A fuel leakage control device, method and application of a multi-oil gas turbine or aircraft engine

Abstract

The present invention discloses a fuel leakage control device, method and application of a multi-oil-circuit gas turbine or aircraft engine, which belongs to the technical field of fuel control of gas turbines or aircraft engines, and is used for the rapid, safe and reliable discharge of fuel from multiple oil circuits when the engine is stopped, while ensuring the independent operation and sealing of each oil circuit under normal operating conditions. The device includes an upper shell, a bushing, an end cover, a valve, a return spring, a push rod and an electromagnetic drive component. A plurality of groups of fuel through holes and oil leakage through holes are provided in the bushing, and accurate separation and control of the fuel passage are achieved through an annular step portion and a conical sealing structure. The method includes the steps of initialization, normal operation of the engine, preparation for oil leakage when stopped, fuel discharge, sequential discharge of multiple oil circuits, completion of discharge and system reset. The present invention has a reasonable structural design, a precise control method, significant sealing performance and oil leakage efficiency, is suitable for a variety of complex working conditions, and has broad application prospects and engineering value.

Description

Technical Field

[0001] The present invention belongs to the technical field of fuel system control of gas turbines or aircraft engines, and relates to a fuel leakage control design of gas turbines or aircraft engines, and in particular to a fuel leakage control device, method and application of a multi-oil-circuit gas turbine or aircraft engine. Background Art

[0002] As the core power unit of modern aircraft, the design of the fuel system of aircraft engines directly affects the performance and reliability of the engine. In order to reduce the fuel consumption rate of the engine and widen the flameout boundary of the combustion chamber, aircraft engines currently generally adopt a multi-fuel supply circuit design scheme, which usually includes a main fuel supply system and an auxiliary fuel supply system to achieve precise fuel supply control under different working conditions. However, the introduction of multi-fuel circuit design also increases the complexity of the fuel system, especially when the engine is stopped. In order to prevent carbon deposition on the fuel nozzle and the fuel main pipe, the fuel in the fuel main pipe must be drained out in time. At the same time, when the engine is running normally, the oil leakage system cannot affect the normal fuel supply of each fuel circuit, which puts higher requirements on the fuel leakage control device.

[0003] At present, conventional fuel drain control devices are mostly switched on and off by various valves driven by hydraulic pressure, and the fuel is sealed and discharged mainly by the opening and closing action of the valves. However, this traditional mechanical fuel drain control device has some inherent defects: First, long-term mechanical operation will cause different degrees of wear of key components such as valves and seals, which will affect the motion sensitivity of the system, and it is easy to cause problems such as jamming and reduced sealing performance, and may even cause fuel leakage problems. Especially under complex working conditions such as high temperature and high pressure, the leaked fuel will further aggravate the carbon deposition problem and may even cause safety hazards such as fire, which directly threatens flight safety. Second, in order to meet the needs of simultaneous oil leakage in multiple oil circuits, traditional oil leakage control devices usually need to configure independent oil leakage channels for each oil circuit, which makes the mechanical transmission structure in the oil leakage control device more complicated, which not only increases the overall weight of the system, but also significantly increases the spatial size of the device, making it difficult to realize the miniaturization design of the fuel system, which is inconsistent with the design requirements of modern aircraft engines for miniaturization and lightweight. At the same time, the control accuracy and response speed of traditional mechanical fuel leakage control devices are significantly reduced with the use time. The wear, deformation, inertia and friction of mechanical transmission parts not only affect the sealing performance, but also significantly affect the control response speed, resulting in reduced oil discharge control accuracy and difficulty in achieving precise control of fuel flow. During the rapid start and stop of the engine, these defects may lead to improper control of the oil discharge timing, affecting the operating safety of the engine. In addition, the complex mechanical transmission structure also increases the difficulty and cost of maintenance.

[0004] In summary, the existing fuel leakage control devices mainly have defects and shortcomings such as mechanical wear leading to reduced sealing performance, complex system structure difficult to achieve miniaturization, insufficient control accuracy and response speed, and insufficient operating stability and adaptability. Therefore, how to design an efficient, reliable, compact and adaptable multi-oil-circuit aircraft engine fuel leakage control device for multiple working conditions is a technical problem that needs to be urgently solved in the field of aircraft engine fuel systems. Summary of the invention

[0005] 1. Purpose of the invention

[0006] In view of the above-mentioned defects and deficiencies of the existing fuel oil leakage control device, in order to solve the limitations of the existing hydraulic actuation oil leakage in terms of sealing performance, structural complexity, response speed and reliability, the present invention aims to provide a fuel oil leakage control device, method and application for a multi-oil gas turbine or aircraft engine, which replaces the start-stop mode of the traditional mechanical hydraulic actuation by adopting an electromagnetic control method to drive the valve, combined with a double-end face reliable sealing structure and a modular design of a multi-oil oil leakage channel, while reducing the size and weight, to achieve the leakage and sealing of more independent oil circuits. At the same time, the present invention optimizes the internal channel design of the bushing, and the connection between multiple groups of reference oil chambers and valve through holes, so as to achieve the synchronous discharge of fuel in multiple oil circuits, and meet the demand for rapid fuel discharge when the engine is stopped. The present invention can not only maintain the miniaturization and lightweight of the system, but also significantly improve the operating efficiency and adaptability of the oil leakage device, and is particularly suitable for complex working conditions of high temperature, high pressure and multi-channel fuel systems.

