Fuel nozzle valve seal for high temperatures

Abstract

A fuel injector valve includes a fuel injector valve sleeve having a passage with an opening for allowing fuel to flow therethrough and a seat. A plunger has a post and a base substantially perpendicular to the post, the plunger configured to move relative to the fuel injector valve sleeve to seal or open the opening of the fuel injector valve. The fuel injector valve further includes a metallic resilient member configured to contact the base of the plunger and the seat of the fuel injector valve sleeve to seal the opening of the fuel injector valve when the plunger is moved to seal the fuel injector valve.

Description

Technical Field

[0001] This disclosure generally relates to seals, and more specifically, to fuel nozzle valve seals for high-temperature applications in gas turbine engines. Background Technology

[0002] A gas turbine engine generally comprises a fan and a core, arranged in flow communication with each other, with the core positioned downstream of the fan in the flow direction through the gas turbine engine. The core of a gas turbine engine typically includes, in a sequential flow order, a compressor section, a combustion section, a turbine section, and an exhaust section. For multi-shaft gas turbine engines, the compressor section may include a high-pressure compressor (HPC) positioned downstream of a low-pressure compressor (LPC), and the turbine section may similarly include a low-pressure turbine (LPT) positioned downstream of a high-pressure turbine (HPT). In this configuration, the HPC is connected to the HPT via a high-pressure shaft (HPS), and the LPC is connected to the LPT via a low-pressure shaft (LPS). In operation, at least a portion of the air from the fan is supplied to the inlet of the core. This portion of air is progressively compressed by the LPC, then by the HPC, until the compressed air reaches the combustion section. Fuel mixes with the compressed air and burns within the combustion section to produce combustion gases. The combustion gases are guided from the combustion section through the HPT and then through the LPT. The combustion gas flow in the turbine section drives the HPT and LPT, each of which in turn drives a corresponding one of the HPC and LPC via the HPS and LPS. The combustion gas is then directed through the exhaust section into, for example, the atmosphere. The LPT drives the LPS, and the LPS drives the LPC. In addition to driving the LPC, the LPS can also drive the fan via the power gearbox, reducing the fan's rotational speed per unit time to a lower speed than the LPS, thereby improving efficiency.

[0003] Fuel, mixed with compressed air and burned in the combustion zone, is delivered through a fuel nozzle. The fuel nozzle includes a check valve with a relatively small diameter plunger (e.g., in the 1 / 4-inch to 1 / 2-inch range), which is lightly loaded when closed, with a load pressure of 10 psi to 40 psi. Typically, the seal when the valve is closed is achieved using an elastomer. The sealing surface of the plunger is covered with a compliant elastomer that is compressed into the mating surface, providing a near-airtight seal. However, current fuel systems can operate at temperatures that preclude the use of elastomers for sealing.

[0004] The foregoing and other features and advantages will become apparent from the following more specific description of various exemplary embodiments, as shown in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar and / or structurally similar elements.

[0005] Figure 1This is a schematic cross-sectional view of a turbine engine according to an embodiment of the present disclosure.

[0006] Figure 2 This is a schematic cross-sectional view of a fuel nozzle valve according to an embodiment of the present disclosure.

[0007] Figure 3 This is a schematic cross-sectional view of a fuel nozzle valve according to another embodiment of the present disclosure.

[0008] Figure 4 This is a schematic cross-sectional view of a fuel nozzle valve according to yet another embodiment of the present disclosure. Detailed Implementation

[0009] Additional features, advantages, and embodiments of this disclosure will become apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, it should be understood that the following detailed description is exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0010] 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 the scope of the claims.

[0011] As used herein and throughout the specification and claims, approximate language can be used to modify any permissible variation without altering the essential function associated with it. Therefore, values ​​modified by one or more terms such as “about,” “approximately,” and “substantially” 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. Scope limitations may be combined and / or interchanged herein and throughout the specification and claims. Unless otherwise specified by context or language, such scopes are defined and include all subscopes contained herein.

[0012] As used herein, the term "axial" refers to a direction and orientation that extends substantially parallel to the centerline of the turbine engine or combustor. Furthermore, the term "radial" refers to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine or fuel-air mixer assembly. Additionally, as used herein, the term "circumferentially" refers to a direction and orientation that extends in an arc around the centerline of the turbine engine or fuel-air mixer assembly.

