Pressure smooth opening electromagnetic device of multi-oil-way multi-electric aero-engine fuel system

Abstract

The invention discloses a pressure smooth opening electromagnetic device of a multi-oil-way and multi-electricity aero-engine fuel system, which is used for realizing stable switching among multiple oil ways in the fuel system and accurate pressure control and effectively reducing electromagnetic force requirements. The device comprises a valve body base, a main valve assembly, an auxiliary valve assembly and an electromagnetic actuation pilot valve assembly, a main valve is of a conical surface structure, it is ensured that good sealing is formed between the main valve and a valve port, smooth flowing of fluid is achieved through a small runner hole, meanwhile, the structure of the main valve is optimally designed in combination with related fluid mechanics theories, and the valve body structure is optimized. And when the main valve actuates, the electromagnetic force demand is effectively reduced. In addition, the auxiliary valve is designed to be a one-way valve, the unidirectionality of fuel oil flowing and the stability of system pressure during multi-oil-way switching are guaranteed, and the reliability of the system is improved. According to the device, through cooperative work of all the assemblies, stable switching among multiple oil ways and accurate pressure control are achieved, and the stability and reliability of an aero-engine multi-oil-way fuel system are remarkably improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft engine fuel system control, and relates to pressure regulation and solenoid valve design of a multi-oil circuit fuel system. Specifically, the present invention is a pressure smooth opening electromagnetic device suitable for a multi-oil circuit multi-electric aircraft engine fuel system, which is used to achieve smooth transition and precise control of the fuel system when switching between different oil circuits, and reduce the required electromagnetic force. Background Art

[0002] With the continuous development of aircraft engine technology, more-electric aircraft engines have gradually become one of the important research directions in the aviation field. Traditional aircraft engines usually rely on fuel pumps and hydraulic actuators driven by accessory cases to achieve fuel supply and execution control, while more-electric aircraft engines use electric fuel pumps and electric actuators to replace the traditional fuel pumps and hydraulic actuators driven by accessory cases. This technological transformation not only improves the electrification level of the system, but also improves the control accuracy and response speed of the fuel system, which helps to optimize the overall performance of the engine.

[0003] In multi-oil and multi-electric aircraft engines, such as Figure 1 As shown in the figure, the fuel system is usually composed of multiple parallel oil circuits. In order to ensure the stable operation of the engine under different working conditions, the smooth and continuous supply of the priority oil circuit (1) and the main oil circuit (2) is extremely important. This process plays a key role in the ignition, acceleration and stable operation of the aircraft engine. Since the traditional fuel regulator is cancelled, the fuel system needs to set a solenoid valve in the 2-way oil circuit to control the opening and closing of the oil circuit. The introduction of the solenoid valve provides the possibility for the automatic control and response speed improvement of the fuel system. However, the traditional solenoid valve has only two states of open and closed under power-on or power-off conditions, that is, it is completely closed when powered on and completely open when powered off. Since the fuel system 1 and 2 of the multi-electric multi-oil circuit engine are connected in parallel, the oil pressure of 1 drops sharply at the moment when the 2-way oil circuit is opened, resulting in a momentary shortage of the oil supply flow of 1. This sudden change in oil pressure and flow can easily cause engine ignition failure, greatly affecting the starting performance and stable operation of the engine.

[0004] In addition, the oil supply characteristics of the engine main oil circuit (2-way) also bring challenges to the design of the solenoid valve. Due to the large oil supply flow rate and high system pressure of the engine main oil circuit (2-way), the solenoid valve core is subjected to a large hydraulic pressure, resulting in a large electromagnetic force required when the solenoid valve core is actuated (opened / closed), which further leads to a large electromagnetic structure of the solenoid valve, which occupies more installation space and weight of the aircraft engine.

[0005] Traditional solenoid valves have certain limitations in the combination of hydraulic drive and electromagnetic control. First, because the solenoid valve must have sufficient electromagnetic force to overcome high hydraulic pressure, the volume and power requirements of its electromagnetic components increase. This not only places higher demands on the system power supply, but also increases the maintenance cost and complexity of aircraft engines. Secondly, the increased size of the solenoid valve makes it difficult to install flexibly, especially in the space-constrained internal structure of aircraft engines, which is more likely to cause installation difficulties and space waste. Furthermore, when the engine needs to frequently switch oil circuits, the response speed and control accuracy of traditional solenoid valves may be insufficient, resulting in limited timeliness and stability of fuel supply.

[0006] In summary, as aircraft engines continue to develop towards high efficiency, light weight and high reliability, the design of the fuel supply system of multi-electric and multi-oil aircraft engines needs to be further optimized. In order to solve the problems of oil supply pressure fluctuation, large valve core force, and bulky electromagnetic structure of traditional solenoid valves in multi-oil systems, it is a technical problem to be urgently solved in the current field of multi-electric aircraft engine technology to develop an electromagnetic device that can realize smooth opening of the fuel system pressure of multi-oil aircraft engines, with a compact structure and low electromagnetic force requirements. Summary of the invention

[0007] (I) Purpose of the invention

[0008] In view of the defects and shortcomings of the existing multi-oil-circuit and multi-electric aircraft engine fuel system, such as unstable fuel supply pressure, large valve core liquid pressure, large electromagnetic force demand, and bulky electromagnetic structure, in order to solve at least one of the above-mentioned and other technical problems in the prior art, the present invention aims to provide a pressure-smooth opening electromagnetic device suitable for a multi-oil-circuit and multi-electric aircraft engine fuel system. In combination with the relevant theories of fluid mechanics, the solenoid valve structure is optimized and designed, and a staged control method of the pilot valve, the main valve and the auxiliary valve is adopted to reasonably distribute the fluid pressure, and the Bernoulli equation is used to accurately calculate the fluid pressure in the process of valve opening and closing, so as to reduce the electromagnetic force while meeting the smooth opening of the multi-oil-circuit system pressure, thereby reducing the demand for electromagnetic force, reducing the volume and weight of the electromagnetic structure, and improving the installation adaptability of the device and the operating stability of the aircraft engine system.