[0007] (II) Technical solution

[0008] In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions:

[0009] The first invention object of the present invention is to provide a fuel leakage control device for a multi-oil-path gas turbine or aircraft engine, which is used to quickly, safely and reliably drain fuel from multiple fuel supply paths when the engine is stopped, while ensuring the independent operation and reliable sealing of each oil path under normal operation, preventing carbon deposition or leakage caused by fuel residue and improving the reliability of the fuel system, and at least comprises an upper shell, an end cover, a bushing, a valve, a push rod and an electromagnetic drive component, wherein:

[0010] The upper shell is fixedly installed on a multi-oil-path gas turbine or an aircraft engine, and its interior is formed as an upper shell inner cavity extending in the axial direction, with a closed top and an open bottom. A secondary fuel oil path channel is provided on the top, and a main fuel oil path channel and a fuel discharge channel are provided on the side wall. The main fuel oil path channel is provided near the middle of the upper shell, and the fuel discharge channel is provided near the bottom of the upper shell;

[0011] The bushing is a hollow cylindrical structure with openings at both ends, coaxially arranged in the inner cavity of the upper shell body, with an axial gap between its top and the top wall of the inner cavity of the upper shell body, and a radial gap between its outer wall and the side wall of the inner cavity of the upper shell body, and the top, lower middle position and bottom of its outer wall are respectively provided with the first and second annular step portions and external threaded portions, a main fuel inlet space is formed between the first and second annular step portions and the side wall of the inner cavity of the upper shell body, a fuel discharge space is formed between the second annular step portion, the external threaded portion and the side wall of the inner cavity of the upper shell body, and the bushing is fixedly connected to the top of the electromagnetic drive component through the external threaded portion; a main fuel through hole connecting the inner cavity of the bushing with the main fuel inlet space, and a fuel discharge through hole connecting the inner cavity of the bushing with the fuel discharge space are also provided on its outer wall; a conical surface structure is provided at the lower middle position of its inner wall, and the inner wall conical surface structure divides the inner cavity of the bushing into an upper space and a lower space in the axial direction, and the lower space is formed as an oil discharge cavity;

[0012] The end cover is fixed to the top of the bushing, and an auxiliary fuel inlet space is formed between the top and the top wall of the inner cavity of the upper shell. An auxiliary fuel through hole connecting the auxiliary fuel inlet space and the inner cavity of the bushing is provided in the center, and a stepped groove is provided at the bottom of the end cover;

[0013] The valve is a cylindrical structure with an opening at the top and a closed bottom, which is coaxially arranged in the upper space of the inner cavity of the bushing, and includes a valve main body and a diameter-reducing part, wherein: the outer wall diameter of the valve main body is adapted to the inner wall diameter of the bushing, and a return spring is provided in the inner cavity of the valve, the top of the return spring is against the stepped groove of the end cover, and the bottom pushes the valve to reset; a reference oil pressure cavity is formed between the outer wall of the diameter-reducing part and the inner wall of the bushing, and a secondary oil circuit oil drain port connecting the inner cavity of the valve and the reference oil pressure cavity is provided on the outer wall, and the bottom is formed into a conical boss structure, which is adapted to the conical surface of the inner wall of the bushing and forms a conical sealing fit;

[0014] The electromagnetic drive component is arranged at the bottom of the upper shell, the top of which is processed into a bushing installation groove with a flange flange, and the bottom is designed as an electromagnetic drive assembly. The bottom wall of the bushing installation groove is provided with a push rod through hole for allowing the push rod to pass through, and the end face is sealed with the bottom of the upper shell through the flange flange;

[0015] The push rod is an axially extending rod-shaped structure, with its bottom fixed to the moving iron core of the electromagnetic drive component and its top abutting against the conical boss at the bottom of the valve. When the electromagnetic drive component is energized, the driving force generated by the moving iron core is transmitted axially along the push rod, pushing the valve to move upward to open the oil leakage channel.

[0016] The second object of the present invention is to provide a fuel leakage control method for a multi-oil gas turbine or aircraft engine. Based on the fuel leakage control device for a multi-oil gas turbine or aircraft engine of the present invention, the control method comprises at least the following steps when implemented:

[0017] SS1. Initialization operation of fuel supply path:

[0018] Check that the main fuel oil circuit, auxiliary fuel oil circuit and oil leakage circuit of the engine are connected with the main fuel oil circuit channel, auxiliary fuel oil circuit channel and fuel leakage channel of the upper shell respectively, and ensure the physical connection between the fuel supply path and the oil leakage path; confirm the installation status of the bushing, valve, end cover and electromagnetic drive components in the fuel leakage control device, ensure that the valve is in the initial sealing position of the return spring, the main fuel inlet space, auxiliary fuel inlet space and fuel leakage space are all in a sealed state, and the fuel supply path maintains normal operation;

[0019] SS2. Fuel supply control under normal engine operation:

[0020] When the engine is in normal operation, the electromagnetic drive component is powered off, and the return spring makes the conical boss of the valve fit with the conical sealing structure of the inner wall of the bushing; the main fuel oil passage is disconnected from the fuel discharge passage, the auxiliary fuel oil passage is disconnected from the fuel discharge passage, the main fuel through hole is connected to the main fuel inlet space, the auxiliary fuel through hole is connected to the auxiliary fuel inlet space, and the respective fuel supply paths are isolated by the sealing structure of the valve and the bushing; the reference oil pressure chamber and the oil discharge chamber are separated by the oil drain port, and the fuel is supplied to the engine through the main fuel oil passage and the auxiliary fuel oil passage, and the oil drain passage is in a closed state;

[0021] SS3. Receiving and controlling the engine stop signal:

[0022] When receiving the engine stop signal, the control system sends a power-on command to the electromagnetic drive component, controls the coil in the electromagnetic drive component to be energized, and generates an axial driving force; at this time, the moving iron core drives the push rod to move upward in the axial direction under the action of the electromagnetic force, overcomes the elastic force of the return spring, and pushes the valve to move upward in the axial direction, thereby releasing the sealing fit between the conical boss at the bottom of the valve and the conical surface of the inner wall of the bushing;

[0023] SS4. The drain passages of the main fuel line and the auxiliary fuel line are open:

[0024] As the valve moves upward, the conical boss at the bottom of the valve is separated from the conical structure of the inner wall of the bushing, the reference oil pressure chamber is gradually connected with the oil drain chamber, the main fuel inlet space is connected with the fuel drain space through the reference oil pressure chamber and the oil drain chamber, and at the same time, the auxiliary fuel inlet space is connected with the fuel drain space through the reference oil pressure chamber and the oil drain chamber, so that the main fuel inlet space, the auxiliary fuel inlet space, the reference oil pressure chamber, the oil drain chamber and the fuel drain space are completely connected, and the main fuel oil circuit and the auxiliary fuel oil circuit are synchronously drained, and the fuel is discharged through the fuel drain passage;

[0025] SS5. Dynamic monitoring of fuel leakage status:

[0026] During the fuel leakage process after the engine stops, the control system monitors the leakage status of the main fuel oil circuit and the auxiliary fuel oil circuit in real time to ensure that the leakage path is unobstructed; when the pressure drops to the preset threshold, it is determined that the leakage process is nearly completed; at the same time, the current value of the electromagnetic drive component is monitored to ensure that it works within the normal range; if the flow of the fuel leakage path is detected to be abnormal or blocked, the control system sends an alarm signal through the fault diagnosis module and automatically controls the electromagnetic drive component to enter a forced power-off state;

[0027] SS6. Reset operation after fuel drain is completed:

[0028] When the fuel drain is completed and the control system confirms that there is no residual fuel in the drain path, the power supply to the electromagnetic drive component is stopped. After the electromagnetic drive component is powered off, the moving iron core is reset under the action of the reset spring, the push rod returns to its position and pushes the valve downward until the conical boss at the bottom of the valve is tightly fitted with the conical structure of the inner wall of the bushing again, and the seal between the reference oil pressure chamber and the drain oil chamber is restored; the main fuel oil circuit, the auxiliary fuel oil circuit and the fuel drain path are disconnected, and the fuel supply path is restored to a sealed state;

[0029] SS7. Sealing performance test after system reset:

[0030] After the fuel drain operation is completed, the system tests the sealing performance of the fuel supply path to ensure that the main fuel circuit and the auxiliary fuel circuit are in good sealing condition; after the test is qualified, it is confirmed that the fuel drain control device has returned to the initial operating state and can be put into engine operation again.

[0031] The third object of the present invention is to provide a multi-oil circuit gas turbine or aircraft engine, including the above-mentioned fuel oil leakage control device of the present invention.

[0032] (III) Technical Effect

[0033] Compared with the prior art, the fuel leakage control device, method and application of the multi-oil-circuit gas turbine or aircraft engine of the present invention have the following beneficial and significant technical effects:

[0034] (1) The present invention provides a plurality of through holes on the upper housing, the bushing and the valve, cooperates with the conical sealing design of the bushing and the valve, and adopts a control structure combining an electromagnetic drive component and a return spring. This not only ensures the independent operation and sealing of the main fuel oil circuit and the auxiliary fuel oil circuit under normal engine operation, but also enables rapid switching to the oil drain mode when the engine is stopped, thereby achieving synchronous discharge of fuel from multiple oil circuits. This eliminates the problems of slow response, leakage or incomplete oil drain caused by complex circuits in traditional hydraulic control systems, thereby improving the efficiency and safety of the fuel system.

[0035] (2) The present invention adopts a conical sealing structure between the valve and the bushing, combined with a spatial separation design of a multi-annular step portion, to ensure that the fuel can maintain a stable sealing state under high pressure and high flow rate environments, avoid performance degradation or safety hazards caused by fuel leakage, and effectively avoid the cross leakage of fuel between the main and auxiliary fuel passages and the fuel discharge passage. The precise design of the reset spring further ensures that the valve is in close contact with the conical surface of the inner wall of the bushing when the power is off and reset, thereby enhancing the sealing reliability of the device and being suitable for complex working conditions such as high pressure and high temperature. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 Shown is a cross-sectional schematic diagram of a fuel leakage control device for a multi-oil-circuit gas turbine or aircraft engine provided by an embodiment of the present invention.

[0037] Figure 2 Shown Figure 1 A local enlarged schematic diagram of area Ⅰ in the middle.

[0038] Figure 3 Shown is a schematic cross-sectional view of each oil cavity / space in an embodiment of the present invention.

[0039] Figure 4 FIG. 1 is a schematic cross-sectional view of an upper housing in an embodiment of the present invention.

[0040] Figure 5 Shown is a schematic cross-sectional view of a bushing in an embodiment of the present invention.

[0041] Figure 6 Shown is a schematic cross-sectional view of a valve in an embodiment of the present invention.

[0042] Figure 7 Shown is a flow chart of a fuel leakage control method for a multi-oil-circuit gas turbine or aircraft engine provided by an embodiment of the present invention.

[0043] Description of reference numerals:

[0044] Upper shell 1, upper shell cavity 10, auxiliary fuel oil channel 11, main fuel oil channel 12, fuel discharge channel 13, bushing 2, inner wall conical structure 20, first annular step portion 21, second annular step portion 22, external threaded portion 23, main fuel through hole 24, fuel discharge through hole 25, main fuel inlet space 26, fuel discharge space 27, upper space 28, lower space 29, end cover 3, stepped groove 31, auxiliary fuel inlet space 32, auxiliary fuel through hole 33, valve 4, valve body 41, diameter reduction portion 42, auxiliary oil channel drain port 43, conical boss structure 44, reference oil pressure chamber 45, return spring 5, adjustment gasket 6, push rod 7, electromagnetic drive component 8. DETAILED DESCRIPTION

[0045] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions of the fuel leakage control device and control method of the multi-oil gas turbine or aircraft engine provided by the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0046] Example 1

[0047] As a specific example, Figures 1 to 6 As shown, the fuel leakage control device for a multi-oil-circuit gas turbine or aircraft engine provided by an embodiment of the present invention is used to quickly, safely and reliably drain fuel from multiple fuel supply paths when the engine is stopped, while ensuring the independent operation and reliable sealing of each oil circuit under normal operating conditions, preventing fuel residue from causing carbon deposition or leakage and improving the reliability of the fuel system. The device mainly includes an upper shell 1, a bushing 2, an end cover 3, a valve 4, a return spring 5, an adjustment gasket 6, a push rod 7, an electromagnetic drive component 8, and sealing rings arranged on multiple joint surfaces.