[0013] As fuel systems are developed to operate at fuel temperatures exceeding the capabilities of elastomers, embodiments of this disclosure seek to provide seals for all-metal fuel systems and rely on geometry to provide the required compliance for suitable sealing performance. Various constructions or seal geometries are provided herein, including: (1) a thin gasket clamped at the outer diameter, with a plunger pushed downwards near the inner diameter; (2) a conical gasket compressed by the plunger when the valve is closed; and (3) a generally conical gasket with a circular inner and outer edge, angled to the sealing surface for abutment against the sealing surface. In all cases, these geometries can be constructed to create a “crisp seal line” with sufficient contact pressure. A crisp seal line, as used herein, means that the sealing interface between the seal and the sealing surface does not seal against surface defects (leading to leak points), and / or the contact pressure applied at the interface between the seal and the sealing surface is substantially uniform. Another sealing construction is to provide a curved surface to maximize the thickness of the contact line. This allows for reduced contact pressure and thus further reduces the seal’s vulnerability to surface defects. When the valve is open, the seal can disengage; when the valve is closed, the seal can engage the plunger, thereby preventing fuel flow.

[0014] Figure 1 This is a schematic cross-sectional view of a turbine engine 10 according to an embodiment of the present disclosure. The turbine engine 10 may include, for example, a turbojet engine, a turboprop engine, a turbofan engine, or a turboshaft engine. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to a reference longitudinal centerline 12) and a radial direction R perpendicular to the axial direction A. Typically, the turbine engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream of the fan section 14.

[0015] The core turbine engine 16 shown typically includes a housing 18, which is substantially tubular and defines an annular inlet 20. Figure 1 As schematically shown, the housing 18 surrounds the compressor section, combustion section 26, turbine section, and injection nozzle section 32 in a series flow relationship. The compressor section includes a turbocharger or low-pressure (LP) compressor 22, with a high-pressure (HP) compressor 24 immediately downstream thereafter. The turbine section includes a high-pressure (HP) turbine 28, with a low-pressure (LP) turbine 30 immediately downstream thereafter. A high-pressure (HP) shaft or spool 34 drives the HP turbine 28 to the HP compressor 24 so that the HP turbine 28 and HP compressor 24 rotate in unison. A low-pressure (LP) shaft or spool 36 drives the LP turbine 30 to the LP compressor 22 so that the LP turbine 30 and LP compressor 22 rotate in unison. The compressor section, combustion section 26, turbine section, and injection nozzle section 32 together define the core airflow path.

[0016] for Figure 1 In the illustrated embodiment, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 generally extend outward from disk 42 along a radial direction R. Each fan blade 40 is operably coupled to an actuating member 44 by means of the fan blades 40, and the actuating member 44 is configured to collectively change the pitch of the fan blades 40. The fan blades 40, disk 42, and actuating member 44 together are rotatable about a longitudinal centerline 12 via a fan shaft 45, which is powered by an LP shaft 36 through a power gearbox 46. The power gearbox 46 includes a plurality of gears 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, to a more efficient fan rotational speed.

[0017] Still referencing Figure 1 In an exemplary embodiment, the disk 42 is covered by a rotatable front hub 48 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 40. Furthermore, the fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of the fan 38 and / or the core turbine engine 16. The nacelle 50 is supported relative to the core turbine engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Additionally, a downstream section 54 of the nacelle 50 extends over the outer portion of the core turbine engine 16 to define a bypass airflow passage 56 therebetween.

[0018] During operation of the turbine engine 10, a volume of air 58 enters the turbine engine 10 through the nacelle 50 and / or the inlet 60 of the fan section 14. As the volume of air 58 passes through the fan blades 40, a first portion of the air 58, as indicated by arrow 62, is directed or diverted to the bypass airflow passage 56, and a second portion of the air 58, as indicated by arrow 64, is directed or diverted to the upstream section of the core airflow path, or more specifically, to the annular inlet 20 of the LP compressor 22. The ratio between the first portion 62 and the second portion 64 of the air is commonly referred to as the bypass ratio. Then, as the second portion 64 of the air passes through the HP compressor 24 and enters the combustion section 26, the pressure of the air 64 increases, where the high-pressure air mixes with fuel and burns to provide combustion gases 66.