[0009] (II) Technical solution

[0010] In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions:

[0011] A pressure smooth opening electromagnetic device for a multi-oil circuit multi-electric aircraft engine fuel system is used to achieve smooth switching and pressure control between different oil circuits in the fuel system of a multi-oil circuit multi-electric aircraft engine, avoid oil pressure fluctuation and unstable fuel supply during the switching process and reduce the required electromagnetic force to ensure the stable operation of the aircraft engine. The device comprises at least a valve body base, a main valve assembly, a secondary valve assembly and an electromagnetically actuated pilot valve assembly. Specifically:

[0012] The valve body base is provided with an oil passage, a main valve mounting valve port and a secondary valve mounting valve port, wherein: the oil passage is provided with a partition plate which divides it into an upstream oil inlet section and a downstream oil outlet section; the main valve mounting valve port is arranged at the top of the valve body base, and is a cylindrical structure extending in the height direction as a whole, and at least one main oil outlet hole communicating with the upstream oil inlet section and one main oil return hole communicating with the downstream oil outlet section are provided at the bottom thereof; the secondary valve mounting valve port is a blind hole channel structure extending in the horizontal direction with one end closed and the other end open, and at least one secondary oil outlet hole communicating with the upstream oil inlet section and one secondary oil return hole communicating with the downstream oil outlet section are provided on the side wall thereof;

[0013] The main valve assembly at least includes a main valve and a main valve return spring, the main valve is arranged in the main valve mounting valve port, and is a plate-like structural member with an annular skirt as a whole, the annular skirt and the circumferential side wall of the main valve mounting valve port form a clearance fit and its top surface is higher than the top surface of the plate-like structural member; the bottom surface center of the plate-like structural member protrudes downward to form a conical structure facing the main oil return hole, a downwardly concave sealing gasket accommodating groove is provided at the center of the top surface, a central oil return hole penetrating downwardly through the conical structure is provided at the bottom of the groove, and a plurality of oil holes penetrating the top and bottom surfaces thereof and distributed along the circumferential direction are also provided on the plate-like structural member; the main valve return spring is installed between the plate-like structural member of the main valve and the bottom wall of the main valve mounting valve port;

[0014] The auxiliary valve assembly is formed as a one-way valve as a whole, and at least comprises a valve seat, a steel ball, a ball holder, an auxiliary valve return spring and a one-way valve seat, which are arranged axially along the blind hole channel of the auxiliary valve mounting valve port, wherein: the valve seat is arranged at an axial position corresponding to the partition plate, and is provided with a central through hole extending axially along the channel, and the channel space in front of it is connected with the auxiliary oil outlet hole; the steel ball, the ball holder and the auxiliary valve return spring are arranged in the inner cavity of the one-way valve seat in sequence; the top of the one-way valve seat is against the rear end surface of the valve seat, and there is a radial gap between its front end side wall and the inner wall of the channel and is connected with the auxiliary oil return hole, and a plurality of oil holes are provided on its front end side wall, and its rear end side wall is arranged on the auxiliary valve mounting valve port in a sealed and fixed manner;

[0015] The electromagnetically actuated pilot valve assembly is installed on the top of the valve body base, and includes at least a moving iron core driven by an electromagnetic coil and a spring-reset pilot valve, wherein: the pilot valve includes at least a valve rod and a sealing gasket, the upper end of the valve rod is fixedly connected to the end of the moving iron core, and the sealing gasket is fixedly arranged at the lower end of the valve rod, and is used to cooperate with the sealing gasket accommodating groove at the top of the main valve to form a seal; the moving iron core drives the valve rod to move axially through the energization operation of the electromagnetic coil, and the reset spring pushes the moving iron core and the valve rod back to the initial position when the electromagnetic coil is powered off.

[0016] (III) Technical Effect

[0017] Compared with the prior art, the pressure-smooth opening electromagnetic device of the multi-oil-circuit aircraft engine fuel system of the present invention has the following beneficial and significant technical effects:

[0018] (1) The present invention realizes the smooth switching and pressure control between different oil circuits in the multi-oil circuit aviation engine fuel system by designing the coordinated working mechanism of the main valve assembly, the auxiliary valve assembly and the electromagnetically actuated pilot valve assembly, and effectively avoids the problem of fuel pressure fluctuation during the oil circuit switching process. The traditional system is prone to sudden oil pressure drop or instantaneous fluctuation when switching the oil circuit. The present invention realizes a smooth transition between the upstream and downstream oil circuits through a reasonable valve structure and control method, so that the fuel flow and pressure can remain stable during the switching process, which significantly improves the engine's ignition success rate and stability.