[0048] In the fuel leakage control device of the multi-oil gas turbine or aircraft engine of the present invention, Figure 1 , Figure 3 , Figure 4 As shown, the upper shell 1 is fixedly connected to the multi-oil-circuit gas turbine or the aircraft engine and its interior is formed into an upper shell inner cavity 10 extending in the axial direction. The top of the upper shell inner cavity 10 is closed and the bottom is open. An auxiliary fuel oil passage 11 extending in the axial direction and communicating with the upper shell inner cavity 10 is provided at the center of the top of the upper shell, and a main fuel oil passage 12 and a fuel discharge passage 13 extending in the radial direction and communicating with the upper shell inner cavity 10 are provided on the side wall of the upper shell, wherein the main fuel oil passage 12 is arranged near the middle position of the upper shell in the axial direction, and the fuel discharge passage 13 is arranged near the bottom of the upper shell in the axial direction, and the auxiliary fuel oil passage 11, the main fuel oil passage 12, and the fuel discharge passage 13 are respectively connected to the main fuel oil passage, the auxiliary fuel oil passage, and the oil discharge passage of the engine.

[0049] Preferably, the auxiliary fuel oil circuit channel 11 of the upper shell 1 extends axially to achieve communication between the auxiliary fuel inlet space 32 in the upper shell inner cavity 10 and the auxiliary fuel oil circuit of the engine; the main fuel oil circuit channel 12 extends radially to achieve communication between the main fuel inlet space 26 in the upper shell inner cavity 10 and the main fuel oil circuit of the engine; the fuel discharge channel 13 extends radially to achieve communication between the fuel discharge space 27 in the upper shell inner cavity 10 and the engine oil discharge passage.

[0050] In the fuel leakage control device of the multi-oil gas turbine or aircraft engine of the present invention, Figure 1 , Figure 3 , Figure 5 As shown, the bushing 2 is a hollow cylindrical structure extending axially and open at both ends, and is coaxially arranged in the upper shell cavity 10, with an axial spacing between its top and the top wall of the upper shell cavity 10, and a radial gap between its outer wall and the side wall of the upper shell cavity 10, and a first annular step portion 21 and a second annular step portion 22 protruding radially outward are respectively provided at the top and the lower middle position of the outer wall, and a sealing structure is formed between the first annular step portion 21, the second annular step portion 22 and the side wall of the upper shell cavity 10, and an external thread portion 23 is also provided at the bottom of the outer wall, and is fixedly connected to the bushing mounting groove at the top of the electromagnetic drive component 8 through the external thread portion 23. The outer wall of the bushing 2 is also provided with a main fuel through hole 24 and a fuel discharge through hole 25 which are connected with the inner cavity thereof, wherein the main fuel through hole 24 is axially arranged between the first annular step portion 21 and the second annular step portion 22, and is axially located below the main fuel oil passage 12 of the upper shell 1, and is arranged adjacent to the second annular step portion 22; the fuel discharge through hole 25 is axially arranged between the second annular step portion 22 and the external threaded portion 13, and its axial position is equivalent to the fuel discharge passage 13 of the upper shell 1.

[0051] The radial space between the first annular step 21, the second annular step 22 and the side wall of the upper shell inner cavity 10 forms a main fuel inlet space 26, and the radial space between the second annular step 22, the external threaded portion 23 and the side wall of the upper shell inner cavity 10 forms a fuel discharge space 27. The main fuel through hole 24 of the bushing 2 and the main fuel oil passage 12 of the upper shell 1 are both connected to the main fuel inlet space 26, and the fuel discharge through hole 25 of the bushing 2 and the fuel discharge passage 13 of the upper shell 1 are both connected to the fuel discharge space 27. In addition, an inner wall conical surface structure 20 protruding radially inward is provided on the inner wall of the bushing 2. The axial setting position of the inner wall conical surface structure 20 is equivalent to that of the second annular step 22, and the inner cavity of the bushing 2 is divided into an upper space 28 and a lower space 29 in the axial direction.

[0052] Preferably, the first annular step portion 21 and the second annular step portion 22 of the bushing 2 are both provided with an annular sealing ring groove, in which a sealing ring is installed, and sealing gaskets are provided between the external thread portion 23 at the bottom of the bushing 2 and the bushing installation groove of the electromagnetic drive component 8, between the end cover 3 and the top of the bushing 2, and between the inner wall conical surface structure 20 of the bushing 2 and the conical surface boss structure 44 at the bottom of the valve 4. In addition, the axial distance between the first annular step portion 21 and the second annular step portion 22 and between the second annular step portion 22 and the external thread portion 23 are optimized according to the fuel flow requirements of the engine to ensure that the main fuel inlet space 26 and the fuel discharge space 27 maintain stable flow distribution under the high-pressure fuel discharge state, and reduce the flow noise and pulsation that may be generated during the discharge process.

[0053] In addition, the axial setting position of the inner wall conical surface structure 20 of the bushing 2 is preferably equivalent to the second annular step portion 22, and a chamfer design with an arc transition is adopted, and the surface roughness of the conical surface sealing fitting is processed to Ra≤0.4 μm to reduce the contact stress concentration problem during the conical surface sealing fitting, and the contact area of ​​the conical surface sealing fitting is optimized to maintain good sealing performance under high-pressure fuel environment and effectively reduce the risk of leakage caused by wear or deformation.

[0054] Preferably, the main fuel through hole 24 and the fuel discharge through hole 25 provided on the outer wall of the bushing 2 extend radially, are multiple in number and are evenly distributed circumferentially, and the axial position of the main fuel through hole 24 is lower than the main fuel oil passage 12 of the upper shell 1 and is located between the first annular step portion 21 and the second annular step portion 22, and the axial position of the fuel discharge through hole 25 is lower than the fuel discharge passage 13 of the upper shell 1 and is located between the second annular step portion 22 and the external threaded portion 23.