[0019] Combustion gas 66 is guided into and expanded by the HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a sequential stage of HP turbine stator blades 68 connected to the housing 18 and HP turbine rotor blades 70 connected to the HP shaft or spool 34, causing the HP shaft or spool 34 to rotate, thereby supporting the operation of the HP compressor 24. Combustion gas 66 is then guided into and expanded by the LP turbine 30. Here, a second portion of the thermal and kinetic energy is extracted from the combustion gas 66 via a sequential stage of LP turbine stator blades 72 connected to the housing 18 and LP turbine rotor blades 74 connected to the LP shaft 36, thereby causing the LP shaft or spool 36 to rotate. This, in turn, supports the operation of the LP compressor 22 and the rotation of the fan 38 via the power gearbox 46.

[0020] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it passes through the bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for directing combustion gas 66 through the core turbine engine 16.

[0021] Figure 1 The turbine engine 101 depicted is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 38 may be configured in any other suitable manner (e.g., as a fixed-pitch fan) and may be further supported using any other suitable fan frame configuration. Furthermore, it should be understood that in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable gas turbine engine.

[0022] Figure 2This is a schematic cross-sectional view of the flow metering portion of a fuel nozzle valve 200 according to an embodiment of the present disclosure. The fuel nozzle valve 200 includes a fuel nozzle valve bushing 202 and a plunger 204. In one embodiment, the plunger 204 has a T-shape. The plunger 204 has a post 204A and a base 204B connected to the post 204A. The post 204A and the base 204B of the plunger 204 are substantially perpendicular to each other and form a T-shape. The fuel nozzle valve bushing 202 has a channel 202C to allow the post 204A of the plunger 204 to move through it. The plunger 204 is configured to move relative to the fuel nozzle valve bushing 202 to seal or open the opening 202A in the fuel nozzle valve bushing 202 to allow fuel 206 to flow between the plunger 204 and the fuel nozzle valve bushing 202. In the open position, fuel 206 flows through the passage 202C of the fuel nozzle valve bushing 202 and then through the opening 202A of the fuel nozzle valve bushing 202. The fuel nozzle valve bushing 202 also has a seat 202B. The seat 202B of the fuel nozzle valve bushing 202 is configured to receive the base 204B of the plunger 204 to seal the opening 202A of the fuel nozzle valve bushing 202.

[0023] The fuel nozzle valve 200 also includes a metallic resilient member 208 (e.g., a bent washer or a Bass spring washer) configured to contact the base 204B of the plunger 204 and the seat 202B of the fuel nozzle valve bushing 202. In one embodiment, the metallic resilient member 208 is attached to or clamped to the wall 202D of the fuel nozzle valve bushing 202D. The metallic resilient member 208 may be made of stainless steel or other metals capable of withstanding relatively high temperatures without losing its elasticity or resilience. The metallic resilient member 208 may be slightly bent to provide spring characteristics, such that the resilient member 208 deforms under applied force or pressure, but can return to or toward its initial configuration when the applied pressure or force is removed.

[0024] In operation, the fuel nozzle valve 200 can be closed by moving the plunger 204 in the closing direction until the base 204B of the plunger 204 abuts against and pushes the metal elastic member 208 with a predetermined force. The metal elastic member 208 bends slightly under the applied force until it contacts and abuts against the seat 202B of the fuel nozzle valve bushing 202. As the plunger 204 closes, the base 204B contacts the metal elastic member 208, causing it to deflect due to its compliant characteristics. The contact surface 208S between the metal elastic member 208 and the base 204B of the plunger 204 can be designed to have sufficient contact pressure or a brittle contact line. The fuel nozzle valve 200 can be opened by moving the plunger 204 in the opening direction opposite to the closing direction until the base 204B of the plunger 204 releases the force or pressure applied to the metal elastic member 208. The plunger 204 continues to move to allow fuel 206 to flow through the opening 202A of the fuel nozzle valve bushing 202, while the metal elastic member 208 remains in place and attached (e.g., clamped or compressed) to the wall 202D of the fuel nozzle valve bushing 202.