[0019] (2) The present invention reduces the need for high-power electromagnetic coils, reduces the required electromagnetic force, and reduces the overall volume of the electromagnetic valve and the power consumption during electromagnetic actuation by adopting a composite control structure of a pilot valve and a main valve. In addition, the precise matching design between the moving iron core and the valve rod of the present invention and the shock-absorbing measures make the electromagnetic actuation process smoother and more efficient, extending the service life of the electromagnetic valve assembly. At the same time, by rationally designing the fluid channel and valve structure, the influence of the hydraulic pressure on the actuation of the electromagnetic valve is reduced, thereby achieving a lighter electromagnetic structure that meets the strict requirements of aircraft engines on weight and volume.

[0020] (3) The present invention adopts the principles of fluid dynamics and improves the fuel flow efficiency by designing a conical structure and a small flow channel hole. This design allows the fluid to pass through at a higher speed when the main valve is opened, thereby reducing the flow resistance and improving the fuel supply efficiency. This technical effect not only improves the engine performance, but also reduces fuel consumption, helping to achieve more economical flight. In addition, the one-way valve design adopted by the present invention ensures that the auxiliary oil circuit can respond quickly and provide stable fuel supply when needed. The auxiliary valve assembly achieves one-way flow through a steel ball and spring structure, effectively preventing reverse flow. This design enhances the reliability of the system and ensures that a good fuel supply state can be maintained under complex working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 Schematic diagram of a multi-oil-circuit fuel system according to an embodiment of the present invention.

[0023] Figure 2 It is a schematic cross-sectional structure diagram of a pressure smooth opening electromagnetic device of a multi-oil circuit multi-electric aircraft engine fuel system according to an embodiment of the present invention, in which the pilot valve and the main valve are both in an open state.

[0024] Figure 3 It is a schematic diagram of the cross-sectional structure of the valve body base in an embodiment of the present invention.

[0025] Figure 4 1 and 2 are a top view (A) and a cross-sectional view (B) of the main valve in an embodiment of the present invention.

[0026] Figure 5 Schematic diagram of the structure of the valve seat in the embodiment of the present invention, wherein (A) is an axonometric view, (B) is a right side view, and (C) is a sectional view.

[0027] Figure 6 Schematic diagram of the structure of the one-way valve seat in the embodiment of the present invention, wherein (A) is an isometric view, (B) is a right side view, and (C) is a sectional view.

[0028] Figure 7 1 is a right side view (A) and a cross-sectional view (B) of the ball holder in an embodiment of the present invention.

[0029] Figure 8 It is a schematic structural diagram of an electromagnetically actuated pilot valve assembly in an embodiment of the present invention.

[0030] Fig. 9 It is a schematic diagram of the state in which the pilot valve is closed and the main valve is opened in the electromagnetic device of the present invention.

[0031] Fig.10 It is a schematic diagram showing that the pilot valve and the main valve in the electromagnetic device of the present invention are both in a closed state.

[0032] Description of reference numerals:

[0033] 1-upper shell, 2-top cover, 3-electromagnetic coil, 4-fastening screw, 5-coil mounting frame, 51-cylindrical base, 52-bracket column, 53-conical groove, 6-valve body base, 61-oil flow channel, 611-upstream oil inlet section, 612-downstream oil outlet section, 62-main valve installation valve port, 621-main oil outlet hole, 622-main oil return hole, 63-auxiliary valve installation valve port, 631-auxiliary oil outlet hole, 632-auxiliary oil return hole, 64-partition, 7-one-way valve seat, 71-first cavity, 72-second cavity, 73-first oil through hole, 74-second oil through hole, 75-annular Sealing groove, 8-sealing ring, 9-auxiliary valve return spring, 10-ball holder, 101-conical groove, 102-spring seat, 11-sealing ring, 12-valve seat, 121-center through hole, 122-annular sealing groove, 13-steel ball, 14-main valve return spring, 15-main valve, 151-plate structure, 152-annular skirt, 153-conical surface structure, 154-sealing gasket accommodating groove, 155-center oil return hole, 156-oil hole, 16-sealing ring, 17-sealing gasket, 18-valve rod, 19-core return spring, 20-moving iron core, 21-sealing ring. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical scheme and advantages of the implementation of the present invention clearer, the technical scheme in the embodiment of the present invention will be described in more detail below in conjunction with the drawings in the embodiment of the present invention. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain the present invention, and should not be understood as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0035] The present invention aims to provide a pressure-smooth opening electromagnetic device suitable for a multi-oil-circuit and multi-electric aircraft engine fuel system. The present invention combines relevant theories of fluid mechanics, optimizes the design of the electromagnetic valve structure, adopts a staged control method of the pilot valve, the main valve and the auxiliary valve, reasonably distributes the fluid pressure, and uses the Bernoulli equation to calculate the fluid pressure in the valve opening and closing process. The electromagnetic force is reduced while the pressure of the multi-oil-circuit system is smoothly opened, thereby reducing the demand for electromagnetic force, reducing the volume and weight of the electromagnetic structure, and improving the installation adaptability of the device and the operating stability of the aircraft engine system.