[0055] In the fuel leakage control device of the multi-oil gas turbine or aircraft engine of the present invention, Figure 1 , Figure 3 As shown, the end cover 3 is fixedly and sealedly arranged on the top of the bushing 2, the top of which is processed to form a flange, the bottom of which is processed to form a stepped groove 31, the space between the top of the end cover 3 and the top wall of the upper shell cavity 10 is formed as a secondary fuel inlet space 32, and a secondary fuel through hole 33 is provided at the center of the top of the end cover 3 to connect the secondary fuel inlet space 32 with the internal space 28 of the bushing 2. And wherein, the secondary fuel through hole 33 is preferably set as an inner hexagonal hole, so that the end cover 3 and the bushing 2 can be rotated and tightened with an inner hexagonal wrench. The stepped groove 31 provided at the bottom of the end cover 3 is used to accommodate the adjustment gasket 6 and fix the upper end of the reset spring 5. Preferably, the adjustment gasket 6 is connected to the top end face of the reset spring 5, and the free length, number of turns and stiffness coefficient of the reset spring 5 are designed to match the mass of the valve 4 and the maximum output thrust of the electromagnetic drive component 8.

[0056] In the fuel leakage control device of the multi-oil gas turbine or aircraft engine of the present invention, Figures 1 to 3 As shown in Figures 6 and 7, the valve 4 is a cylindrical structure with an open top and a closed bottom, which is coaxially arranged in the upper space 28 of the inner cavity of the bushing 2, and includes a valve body 41 and a diameter-reducing portion 42 arranged at the bottom of the valve body 41 and is formed as a stepped structure as a whole, wherein: the outer wall diameter of the valve body 41 is adapted to the inner wall diameter of the bushing 2, and can move up and down in the axial direction relative to the inner wall of the bushing 2, and a return spring 5 is arranged in the inner cavity of the valve body 41, and the return spring 5 is arranged in the inner cavity of the valve body 41. The upper end of the spring 5 is arranged in the stepped groove 31 of the end cover 3 to provide a reset force to reset the valve 4 to the sealing position when the electromagnetic drive component is powered off; the space between the outer wall of the diameter reduction portion 42 and the inner wall of the bushing 2 is formed as a reference oil pressure chamber 45, and a secondary oil circuit drain port 43 connecting the valve cavity and the reference oil pressure chamber 44 is provided on its outer wall, and its bottom wall is processed to form a conical boss structure 44, and is adapted to the inner wall conical structure 20 of the bushing 2 to form a conical sealing fit.

[0057] Preferably, the transition portion between the valve body 41 and the diameter reduction portion 42 in the valve inner cavity is formed as an annular step surface for limiting the lower end position of the reset spring 5, and the axial distance between the annular step surface and the end cover step groove is optimized so that the reset spring maintains a stable compression state when the electromagnetic drive component is powered off, and the reset spring applies elastic force upward to ensure that the valve avoids tilting or jamming during the reset process, thereby further improving the sealing performance and the stability of the device operation. In addition, the auxiliary oil circuit oil leakage port 43 provided on the outer wall of the diameter reduction portion 42 extends radially and is evenly distributed in the circumferential direction to ensure that there is sufficient flow area during the auxiliary oil circuit oil leakage process, and the axial setting position of the auxiliary oil circuit oil leakage port 43 needs to ensure that the valve inner cavity, the reference oil pressure chamber and the oil discharge oil chamber can be connected at the same time during the upward movement of the valve 4, and the auxiliary oil circuit oil leakage port 43 is completely isolated from the reference oil pressure chamber 45 when the valve 4 is reset to the sealing position.

[0058] In the fuel leakage control device of the multi-oil gas turbine or aircraft engine of the present invention, Figure 1 As shown, the electromagnetic drive component 8 is arranged at the bottom of the upper housing 1, the top of which is processed into a bushing installation groove with a flange flange, the bottom is designed as an electromagnetic drive assembly, the bottom wall of the bushing installation groove is provided with a push rod through hole for allowing the push rod to pass through, and the end face is sealed with the bottom of the upper housing 1 through the flange flange. The push rod 7 is a rod-shaped structure extending in the axial direction, the bottom of which is fixedly connected to the moving iron core of the electromagnetic drive component 8, the rod body of which passes through the push rod through hole on the bushing installation groove of the electromagnetic drive component 8, and the top of which abuts against the conical boss structure at the bottom of the valve 4.

[0059] Preferably, the electromagnetic drive assembly 8 includes a coil, a static iron core and a moving iron core. The stroke of the moving iron core is designed to be no less than 3 mm. The design parameters of the coil need to ensure that sufficient electromagnetic driving force can be generated under a 24V working voltage to overcome the effects of the reset spring force and the oil pressure. In terms of the structural setting of the push rod 7, the push rod 7 is preferably made of non-magnetic material to avoid being affected by the electromagnetic field. The connection between the push rod 7 and the moving iron core is fixed by a thread. The contact surface between the top and the bottom of the valve is specially hardened to improve wear resistance. The axial length of the push rod is reasonably designed according to the stroke requirements of the electromagnetic drive component.

[0060] The working principle of the engine fuel leakage control device of the present invention is as follows:

[0061] When the engine is in normal operation, the fuel leakage control device is normally closed, the main fuel inlet space 26 and the reference oil pressure chamber 45 are cut off, and the end faces of the two oil pressure chambers are sealed. The auxiliary fuel inlet space 32 is connected to the valve oil chamber and the reference oil pressure chamber 45. Under the dual effects of the high pressure in the valve oil chamber and the spring force of the return spring, the valve 4 is sealed with the bushing end face, and the entire oil leakage circuit is in a closed state. The main and auxiliary oil circuits do not interfere with each other and operate independently, ensuring the normal oil supply of each oil circuit of the engine.