[0025] Figure 3 This is a schematic cross-sectional view of the flow metering portion of a fuel nozzle valve 300 according to another embodiment of the present disclosure. This embodiment is similar in many respects to... Figure 2 The illustrated embodiment. In this embodiment, with Figure 2 Similar to the aforementioned embodiments, the fuel nozzle valve 300 also includes a fuel nozzle valve bushing 202 and a plunger 204. Therefore, the description of common features will not be repeated in the following paragraphs. The fuel nozzle valve 300 includes a metallic resilient member 302 configured to contact the base 204B of the plunger 204 and the seat 202B of the fuel nozzle valve bushing 202. In this embodiment, the metallic resilient member 302 is disposed on or coupled to the plunger 204. For example, the metallic resilient member 302 is coupled to the base 204B of the plunger 204. For example, the metallic resilient member 302 is coupled to the base 204B of the plunger 204 by gluing, welding, or clamping the outer edge of the metallic resilient member 302 to the base 204B of the plunger 204. The metallic resilient member 302 may be made of stainless steel or other metals that can withstand relatively high temperatures without losing elasticity or resilience. The metallic resilient member 302 may be slightly bent to provide spring-like characteristics. In one embodiment, the metallic elastic member 302 may have a conical shape (e.g., a conical washer), wherein the larger diameter of the conical shape may be configured to contact the base 204B of the plunger, and the smaller diameter of the conical shape may be configured to abut against the post 204A of the plunger 204. In this way, the metallic elastic member 302 with the conical shape can be assembled around the plunger 204. The metallic elastic member 302 is configured to move with the plunger 204.

[0026] In operation, the fuel nozzle valve 300 can be closed by moving the plunger 204 in the closing direction until the base 204B of the plunger 204, which holds the metal elastic member 302, abuts against and pushes the fuel nozzle valve 300 with a predetermined force. The metal elastic member 302 abuts against the seat 202B of the fuel nozzle valve bushing 202 and bends slightly under the applied force. As the plunger 204 closes the fuel nozzle valve 300, the base 204B contacts the metal elastic member 302, causing the metal elastic member 302 to deflect due to its compliant characteristics.

[0027] In the closed position, the metal elastic member 302 is compressed between the base 204B of the plunger 204 and the edge 202E of the seat 202B of the fuel nozzle valve bushing 202. The contact surface 302S between the metal elastic member 302 and the edge 202E of the seat 202B can be designed for high contact pressure or a wider contact line. The fuel nozzle valve 300 can be opened by moving the plunger 204 in the opening direction opposite to the closing direction until the base 204B of the plunger 204 releases the force or pressure applied to the metal elastic member 302. The plunger 204 continues to move to allow fuel 206 to flow through the opening 202A of the fuel nozzle valve bushing 202, while the metal elastic member 302 moves together with the base 204B of the plunger 204. In one embodiment, a lip (not shown) may be included on the base 204B of the plunger 204, for example at the outer edge of the base 204B, to hold the resilient metal member 302 in a specific position when the plunger 204 is moved to the open position. For example, the outer edge of the resilient member 302 may be inserted into the lip provided at the outer edge of the base 204 to engage the outer edge of the resilient member 302 to the base 204B to maintain contact between the resilient member 302 and the base 204B during movement of the plunger 204.

[0028] Figure 4 This is a schematic cross-sectional view of the flow metering portion of a fuel nozzle valve 400 according to yet another embodiment of the present disclosure. This embodiment is similar in many respects to... Figure 3 The illustrated embodiment. In this embodiment, with Figure 3 Similar to the aforementioned embodiment, the fuel nozzle valve 400 also includes a fuel nozzle valve bushing 202 and a plunger 204. Therefore, the description of common features will not be repeated in the following paragraphs. The fuel nozzle valve 400 includes a metallic resilient member 402 configured to contact the base 204B of the plunger 204 and the seat 202B of the fuel nozzle valve bushing 202. In this embodiment, similar to... Figure 3The embodiment includes a metal elastic member 302, and another metal elastic member 402 disposed on a base 204B. The metal elastic member 402 may be made of stainless steel or other metals capable of withstanding relatively high temperatures without losing elasticity or resilience. The metal elastic member 402 may be slightly bent to provide spring properties. In one embodiment, the metal elastic member 402 may have a conical shape (e.g., a conical washer), wherein the larger diameter of the conical shape may be configured to contact the base 204B of the plunger, and the smaller diameter of the conical shape may be configured to contact or abut against the post 204A of the plunger 204. In this way, the conical metal elastic member 402 is configured to assemble around the plunger 204. In one embodiment, the metal elastic member 402 is a conical washer engraved with an inner edge 402A and an outer edge 402B. The inner edge 402A is circular to match the shape or contour of the post 204A of the plunger 204, and the outer edge 402B is square such that when the plunger 204 moves to close the opening 400A of the fuel injector valve 400, the outer edge 402B aligns with the wall 202D of the fuel injector valve bushing 202. In one embodiment, as... Figure 4 As shown, the inner edge 402A of the metal elastic member 402 is thicker than the outer edge 402B of the metal elastic member 402. In order to reduce or substantially prevent the possibility of seal flutter in the fuel 206 flow when the fuel nozzle valve 400 is opened, the metal elastic member 402 may be oriented such that the thinner outer edge 402B is oriented in the fuel flow direction.