[0036] As a specific example, Figure 2 As shown, the pressure smooth opening electromagnetic device of the fuel system of a multi-oil circuit and multi-electric aircraft engine of the embodiment of the present invention includes an upper shell body 1, a top cover 2, an electromagnetic coil 3, a fastening screw 4, a coil mounting frame 5, a valve body base 6, a one-way valve seat 7, a sealing ring 8, a secondary valve return spring 9, a ball holder 10, a sealing ring 11, a valve seat 12, a steel ball 13, a main valve return spring 14, a main valve 15, a sealing ring 16, a sealing gasket 17, a valve rod 18, an iron core return spring 19, a moving iron core 20, a sealing ring 21 and other structural components.

[0037] In the embodiment of the present invention, the main structure of the valve body base 6 is as follows Figure 3 As shown, an oil passage 61, a main valve mounting valve port 62 and an auxiliary valve mounting valve port 63 are provided thereon, wherein: a partition 64 is provided in the oil passage 61 to separate it into an upstream oil inlet section 611 and a downstream oil outlet section 612; the main valve mounting valve port 62 is arranged on the top of the valve body base 6, and is a cylindrical structure extending in the height direction as a whole, and at least one main oil outlet hole 621 communicating with the upstream oil inlet section 611 and a main oil return hole 622 communicating with the downstream oil outlet section 612 are provided at its bottom; the auxiliary valve mounting valve port 63 is a blind hole channel structure extending in the horizontal direction with one end closed and the other end open, and at least one auxiliary oil outlet hole 631 communicating with the upstream oil inlet section 611 and one auxiliary oil return hole 632 communicating with the downstream oil outlet section 612 are provided on its side wall.

[0038] Preferably, the oil flow channel 61 extends in the horizontal direction and passes through the main body of the valve body base 6, with one end forming an oil inlet end and the other end forming an oil outlet end. The oil inlet end is used to connect to an upstream fuel pump or fuel regulator through a pipeline, and the oil outlet end is used to connect to a downstream combustion chamber or fuel nozzle through a pipeline. The inner wall of the oil flow channel 61 is precision machined and polished to reduce friction resistance during the flow of fuel, and its diameter is adjusted according to the fuel flow demand to ensure that a stable fuel pressure is maintained under different working conditions.

[0039] In the embodiment of the present invention, the main valve return spring 14, the main valve 15 and other components constitute the main valve structure. Figure 2, 4 As shown. The main valve 15 is arranged in the main valve installation valve port 62, and is a plate-like structure 151 with an annular skirt 152 as a whole. The annular skirt 152 forms a clearance fit with the circumferential side wall of the main valve installation valve port 62, and its top surface is higher than the top surface of the plate-like structure 151; the center of the bottom surface of the plate-like structure 151 protrudes downward to form a conical structure 153 facing the main oil return hole 622, and a sealing gasket accommodating groove 154 is provided at the center of the top surface, and a central oil return hole 155 penetrating downward through the conical structure 153 is provided at the bottom of the groove, and a plurality of oil holes 156 penetrating through the top and bottom surfaces and distributed along the circumferential direction are also provided on the plate-like structure 151; the main valve reset spring 14 is installed between the plate-like structure 151 of the main valve 15 and the bottom wall of the main valve installation valve port 62.

[0040] Preferably, the main valve return spring 14 adopts a variable cross-section design, in which the bottom coil diameter is larger than the top coil diameter and the overall structure is conical, so as to reduce the overall height of the spring while ensuring sufficient return force, reduce the axial size of the device, and provide nonlinear elastic characteristics. A larger return force is provided at the initial opening of the main valve 15, and the return force is reduced when it is close to the fully open position, which helps to achieve a smoother oil circuit switching process.

[0041] In the embodiment of the present invention, the one-way valve seat 7, the sealing ring 8, the auxiliary valve return spring 9, the ball holder 10, the sealing ring 11, the valve seat 12, the steel ball 13 and other components constitute the auxiliary valve structure. Figure 2 , 5 As shown in Figures 1 to 7, the valve seat 12 is arranged at an axial position corresponding to the partition 64, and is provided with a central through hole 121 extending along the axial direction of the channel, and the channel space in front of it is connected with the auxiliary oil outlet hole 631; the steel ball 13, the ball holder 10, and the auxiliary valve return spring 9 are arranged in the inner cavity 71, 72 of the one-way valve seat 7 in sequence; the top of the one-way valve seat 7 is against the rear end surface of the valve seat 12, and there is a radial gap between its front end side wall and the inner wall of the channel and is connected with the auxiliary oil return hole 632, and a plurality of oil holes 73, 74 are provided on its front end side wall, and its rear end side wall is arranged on the auxiliary valve mounting valve port 63 in a sealed and fixed manner.

