, and the major axis defines an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to ninety degrees.

5. The gas turbine engine of claim 1, wherein, wherein, the orifice of each of the one or more slots has a major axis and a minor axis, and the major axis forms an angle b with the reciprocating axis, and b ranges in magnitude from zero degrees to forty-five degrees.

6. The gas turbine engine of claim 1, wherein, wherein, the orifice of each of the one or more slots has a circular, elliptical cross-sectional area, or has a major axis of length L and a minor axis, wherein the major axis extends from a semicircular portion of diameter D1 to a semicircular portion of diameter D2, and D2 / D1 ranges from 0.25 to 4, and L / D1 ranges from 1 to 25.

7. The gas turbine engine of claim 1, wherein, wherein, The telescoping valve body has three or more slots, the orifice of each slot has a circular cross-sectional area with a diameter D, the orifice of each slot is positioned a distance L from the orifice of the respective nearest adjacent slot, and each distance L ranges from negative two times to two times the average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest adjacent slot, wherein a distance less than zero indicates an interleaved and overlapping configuration.

8. The gas turbine engine of claim 1, wherein, wherein, The telescoping valve body has three or more slots, the orifice of each slot has a circular cross-sectional area with a diameter D, the orifice of each slot is positioned a distance L from the orifice of the respective nearest adjacent slot, and each distance L ranges from negative two times to zero times the average of the diameter D of the orifice of the slot and the diameter D of the orifice of the respective nearest adjacent slot, such that the three or more slots are in an interleaved and overlapping configuration.

9. The gas turbine engine of claim 1, wherein, wherein, The internal passage has a circular cross-sectional area perpendicular to the reciprocating axis, the circular cross-sectional area has a diameter D, and D decreases over a portion of the distance along the direction of the reciprocating axis.

10. The gas turbine engine of claim 1, wherein, wherein, Each of the one or more passages has a cross-sectional area measured at the outer surface of the wall, and the cross-sectional area is circular or elliptical.

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