[0029] In operation, the fuel nozzle valve 400 can be closed by moving the plunger 204 in the closing direction until the base 204B of the plunger 204, which holds the metal elastic member 402, abuts against and pushes the seat 202B of the fuel nozzle valve bushing 202 with a predetermined force. The metal elastic member 402 abuts against the seat 202B of the fuel nozzle valve bushing 202 and bends slightly under the applied force. As the plunger 204 closes the fuel nozzle valve bushing 202, the base 204B contacts the metal elastic member 402, causing the metal elastic member 402 to deflect due to its compliant characteristics.

[0030] In the closed position, the resilient member 402 is compressed between the base 204B of the plunger 204 and the edge 202E of the seat 202B of the fuel nozzle valve bushing 202. The contact surface 402S between the resilient member 402 and the edge 202E of the seat 202B can be designed for high contact pressure or a wider contact line. The fuel nozzle valve 400 can be opened by moving the plunger 204 in the opening direction opposite to the closing direction until the base 204B of the plunger 204 releases the force or pressure applied to the resilient member 402. The plunger 204 continues to move to allow fuel 206 to flow through the opening 202A of the fuel nozzle valve 400, while the resilient member 402 moves together with the base 204B of the plunger 204.

[0031] High-temperature fuels offer numerous engine system-level advantages in terms of combustion efficiency and thermal management capabilities. Seals in fuel nozzles that can operate at temperatures exceeding the capabilities of elastomers are a viable technology.

[0032] Metallic elastic members 208, 302, and 402 can be configured to operate in relatively high temperature environments (between 800°F and 1500°F). Metallic elastic members 208, 302, and 402 can provide a seal with relatively low and relatively uniform contact pressure. In some embodiments, metallic elastic members 208, 302, and 402 may be coated with a material to provide additional stiffness and / or resistance to particles in flow. The coating material can be applied to the entire surface of the metallic elastic members 208, 302, and 402. For example, a compliant coating can be used to improve the uniformity of contact pressure by utilizing a larger contact area.

[0033] As can be understood from the above discussion, a fuel nozzle valve includes: a fuel nozzle valve bushing having a channel and a seat, the channel having an opening allowing fuel to flow through it; and a plunger having a post and a base substantially perpendicular to the plunger, the plunger being configured to move relative to the fuel nozzle valve bushing to seal or open the opening of the fuel nozzle valve. The fuel system also includes a metallic elastic member configured to contact the base of the plunger and the seat of the fuel nozzle valve to seal the opening of the fuel nozzle valve when the plunger moves to seal the fuel nozzle valve.

[0034] According to the fuel nozzle valve described above, a metal elastic member is attached to the wall of the fuel nozzle valve, and the metal elastic member remains attached to the wall of the fuel nozzle valve when the plunger moves to open the fuel nozzle valve.

[0035] According to any of the preceding clauses, when the plunger moves to close and seal the fuel nozzle valve, the base of the plunger abuts against and pushes the metal elastic member until the metal elastic member abuts against the seat of the fuel nozzle valve.

[0036] According to any of the above-mentioned fuel nozzle valves, a metal elastic member is connected to a plunger.

[0037] According to any of the preceding clauses, the metal elastic member of the fuel nozzle valve is configured to move together with the plunger.

[0038] According to any of the preceding clauses, the metal elastic member is configured to be compressed between the base of the plunger and the edge of the seat of the fuel nozzle valve bushing.

[0039] According to any of the preceding clauses, the metal elastic member of the fuel nozzle valve is coated with a coating material to provide additional stiffness and / or resistance to particles in the fuel flow.