[0042] Preferably, at least one annular sealing groove 75 is provided on the outer circumferential surface of the one-way valve seat 7, and a sealing ring 8 is installed in the annular sealing groove 75 to achieve sealing between the one-way valve seat 7 and the blind hole channel of the auxiliary valve mounting valve port 63; in addition, an external thread is also provided on the outer circumferential surface of the one-way valve seat 7, and an internal thread is provided on the inner wall of the blind hole channel of the auxiliary valve mounting valve port 63, and the one-way valve seat 7 and the blind hole channel of the auxiliary valve mounting valve port 63 are fixedly connected by threads. In addition, the inner cavity of the one-way valve seat 7 is formed into a stepped structure, including at least a first cavity 71 with a larger inner diameter arranged near its top and a second cavity 72 with a smaller inner diameter arranged near its end, wherein the ball holder 10 is arranged in the first cavity 71 in a manner that it can slide left and right in the axial direction, and its front end face is processed to form a conical groove 101 to support the steel ball 13 to ensure that the steel ball 13 remains stably positioned when the oil pressure changes, and its rear end face is processed to form a spring seat 102; the main body of the auxiliary valve reset spring 9 is arranged in the second cavity 72, its top is against the rear end face of the ball holder 10, and the end is against the bottom wall of the second cavity 72 to provide a reset force when the steel ball moves under pressure. Further preferably, a first oil hole 73 is provided on the front end side wall of the first cavity 71 of the one-way valve seat 7, for guiding the fuel into the first cavity 71 during the movement of the ball holder 10, and a second oil hole 74 is provided on the front end side wall of the second cavity 72, for discharging the fuel when the auxiliary valve reset spring 9 is under pressure, thereby reducing the influence of back pressure on the reset action.

[0043] Preferably, at least one annular sealing groove 122 is provided on the outer peripheral surface of the valve seat 12, and a sealing ring 11 is installed in the annular sealing groove 122 to achieve sealing between the valve seat 12 and the blind hole channel of the auxiliary valve mounting valve port 63; and, the central through hole 121 of the valve seat 12 is configured as a conical expansion structure to reduce the flow resistance of the fuel when it enters the central through hole 121, and to reduce the generation of turbulence and bubbles by guiding the fuel to flow smoothly into the through hole.

[0044] In the embodiment of the present invention, the sealing gasket 17, the valve rod 18, the iron core return spring 19, and the moving iron core 20 constitute the pilot valve structure, and the top cover 2, the coil assembly 3, the coil mounting frame 5, the sealing ring 21, etc. constitute the electromagnetic actuation structure. Specifically, Figure 2 , 8 As shown, the electromagnetically actuated pilot valve assembly is installed on the top of the valve body base 6, and the pilot valve includes at least a valve rod 18 and a sealing gasket 17. The upper end of the valve rod 18 is fixedly connected to the end of the moving iron core 20, and the sealing gasket 17 is fixedly arranged at the lower end of the valve rod 18, and is used to cooperate with the sealing gasket accommodating groove 154 at the top of the main valve 15 to form a seal; the moving iron core 20 drives the valve rod 18 to move axially through the energization operation of the electromagnetic coil, and when the electromagnetic coil is de-energized, the moving iron core 20 and the valve rod 18 are pushed back to the initial position by the reset spring.

[0045] The electromagnetically actuated pilot valve assembly is also provided with an electromagnetic coil assembly, which includes at least a top cover 2, an electromagnetic coil 3 and a coil mounting frame 5, wherein: the coil mounting frame 5 includes at least a cylindrical base 51 and a bracket column 52 formed at the center of the top surface of the cylindrical base 51 and extending axially upward, the inner circumferential wall of the cylindrical base 51 is provided with an internal thread and is fixedly arranged on the outer circumferential wall of the main valve mounting valve port 62 by a threaded connection, and the inner circumferential wall of the cylindrical base 51 is provided with an annular sealing groove and a sealing ring 21 to achieve sealing between the cylindrical base 51 and the main valve mounting valve port 62; the electromagnetic coil 3 is axially sleeved and installed on the bracket column 52, and the top cover 2 is threadedly connected and fixedly arranged on the top of the bracket column 52 to achieve axial constraint on the top of the electromagnetic coil 3.

[0046] Preferably, the support column 52 of the coil mounting frame 5 is a hollow cylindrical structure with an open top as a whole, and the bottom of the cylindrical inner cavity is processed to form a conical groove 53, and the bottom wall of the conical groove 53 is provided with a valve rod through hole extending downward and penetrating the cylindrical base 51; the moving iron core 20 is accommodated in the cylindrical inner cavity in a manner that it can slide up and down in the axial direction, and a step structure for supporting the iron core return spring 19 is provided on its side wall, and the other end of the iron core return spring is against the top surface of the conical groove; and the end of the moving iron core 20 is processed to form a conical surface structure, which is compatible with the conical surface of the conical groove and an air gap is formed between the two to realize the axial movement of the moving iron core 20; a threaded connection hole is provided at the center of the conical surface structure of the moving iron core 20, and the valve rod 18 passes upward through the valve rod through hole and is threadedly fixed to the end of the moving iron core 20. In addition, the moving iron core 20 and the cylindrical inner cavity of the support column 52 of the coil mounting frame 5 are preferably clearance-fitted, with a diameter clearance range of Φ0.005mm to Φ0.015mm and a coaxial error range of Φ0.01mm to Φ0.03mm, which plays an axial centering role.

[0047] Preferably, the electromagnetic device of the present invention further comprises an upper housing 1, such as Figure 2 As shown, a through hole is provided at the lower end of the upper shell 1, and a threaded hole is provided at a corresponding position of the coil mounting frame 5. The through hole and the threaded hole are connected by fastening screws 4 to achieve fixation between the upper shell 1 and the coil mounting frame 5.