[0062] When the engine stops, the electromagnetic drive component 8 is powered on and actuated, and the push rod 7 drives the valve 4 to move upward. At this time, the reference oil pressure chamber 45 is connected to the main fuel inlet space 26, and the reference oil pressure chamber 45 is also connected to the lower space 29 of the bushing 2 and the fuel discharge space 27. The fuel in the main oil circuit of the engine and the auxiliary oil circuit of the engine is discharged from the fuel discharge channel 13 to the engine oil discharge circuit or the residual oil collection device through the main fuel circuit channel 12 and the auxiliary fuel circuit channel 11 of the upper shell 1, and then the engine stops and the main and auxiliary oil circuits of the engine are discharged at the same time; when the engine fuel pump stops, the electromagnetic drive component 8 is powered off, and the valve 4 automatically resets and closes under the action of the reset spring 5. The main and auxiliary oil circuits stop draining oil and are resealed.

[0063] According to the fuel leakage control device of a multi-oil-circuit gas turbine or aircraft engine of the present invention, when more oil circuits need to be drained at the same time, multiple groups of through holes can be provided on the bushing 2, and multiple groups of reference oil chambers can be opened at the corresponding positions of the valve 4, so that the fuel of multiple oil circuits can be drained at the same time.

[0064] Example 2

[0065] Based on the multi-oil-circuit gas turbine or aircraft engine fuel leakage control device provided in Example 1, Example 2 further provides a multi-oil-circuit gas turbine or aircraft engine fuel leakage control method in combination with the operating characteristics of the device. The control method is described below in combination with specific operating steps. Figure 7 As shown, the fuel leakage control method mainly includes the following steps:

[0066] SS1. Initialization operation of fuel supply path:

[0067] Check that the main fuel oil circuit, auxiliary fuel oil circuit and oil leakage circuit of the engine are connected with the main fuel oil circuit channel, auxiliary fuel oil circuit channel and fuel leakage channel of the upper shell respectively, and ensure the physical connection between the fuel supply path and the oil leakage path; confirm the installation status of the bushing, valve, end cover and electromagnetic drive components in the fuel leakage control device, ensure that the valve is in the initial sealing position of the return spring, the main fuel inlet space, auxiliary fuel inlet space and fuel leakage space are all in a sealed state, and the fuel supply path maintains normal operation;

[0068] SS2. Fuel supply control under normal engine operation:

[0069] When the engine is in normal operation, the electromagnetic drive component is powered off, and the return spring makes the conical boss of the valve fit with the conical sealing structure of the inner wall of the bushing; the main fuel oil passage is disconnected from the fuel discharge passage, the auxiliary fuel oil passage is disconnected from the fuel discharge passage, the main fuel through hole is connected to the main fuel inlet space, the auxiliary fuel through hole is connected to the auxiliary fuel inlet space, and the respective fuel supply paths are isolated by the sealing structure of the valve and the bushing; the reference oil pressure chamber and the oil discharge chamber are separated by the oil drain port, and the fuel is supplied to the engine through the main fuel oil passage and the auxiliary fuel oil passage, and the oil drain passage is in a closed state;

[0070] SS3. Receiving and controlling the engine stop signal:

[0071] When receiving the engine stop signal, the control system sends a power-on command to the electromagnetic drive component, controls the coil in the electromagnetic drive component to be energized, and generates an axial driving force; at this time, the moving iron core drives the push rod to move upward in the axial direction under the action of the electromagnetic force, overcomes the elastic force of the return spring, and pushes the valve to move upward in the axial direction, thereby releasing the sealing fit between the conical boss at the bottom of the valve and the conical surface of the inner wall of the bushing;

[0072] SS4. The drain passages of the main fuel line and the auxiliary fuel line are open:

[0073] As the valve moves upward, the conical boss at the bottom of the valve is separated from the conical structure of the inner wall of the bushing, the reference oil pressure chamber is gradually connected with the oil drain chamber, the main fuel inlet space is connected with the fuel drain space through the reference oil pressure chamber and the oil drain chamber, and at the same time, the auxiliary fuel inlet space is connected with the fuel drain space through the reference oil pressure chamber and the oil drain chamber, so that the main fuel inlet space, the auxiliary fuel inlet space, the reference oil pressure chamber, the oil drain chamber and the fuel drain space are completely connected, and the main fuel oil circuit and the auxiliary fuel oil circuit are synchronously drained, and the fuel is discharged through the fuel drain passage;

[0074] SS5. Dynamic monitoring of fuel leakage status:

[0075] During the fuel leakage process after the engine stops, the control system monitors the leakage status of the main fuel oil circuit and the auxiliary fuel oil circuit in real time to ensure that the leakage path is unobstructed; when the pressure drops to the preset threshold, it is determined that the leakage process is nearly completed; at the same time, the current value of the electromagnetic drive component is monitored to ensure that it works within the normal range; if the flow of the fuel leakage path is detected to be abnormal or blocked, the control system sends an alarm signal through the fault diagnosis module and automatically controls the electromagnetic drive component to enter a forced power-off state;

[0076] SS6. Reset operation after fuel drain is completed:

[0077] When the fuel drain is completed and the control system confirms that there is no residual fuel in the drain path, the power supply to the electromagnetic drive component is stopped. After the electromagnetic drive component is powered off, the moving iron core is reset under the action of the reset spring, the push rod returns to its position and pushes the valve downward until the conical boss at the bottom of the valve is tightly fitted with the conical structure of the inner wall of the bushing again, and the seal between the reference oil pressure chamber and the drain oil chamber is restored; the main fuel oil circuit, the auxiliary fuel oil circuit and the fuel drain path are disconnected, and the fuel supply path is restored to a sealed state;

[0078] SS7. Sealing performance test after system reset:

[0079] After the fuel drain operation is completed, the system tests the sealing performance of the fuel supply path to ensure that the main fuel circuit and the auxiliary fuel circuit are in good sealing condition; after the test is qualified, it is confirmed that the fuel drain control device has returned to the initial operating state and can be put into engine operation again.