[0040] According to any of the preceding clauses, the metal elastic member has a conical shape, the larger diameter of the conical shape contacting the base of the plunger, and the smaller diameter of the conical shape contacting the post of the plunger.

[0041] According to any of the preceding clauses, the fuel nozzle valve has a conical metal elastic member configured to assemble around the plunger.

[0042] According to any of the preceding clauses, the fuel nozzle valve has a conical metal elastic member configured to have: a circular inner edge for providing a contact surface with the plunger; and an outer edge that is square, such that when the plunger moves to close the opening of the fuel nozzle valve, the outer edge aligns with the wall of the fuel nozzle valve bushing.

[0043] According to any of the preceding clauses, in a fuel nozzle valve, the inner edge of the conical metal elastic member is thicker than the outer edge of the conical metal elastic member, and when the fuel nozzle valve is open, the outer edge is oriented in the fuel flow direction to reduce or substantially prevent seal flutter. Seal flutter can occur when the seal moves in an irregular or fluttering motion (e.g., flapping).

[0044] Another aspect of this disclosure is to provide a turbine engine having a fuel system. The fuel system includes a fuel nozzle valve having: a passage and a seat, the passage having an opening for allowing fuel to flow through it; and a plunger having a post and a base substantially perpendicular to the post, the plunger being configured to move relative to a fuel nozzle valve bushing to seal or open the opening of the fuel nozzle valve. The fuel system further includes a metallic elastic member configured to contact the base of the plunger and the seat of the fuel nozzle valve to seal the opening of the fuel nozzle valve when the plunger moves to seal the fuel nozzle valve.

[0045] According to any of the preceding clauses of the turbine engine, the metal elastic member is attached to the wall of the fuel nozzle valve bushing, and when the plunger moves to open the fuel nozzle valve, the metal elastic member remains attached to the wall of the fuel nozzle valve bushing.

[0046] According to any of the preceding clauses of the turbine engine, when the plunger moves to close and seal the fuel nozzle valve, the base of the plunger abuts against and pushes the metal elastic member until the metal elastic member abuts against the seat of the fuel nozzle valve bushing.

[0047] According to any of the preceding clauses, in a turbine engine, a metal elastic member is connected to a plunger.

[0048] According to any of the preceding clauses of the turbine engine, the metal elastic member is configured to move together with the plunger.

[0049] According to any of the preceding clauses, the metal elastic member is configured to be compressed between the base of the plunger and the edge of the seat of the fuel nozzle valve bushing.

[0050] According to any of the preceding clauses, the metal elastic component is coated with a coating material to provide additional stiffness and / or resistance to particles in the fuel flow.

[0051] According to any of the preceding clauses, the metal elastic member has a conical shape, the larger diameter of the conical shape contacting the base of the plunger, and the smaller diameter of the conical shape contacting the post of the plunger.

[0052] According to any of the preceding clauses, the turbine engine has a conical metal elastic member configured to assemble around the plunger.

[0053] According to any of the preceding clauses, the turbine engine has a conical metal elastic member configured to have: a circular inner edge for providing a contact surface with the plunger; and an outer edge that is square, such that when the plunger moves to close the opening of the fuel nozzle valve, the outer edge aligns with the wall of the fuel nozzle valve bushing.

[0054] According to any of the preceding clauses, the inner edge of the conical metal elastic member is thicker than the outer edge of the conical metal elastic member, wherein when the fuel nozzle valve is open, the outer edge is oriented in the fuel flow direction to reduce or substantially prevent seal flutter.

[0055] While the foregoing description is directed to preferred embodiments of the present disclosure, it should be noted that other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A fuel nozzle valve, characterized in that, include: A fuel nozzle valve bushing having a channel and a seat, the channel having an opening that allows fuel to flow through it; A plunger having a post and a base forming a T-shape, the plunger being configured to move relative to the fuel nozzle valve bushing to seal or open the opening of the fuel nozzle valve; and A metal elastic member configured to contact the base of the plunger and the seat of the fuel nozzle valve bushing to seal the opening of the fuel nozzle valve when the plunger moves to seal the fuel nozzle valve. The metal elastic member has a conical shape and is configured to be compressed between the base of the plunger and the edge of the seat of the fuel nozzle valve bushing, and the contact surface between the metal elastic member and the edge of the seat is located between the inner edge and the outer edge of the metal elastic member.