[0048] Combine the following Figure 2 , 9 10. The working principle of the pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system provided by the embodiment of the present invention is introduced as follows:

[0049] When the system needs to switch fuel or adjust pressure, the electromagnetic coil of the electromagnetically actuated pilot valve assembly is energized first, and the electromagnetic coil drives the moving iron core to move axially. The moving iron core drives the pilot valve to open or close through the valve rod. Under the action of electromagnetic force, the pilot valve controls the oil flow path of the main valve assembly, so that the main valve can be opened or closed smoothly. In this process, the pilot valve is responsible for adjusting the fuel pressure entering the main valve to ensure that the main valve will not be subjected to sudden pressure shock when it is opened, thereby maintaining the stability of the fuel system. The main valve moves under the action of pressure difference, and its annular skirt and conical surface structure accurately control the fuel flow passing through. The central oil return hole design ensures fast response and precise adjustment. The auxiliary valve assembly is a one-way valve device, which is set in the downstream part of the oil flow channel. When the system oil pressure reaches a specific value, the auxiliary valve opens to alleviate the pressure difference between the upstream and downstream, and assists the main valve assembly to achieve smooth switching. The steel ball and return spring of the auxiliary valve work together to ensure that it responds quickly and resets when the pressure changes, effectively preventing fuel backflow or uneven pressure in the system. The return spring design of the main valve and auxiliary valve ensures that the valve can quickly return to a safe position in the event of power failure or abnormal conditions to ensure system safety. Through the precise control of the main valve and the auxiliary valve, the smooth switching of the oil circuit and the smooth opening of the pressure are achieved, avoiding sudden pressure fluctuations. The overall device ensures that the fuel system maintains a smooth and rapid response and adjustment under different working conditions through the coordinated control of the main valve, pilot valve and auxiliary valve, ensuring the stability and efficiency of engine operation.

[0050] More specifically, the working principle of the electromagnetic device for smoothly opening the fuel system pressure of a multi-oil circuit and multi-electric aircraft engine according to the embodiment of the present invention can be divided into four stages, covering the entire process from engine starting to oil circuit closing. The specific process of each stage and the physical principle behind it will be described in detail below:

[0051] Phase 1: Engine start-up and initial fuel supply. In the starting and ignition phase of a multi-oil and multi-electric engine, the system first activates the 2-way solenoid valve. After the 2-way solenoid valve is energized, the electromagnetically actuated pilot valve presses the main valve 15 to form a sealing structure with the valve body base 6. At this time, the high-pressure pump starts to work, and the fuel is supplied to the combustion chamber through the 1st path. The key to this phase is to ensure that the fuel can stably enter the combustion chamber to achieve smooth ignition of the engine. By precisely controlling the opening of the solenoid valve, the system ensures a continuous and stable supply of fuel in the initial stage, effectively avoiding the oil pressure fluctuations that may occur in traditional systems when switching fuel. According to the basic principles of fluid mechanics, when the high-pressure pump is working, the fuel pressure in the system will rise rapidly, laying the foundation for the smooth progress of subsequent stages.

[0052] Phase 2: Increase in system speed and opening of the auxiliary valve. As the engine speed increases, the fuel pressure P0 of the system increases. When the pressure reaches the preset threshold, the auxiliary valve of the 2-way valve opens, allowing part of the fuel to flow out of the auxiliary valve, thereby adjusting the pressure difference inside the system. During this process, a pressure difference ΔP is formed between the upper and lower surfaces of the main valve 15. The existence of this pressure difference ensures that the fuel can flow smoothly in the system, while balancing the pressure between the upstream and downstream, thus laying the foundation for subsequent pressure regulation and valve switching. Through the reasonable opening of the auxiliary valve, the system maintains a smooth fuel flow during the increase in speed, ensuring continuous ignition and stable operation of the engine.

[0053] Stage 3: Successful ignition of the combustion chamber and opening of the main valve. When the 2-way combustion chamber nozzles are successfully connected, the 2-way solenoid valve is powered off. Under the action of the iron core reset spring, the moving iron core 20 moves upward. At this time, as the electromagnetic force is released, the pilot valve is reset, and the small flow channel in the middle of the main valve is opened, so that the pressure difference ΔP between the upper and lower surfaces of the main valve 15 is gradually reduced to 0. The elastic potential energy of the main valve reset spring 14 is released, pushing the main valve 15 to open. At this time, the main flow channel is fully opened, and the inlet and outlet pressures are basically consistent. The auxiliary valve will automatically close, completing the smooth switch from the auxiliary oil circuit to the main oil circuit. This process ensures the continuity and stability of the fuel when entering the combustion chamber, and avoids the problem of unstable fuel flow caused by sudden changes in pressure difference. The control logic of this stage coordinates the pilot valve and the large valve, so that the system can smoothly switch to the main fuel supply state after the combustion chamber is ignited.

[0054] Phase 4: Closing of the oil circuit and resealing of the main valve. When the flight mission requires closing the two oil circuits, the solenoid valve is energized again. At this time, the pilot valve moves downward to seal the small flow channel in the middle of the main valve 15, thereby sealing the flow channel of the main valve. After the pilot valve I is closed, the fluid flows through the main channel. Since the effective area of ​​the fuel flow near the valve of the main channel is distributed in an annular shape on the flow path, the fuel flow rate at the valve port increases. According to the Bernoulli principle, the pressure decreases accordingly. This pressure reduction further assists the closing of the main valve, forming a positive feedback mechanism. This design reduces the dependence on electromagnetic force, so that the system does not need to apply additional electromagnetic force during the closing process, which improves the energy efficiency of the system.