[0080] In summary, the fuel leakage control method for a multi-oil-circuit gas turbine or aircraft engine provided in this embodiment 2 realizes precise control and sequential discharge of multiple fuel supply paths, can efficiently and safely discharge the residual fuel after the engine is shut down, effectively prevents carbon deposits and leakage, improves the reliability and safety of the fuel system, and can be flexibly adjusted according to the engine operating conditions and the instructions of the control system to meet the efficient oil leakage requirements under complex operating conditions.

[0081] Through the detailed description of the above specific implementation methods, the multi-oil-circuit gas turbine or aircraft engine fuel leakage control device and control method of the present invention fully demonstrate its significant advantages in structural optimization, function realization and operational reliability. Through precise design and efficient control strategy, the present invention realizes the independent operation of the fuel supply path and the fast, safe and reliable leakage in the parking state, which has a wide range of engineering application value and innovative significance. The embodiments in this specification are only to further illustrate the preferred implementation mode of the technical solution of the present invention, and do not constitute a limitation on the scope of protection of the present invention.

Claims

1. A fuel leakage control device for a multi-oil gas turbine or aircraft engine, comprising an upper housing, an end cover, a bushing, a valve, a push rod and an electromagnetic drive component, characterized in that: The upper shell is fixedly mounted on a multi-oil-path gas turbine or an aircraft engine, and an inner cavity is formed inside thereof, which is axially extending, has a closed top, and is open at the bottom. An auxiliary fuel oil path is arranged on the top, and a main fuel oil path and a fuel discharge channel are arranged on the side wall. The main fuel oil path is arranged near the middle of the upper shell, and the fuel discharge channel is arranged near the bottom of the upper shell. The bushing is a hollow cylindrical structure with openings at both ends, coaxially arranged in the inner cavity of the upper shell body, with an axial gap between the top and the top wall of the inner cavity of the upper shell body, and a radial gap between the outer wall and the side wall of the inner cavity of the upper shell body, and the top, the lower middle position, and the bottom of the outer wall are respectively provided with the first and second annular step portions and the external threaded portion, the main fuel inlet space is formed between the first and second annular step portions and the side wall of the inner cavity of the upper shell body, and the fuel discharge space is formed between the second annular step portion, the external threaded portion and the side wall of the inner cavity of the upper shell body, and the bushing is fixedly connected to the top of the electromagnetic drive component through the external threaded portion; the outer wall is also provided with a main fuel through hole connecting the inner cavity of the bushing with the main fuel inlet space, and a fuel discharge through hole connecting the inner cavity of the bushing with the fuel discharge space; the inner wall is provided with a conical surface structure at the lower middle position, and the inner wall conical surface structure divides the inner cavity of the bushing into an upper space and a lower space in the axial direction, and the lower space is formed as an oil discharge cavity; The end cover is fixed to the top of the bushing, and an auxiliary fuel inlet space is formed between the top of the end cover and the top wall of the inner cavity of the upper shell. An auxiliary fuel through hole connecting the auxiliary fuel inlet space and the inner cavity of the bushing is provided in the center, and a stepped groove is provided at the bottom; The valve is a cylindrical structure with an opening at the top and a closed bottom, which is coaxially arranged in the upper space of the inner cavity of the bushing, and includes a valve main body and a diameter-reducing part, wherein: the outer wall diameter of the valve main body is adapted to the inner wall diameter of the bushing, and a return spring is provided in the inner cavity of the valve, the top of the return spring abuts against the stepped groove of the end cover, and the bottom pushes the valve to reset; a reference oil pressure cavity is formed between the outer wall of the diameter-reducing part and the inner wall of the bushing, and a secondary oil circuit oil drain port connecting the inner cavity of the valve and the reference oil pressure cavity is provided on the outer wall, and a conical boss structure is formed at the bottom, and is adapted to the conical surface of the inner wall of the bushing to form a conical sealing fit; The electromagnetic drive component is arranged at the bottom of the upper shell, the top of which is processed into a bushing installation groove with a flange flange, and the bottom is designed as an electromagnetic drive assembly. The bottom wall of the bushing installation groove is provided with a push rod through hole for allowing the push rod to pass through, and the end face is sealed with the bottom of the upper shell through the flange flange; The push rod is an axially extending rod-shaped structure, the bottom of which is fixed to the moving iron core of the electromagnetic drive component, and the top of which is pressed against the conical boss at the bottom of the valve. When the electromagnetic drive component is energized, the driving force generated by the moving iron core is transmitted axially along the push rod, pushing the valve to move upward to open the oil drain channel. In addition, the axial setting position of the secondary oil circuit oil drain port must ensure that the valve inner cavity, the reference oil pressure cavity and the oil drain cavity can be connected simultaneously during the upward movement of the valve, and the main fuel through hole is completely isolated from the reference oil pressure cavity when the valve is reset to the sealing position.

2. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: In the upper shell, the auxiliary fuel oil circuit channel extends axially to achieve communication between the auxiliary fuel inlet space in the inner cavity of the upper shell and the auxiliary fuel oil circuit of the engine; the main fuel oil circuit channel extends radially to achieve communication between the main fuel inlet space in the inner cavity of the upper shell and the main fuel oil circuit of the engine; the fuel discharge channel extends radially to achieve communication between the fuel discharge space in the inner cavity of the upper shell and the engine oil discharge channel.

3. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: The first and second annular step portions of the bushing are both provided with annular sealing ring grooves in which sealing rings are installed. Sealing gaskets are provided between the external threaded portion at the bottom of the bushing and the bushing installation groove of the electromagnetic drive component, between the end cover and the top of the bushing, and between the conical surface of the inner wall of the bushing and the conical boss at the bottom of the valve.

4. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: In the bushing, the axial distances between the first annular step portion and the second annular step portion and between the second annular step portion and the external threaded portion are optimized according to the engine fuel flow requirements to ensure that the main fuel inlet space and the fuel discharge space maintain stable flow distribution under high-pressure fuel discharge conditions and reduce flow noise and pulsation that may be generated during the discharge process.

5. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: In the bushing, the axial setting position of the inner wall conical surface structure is equivalent to the second annular step portion, and a chamfer design with arc transition is adopted. The surface roughness of the conical surface sealing fitting is processed to Ra≤0.4 μm, and the contact area of ​​the conical surface sealing fitting is optimized.

6. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: The main fuel through hole and the fuel discharge through hole arranged on the outer wall of the bushing extend radially, are multiple in number and are evenly distributed circumferentially, and the axial position of the main fuel through hole is lower than the main fuel oil passage of the upper shell and is located between the first annular step portion and the second annular step portion, and the axial position of the fuel discharge through hole is lower than the fuel discharge passage of the upper shell and is located between the second annular step portion and the external threaded portion.

7. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: An adjustment gasket is provided in the stepped groove of the end cover, and the adjustment gasket is connected to the top end surface of the reset spring. The free length, number of turns and stiffness coefficient of the reset spring are designed to match the mass of the valve and the maximum output thrust of the electromagnetic drive component.

8. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: In the valve, the transition portion between the valve body and the reduced diameter portion in the valve inner cavity is formed as an annular step surface for limiting the lower end position of the reset spring, and the axial distance between the annular step surface and the end cover step groove is optimized so that the reset spring maintains a stable compression state when the electromagnetic drive component is powered off.

9. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: The auxiliary oil channel oil leakage port arranged on the outer wall of the diameter reduction portion extends radially and is evenly distributed in the circumferential direction to form a plurality of auxiliary oil channel oil leakage ports, so as to ensure that the auxiliary oil channel has a sufficient flow area during oil leakage.

10. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: The electromagnetic drive assembly includes a coil, a static iron core and a moving iron core. The stroke of the moving iron core is designed to be no less than 3 mm. The design parameters of the coil need to ensure that sufficient electromagnetic driving force can be generated under a 24V operating voltage to overcome the effects of the reset spring force and the oil pressure.

11. The fuel leakage control device for a multi-oil gas turbine or aircraft engine according to claim 1, characterized in that: The push rod is made of non-magnetic material, and is connected to the moving iron core by threaded fixing. The contact surface between the top and the bottom of the valve is surface hardened, and the axial length of the push rod is optimized according to the stroke requirements of the electromagnetic drive component.

12. A fuel leakage control method for a multi-oil-circuit gas turbine or aircraft engine, based on the fuel leakage control device for a multi-oil-circuit gas turbine or aircraft engine according to any one of claims 1 to 11, characterized in that: The control method comprises at least the following steps when implemented: SS1. Check that the main fuel oil circuit, auxiliary fuel oil circuit and oil drain circuit of the engine are connected with the main fuel oil circuit channel, auxiliary fuel oil circuit channel and fuel drain circuit of the upper shell respectively, and ensure the physical connection between the fuel supply path and the oil drain path; confirm the installation status of the bushing, valve, end cover and electromagnetic drive components, and ensure that the valve is in the initial sealing position of the return spring; SS2. When the engine is in normal operation, the electromagnetic drive component is powered off, and the return spring makes the conical boss of the valve fit with the conical sealing structure of the inner wall of the bushing; the main fuel oil passage is disconnected from the fuel discharge passage, the auxiliary fuel oil passage is disconnected from the fuel discharge passage, the main fuel through hole is connected to the main fuel inlet space, and the auxiliary fuel through hole is connected to the auxiliary fuel inlet space, and the respective fuel supply paths are isolated by the sealing structure of the valve and the bushing; the reference oil pressure chamber and the oil discharge chamber are separated by the oil drain port, and the fuel is supplied to the engine through the main fuel oil passage and the auxiliary fuel oil passage, and the oil drain passage is in a closed state; SS3. When receiving the engine stop signal, the control system sends a power-on command to the electromagnetic drive component, controls the coil in the electromagnetic drive component to be energized, and the moving iron core drives the push rod to move axially upward under the action of the electromagnetic force, overcomes the elastic force of the return spring, and pushes the valve to move axially upward, releasing the sealing fit between the conical boss at the bottom of the valve and the conical surface of the inner wall of the bushing; SS4. As the valve moves upward, the conical boss at the bottom of the valve separates from the conical structure of the inner wall of the bushing, the reference oil pressure chamber and the oil drain chamber are gradually connected, the main fuel inlet space and the fuel drain space are connected through the reference oil pressure chamber and the oil drain chamber, and the auxiliary fuel inlet space and the fuel drain space are connected through the reference oil pressure chamber and the oil drain chamber, so that the main fuel inlet space, the auxiliary fuel inlet space, the reference oil pressure chamber, the oil drain chamber and the fuel drain space are completely connected; SS5. During the fuel leakage process after the engine stops, the control system monitors the leakage status of the main fuel circuit and the auxiliary fuel circuit in real time to ensure that the leakage path is unobstructed; when the pressure drops to the preset threshold, it is determined that the leakage process is nearly completed; if the flow of the fuel leakage path is abnormal or blocked, the control system sends an alarm signal through the fault diagnosis module and controls the electromagnetic drive component to enter the forced power-off state; SS6. When the fuel leakage is completed and the control system confirms that there is no residual fuel in the leakage path, the power supply to the electromagnetic drive component is stopped, the moving iron core is reset under the action of the reset spring, the push rod returns to its position and pushes the valve downward until the conical boss at the bottom of the valve fits tightly with the conical structure of the inner wall of the bushing again; the main fuel oil circuit, the auxiliary fuel oil circuit and the fuel leakage path are disconnected, and the fuel supply path is restored to a sealed state; SS7. After the fuel drain operation is completed, the system will test the sealing performance of the fuel supply path to ensure that the main fuel circuit and the auxiliary fuel circuit are in good sealing condition; after passing the test, it will be confirmed that the fuel drain control device has returned to its initial operating state and can be put back into engine operation.

13. A multi-oil gas turbine or aircraft engine, characterized in that: A fuel leakage control device for a multi-oil-circuit gas turbine or aircraft engine comprising the device described in any one of claims 1 to 11.

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