2. The fuel nozzle valve according to claim 1, characterized in that, in, The resilient metal member is attached to the wall of the fuel nozzle valve bushing, and remains attached to the wall of the fuel nozzle valve bushing when the plunger moves to open the fuel nozzle valve.

3. The fuel nozzle valve according to claim 1, characterized in that, in, When the plunger moves to close and seal the fuel nozzle valve, the base of the plunger abuts against and pushes the metal elastic member until the metal elastic member abuts against the seat of the fuel nozzle valve bushing.

4. The fuel nozzle valve according to claim 1, characterized in that, in, The metal elastic member is connected to the plunger.

5. The fuel nozzle valve according to claim 1, characterized in that, in, The metal elastic member is configured to move together with the plunger.

6. The fuel nozzle valve according to claim 1, characterized in that, in, The metal elastic member is coated with a coating material to provide additional stiffness and / or resistance to particles in the fuel.

7. The fuel nozzle valve according to claim 1, characterized in that, in, The larger diameter of the cone shape contacts the base of the plunger, and the smaller diameter of the cone shape contacts the post of the plunger.

8. The fuel nozzle valve according to claim 7, characterized in that, in, The metal elastic member having the conical shape is configured to assemble around the plunger.

9. The fuel nozzle valve according to claim 7, characterized in that, in, The metal elastic member having the conical shape is configured to have: a circular inner edge for providing a contact surface with the post of the plunger; and an outer edge that is square, such that when the plunger moves to close the opening of the fuel nozzle valve, the outer edge is aligned with the wall of the fuel nozzle valve bushing.

10. The fuel nozzle valve according to claim 7, characterized in that, in, The inner edge of the metal elastic member having the conical shape is thicker than the outer edge of the metal elastic member having the conical shape, wherein, when the fuel nozzle valve is open, the outer edge is oriented in the fuel flow direction to reduce or prevent seal flutter.

11. A turbine engine, characterized in that, include: Fuel nozzle valve, the fuel nozzle valve comprising: (a) A fuel nozzle valve bushing having a channel and a seat, the channel having an opening that allows fuel to flow through it; (b) A plunger having a post and a base forming a T-shape, the plunger being configured to move relative to the fuel nozzle valve bushing to seal or open the opening of the fuel nozzle valve; and (c) A metal elastic member configured to contact the base of the plunger and the seat of the fuel nozzle valve to seal the opening of the fuel nozzle valve when the plunger moves to seal the fuel nozzle valve. The metal elastic member has a conical shape and is configured to be compressed between the base of the plunger and the edge of the seat of the fuel nozzle valve bushing, and the contact surface between the metal elastic member and the edge of the seat is located between the inner edge and the outer edge of the metal elastic member.

12. The turbine engine according to claim 11, characterized in that, in, The resilient metal member is attached to the wall of the fuel nozzle valve bushing, and remains attached to the wall of the fuel nozzle valve bushing when the plunger moves to open the fuel nozzle valve.

13. The turbine engine according to claim 11, characterized in that, in, When the plunger moves to close and seal the fuel nozzle valve, the base of the plunger abuts against and pushes the metal elastic member until the metal elastic member abuts against the seat of the fuel nozzle valve bushing.

14. The turbine engine according to claim 11, characterized in that, in, The metal elastic member is connected to the plunger.

15. The turbine engine according to claim 11, characterized in that, in, The metal elastic member is configured to move together with the plunger.

16. The turbine engine according to claim 11, characterized in that, in, The larger diameter of the cone shape contacts the base of the plunger, and the smaller diameter of the cone shape contacts the post of the plunger.

17. The turbine engine according to claim 16, characterized in that, in, The metal elastic member having the conical shape is configured to assemble around the plunger.

18. The turbine engine according to claim 16, characterized in that, in, The metal elastic member having the conical shape is configured to have: a circular inner edge for providing a contact surface with the post of the plunger; and an outer edge that is square, such that when the plunger moves to close the opening of the fuel nozzle valve, the outer edge is aligned with the wall of the fuel nozzle valve bushing.

19. The turbine engine according to claim 16, characterized in that, in, The inner edge of the metal elastic member having the conical shape is thicker than the outer edge of the metal elastic member having the conical shape, wherein, when the fuel nozzle valve is open, the outer edge is oriented in the fuel flow direction to reduce or prevent seal flutter.

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