[0055] An important feature of the present invention is that it can significantly reduce the required electromagnetic force. In order to reduce the electromagnetic force, the present invention uses the Bernoulli equation principle in fluid mechanics in its design. Ignoring the viscosity loss, the flow of fuel in the fuel supply pipeline can be approximated as an ideal fluid, and the flow follows the Bernoulli equation:

[0056]

[0057] When the solenoid valve is energized, the electromagnetic force pushes the pilot valve to close. When the fuel flows out from the main channel, the annular distribution of the flow channel increases the flow velocity v2 and reduces the pressure P2. There is a large pressure difference between the upper and lower surfaces of the main valve 15. The large liquid pressure will further promote the closing of the main valve without the need for a larger electromagnetic force.

[0058] In the present invention, the entire device realizes the stable switching and pressure regulation of the fuel system in a multi-oil circuit and multi-electric aircraft engine through the coordinated control of a multi-stage valve and an electromagnetic actuator. The cooperation of the pilot valve, the main valve and the auxiliary valve ensures the smooth transition of the fuel pressure under different working conditions. In particular, through the precise control of the electromagnetically actuated pilot valve, the up and down movement of the moving iron core can quickly respond to system requirements and timely control the opening and closing of the fuel flow channel in the power-on and power-off states. In addition, the auxiliary valve assembly automatically opens when the system pressure exceeds a certain threshold, and the upstream and downstream pressure differences are balanced through the one-way valve structure, so that the system can still maintain stable operation under high pressure and high load conditions.

[0059] In addition, the invention ensures the stability of the system during operation through the precise matching between the electromagnetic coil and the moving iron core. The clearance matching between the moving iron core and the valve rod, as well as the optimized design of the ball holder, steel ball and other components, enable the entire system to not only operate stably under normal working pressure, but also maintain low friction and wear under high pressure conditions.

[0060] In summary, the working principle of the present invention realizes efficient and smooth switching of the multi-oil and multi-electric aircraft engine fuel system through precise control of multi-stage valves and electromagnetic actuation, optimizes the electromagnetic force requirements by using the principles of fluid mechanics, and ensures the safety and stability of the system under high pressure conditions.

[0061] The above is only a preferred embodiment of the present invention, and does not limit the present invention in any way. Any simple modification, change and equivalent structural change made to the above embodiment according to the technical essence of the present invention still fall within the protection scope of the technical solution of the present invention. It has a wide range of applications, is suitable for a variety of hydraulic and other working conditions, and has reliable performance.

Claims

1. A pressure-smooth opening electromagnetic device for a multi-oil-circuit multi-electric aircraft engine fuel system, comprising at least a valve body base, a main valve assembly, a secondary valve assembly and an electromagnetically actuated pilot valve assembly, characterized in that: The valve body base is provided with an oil passage, a main valve mounting valve port and a secondary valve mounting valve port, wherein: the oil passage is provided with a partition plate which divides it into an upstream oil inlet section and a downstream oil outlet section; the main valve mounting valve port is arranged at the top of the valve body base, and is a cylindrical structure extending in the height direction as a whole, and at least one main oil outlet hole communicating with the upstream oil inlet section and one main oil return hole communicating with the downstream oil outlet section are provided at the bottom thereof; the secondary valve mounting valve port is a blind hole channel structure extending in the horizontal direction with one end closed and the other end open, and at least one secondary oil outlet hole communicating with the upstream oil inlet section and one secondary oil return hole communicating with the downstream oil outlet section are provided on the side wall thereof; The main valve assembly at least includes a main valve and a main valve return spring, the main valve is arranged in the main valve mounting valve port, and is a plate-like structural member with an annular skirt as a whole, the annular skirt and the circumferential side wall of the main valve mounting valve port form a clearance fit and its top surface is higher than the top surface of the plate-like structural member; the bottom surface center of the plate-like structural member protrudes downward to form a conical structure facing the main oil return hole, a downwardly concave sealing gasket accommodating groove is provided at the center of the top surface, a central oil return hole penetrating downwardly through the conical structure is provided at the bottom of the groove, and a plurality of oil holes penetrating the top and bottom surfaces thereof and distributed along the circumferential direction are also provided on the plate-like structural member; the main valve return spring is installed between the plate-like structural member of the main valve and the bottom wall of the main valve mounting valve port; The auxiliary valve assembly is formed as a one-way valve as a whole, and at least comprises a valve seat, a steel ball, a ball holder, an auxiliary valve return spring and a one-way valve seat, which are arranged axially along the blind hole channel of the auxiliary valve mounting valve port, wherein: the valve seat is arranged at an axial position corresponding to the partition plate, and is provided with a central through hole extending axially along the channel, and the channel space in front of it is connected with the auxiliary oil outlet hole; the steel ball, the ball holder and the auxiliary valve return spring are arranged in the inner cavity of the one-way valve seat in sequence; the top of the one-way valve seat is against the rear end surface of the valve seat, and there is a radial gap between its front end side wall and the inner wall of the channel and is connected with the auxiliary oil return hole, and a plurality of oil holes are provided on its front end side wall, and its rear end side wall is arranged on the auxiliary valve mounting valve port in a sealed and fixed manner; The electromagnetically actuated pilot valve assembly is installed on the top of the valve body base, and includes at least a moving iron core driven by an electromagnetic coil and a spring-reset pilot valve. The pilot valve includes at least a valve rod and a sealing gasket. The upper end of the valve rod is fixedly connected to the end of the moving iron core, and the sealing gasket is fixedly arranged at the lower end of the valve rod to cooperate with the sealing gasket accommodating groove at the top of the main valve to form a seal; the moving iron core drives the valve rod to move axially through the energization operation of the electromagnetic coil, and the reset spring pushes the moving iron core and the valve rod back to the initial position when the electromagnetic coil is de-energized.

2. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: The oil flow channel extends in a horizontal direction and passes through the main body of the valve body base, one end of which is formed as an oil inlet end, and the other end is formed as an oil outlet end. The oil inlet end is used to be connected to an upstream fuel pump through a pipeline, and the oil outlet end is used to be connected to a downstream combustion chamber or fuel nozzle through a pipeline. The inner wall of the oil flow channel is precisely processed and polished to reduce friction resistance during the flow of fuel, and its diameter is adjusted according to the fuel flow requirement.

3. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: The main valve return spring adopts a variable cross-section design, with a bottom coil diameter larger than a top coil diameter and an overall conical structure, so as to reduce the overall height of the spring while ensuring sufficient return force, reduce the axial size of the device, and provide nonlinear elastic characteristics. A larger return force is provided at the initial opening of the main valve, and the return force is reduced when it is close to the fully open position, which helps to achieve a smoother oil circuit switching process.

4. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: At least one annular sealing groove is provided on the outer circumferential surface of the one-way valve seat, and a sealing ring is installed in the annular sealing groove to achieve sealing between the one-way valve seat and the blind hole channel of the auxiliary valve mounting valve port; and, the outer circumferential surface of the one-way valve seat is also provided with an external thread, and the inner wall of the blind hole channel of the auxiliary valve mounting valve port is provided with an internal thread, and the one-way valve seat and the blind hole channel of the auxiliary valve mounting valve port are fixedly connected by threads.

5. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: The inner cavity of the one-way valve seat is formed into a stepped structure, including at least a first cavity with a larger inner diameter arranged near its top and a second cavity with a smaller inner diameter arranged near its end, wherein the ball holder is arranged in the first cavity in a manner that it can slide left and right in the axial direction, and its front end face is processed into a conical groove to support the steel ball to ensure that the steel ball remains stably positioned when the oil pressure changes, and its rear end face is processed into a spring seat; the main body of the auxiliary valve reset spring is arranged in the second cavity, its top portion abuts against the rear end face of the ball holder, and the end abuts against the bottom wall of the second cavity to provide a reset force when the steel ball moves under pressure.

6. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 5 is characterized in that: A first oil hole is provided on the front end side wall of the first cavity of the one-way valve seat, which is used to guide the fuel into the first cavity during the movement of the ball holder. A second oil hole is provided on the front end side wall of the second cavity, which is used to discharge the fuel when the auxiliary valve return spring is under pressure, thereby reducing the influence of back pressure on the return action.

7. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: At least one annular sealing groove is provided on the outer peripheral surface of the valve seat, and a sealing ring is installed in the annular sealing groove to achieve sealing between the valve seat and the blind hole channel of the auxiliary valve mounting valve port; and the central through hole of the valve seat is set as a conical expansion structure to reduce the flow resistance of the fuel when it enters the central through hole and reduce the generation of turbulence and bubbles.

8. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 1 is characterized in that: The electromagnetically actuated pilot valve assembly is also provided with an electromagnetic coil assembly, and the electromagnetic coil assembly includes at least a top cover, an electromagnetic coil and a coil mounting frame, wherein: the coil mounting frame includes at least a cylindrical base and a bracket column formed at the center of the top surface of the cylindrical base and extending axially upward, the inner circumferential wall of the cylindrical base is provided with an internal thread and is fixedly arranged on the outer circumferential wall of the main valve mounting valve port by a threaded connection, and the inner circumferential wall of the cylindrical base is provided with an annular sealing groove and a sealing ring to achieve sealing with the main valve mounting valve port; the electromagnetic coil is axially sleeved and installed on the bracket column, and the top cover is threadedly connected and fixedly arranged on the top of the bracket column to achieve axial constraint on the top of the electromagnetic coil.

9. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 8, characterized in that: The support column of the coil mounting frame is a hollow cylindrical structure with an open top as a whole, and the bottom of the cylindrical inner cavity is processed to form a conical groove, and a valve rod through hole extending downward and passing through the cylindrical base is provided on the bottom wall of the conical groove; the moving iron core is accommodated in the cylindrical inner cavity in a manner that it can slide up and down in the axial direction, and a step structure for supporting an iron core return spring is provided on its side wall, and the other end of the iron core return spring is against the top surface of the conical groove.

10. The pressure smooth opening electromagnetic device of the multi-oil circuit multi-electric aircraft engine fuel system according to claim 9, characterized in that: The end of the moving iron core is processed to form a conical structure, which is adapted to the conical surface of the conical groove and an air gap is formed between the two to achieve axial movement of the moving iron core; a threaded connection hole is provided at the center of the conical structure of the moving iron core, and the valve rod passes upward through the valve rod through hole and is threadedly fixed to the end of the moving iron core.

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