Aviation fuel valve

Abstract

The invention provides an aviation fuel valve which comprises a valve body, and an oil inlet channel, a main oil way and a starting oil way are arranged in the valve body; the main oil way comprises a fuel oil leading-in channel, an adjusting cavity and a fuel oil hole, the front end of the fuel oil leading-in channel communicates with the oil inlet channel, the rear end of the fuel oil leading-in channel is connected to the front end of the adjusting cavity, the front end of the fuel oil hole is formed in the inner circumferential wall of the middle of the adjusting cavity, and a first piston valve element is arranged in the adjusting cavity; a control cavity is further formed in the valve body, a second piston valve element is arranged in the control cavity, the second piston valve element and the first piston valve element are connected through a connecting shaft, the control cavity is divided into a front cavity and a rear cavity, the front cavity is communicated with the air outlet end of an aircraft engine compressor, and the rear cavity is communicated with the outside atmosphere. When the first piston valve element is located at the front end of the adjusting cavity, the fuel oil hole is closed, and when the first piston valve element moves from front to back, the fuel oil hole is gradually opened. The valve can avoid too fast oil inlet of a main oil way, prevent sudden pressure drop of a starting oil way, and improve the starting reliability of an aircraft engine.

Description

Technical Field

[0001] The present invention relates to the technical field of fuel valves, and in particular to an aviation fuel valve. Background Art

[0002] Modern small and medium-sized aircraft engine fuel systems use electric fuel pumps and dual oil circuit solutions, that is, electric fuel pumps are used to control fuel supply, and the starting oil circuit is connected to a centrifugal starting nozzle. The nozzle atomizes the fuel and then ignites the fuel with a high-energy igniter, so that the engine starts. After starting, the engine is supplied with fuel by a venturi nozzle connected to the main oil circuit. At present, this solution has a main oil circuit with a much smaller flow resistance than the starting oil circuit, and the main oil circuit enters the oil too quickly. At the moment of switching between the starting oil circuit and the main oil circuit, the starting oil circuit pressure drops sharply, and the fuel supply is reduced, which can easily lead to engine start failure. Summary of the invention

[0003] The technical problem to be solved by the present invention is that the main oil circuit enters the oil circuit too quickly, causing the starting oil circuit pressure to drop suddenly, reducing the oil supply, and easily leading to engine starting failure. In order to overcome the above defects of the prior art, the present invention provides an aviation fuel valve.

[0004] The present invention provides an aviation fuel valve, comprising a valve body, wherein an oil inlet passage, a main oil circuit and a starting oil circuit are arranged in the valve body, wherein the oil inlet passage is communicated with the main oil circuit and the starting oil circuit, wherein a fuel filtering mechanism is arranged in the oil inlet passage, wherein the main oil circuit is used to be connected with an aircraft main fuel system, wherein the starting oil circuit is used to be connected with an aircraft starting fuel system, wherein the aircraft starting fuel system starts an aircraft engine; wherein the main oil circuit comprises a fuel introduction passage, an adjusting chamber and a fuel hole, wherein the front end of the fuel introduction passage is communicated with the oil inlet passage, wherein the rear end of the fuel introduction passage is connected to the front end of the adjusting chamber, wherein the adjusting chamber is a cylindrical chamber, wherein the front end of the fuel hole is arranged on the inner peripheral wall in the middle of the adjusting chamber, and wherein the fuel hole The rear end is connected to the main fuel system of the aircraft, and a first piston valve core that moves axially is provided in the regulating chamber; a control chamber is also provided in the valve body, and a movable second piston valve core is provided in the control chamber, and the second piston valve core is connected to the first piston valve core through a connecting shaft, and the second piston valve core seals and separates the control chamber into a front chamber and a rear chamber, and the front chamber is connected to the air outlet end of the aircraft engine compressor, and the pressure at the air outlet end of the aircraft engine compressor gradually increases as the aircraft engine is started, and the rear chamber is connected to the outside atmosphere; when the first piston valve core is located at the front end of the regulating chamber, the fuel hole is closed, and when the first piston valve core moves from front to rear, the fuel hole is gradually opened.

[0005] Compared with the prior art, the aviation fuel valve of the present application has the following advantages: when the first piston valve core is located at the front end of the regulating chamber, the fuel hole is closed, that is, the fuel hole is disconnected from the fuel introduction channel, so that the valve body supplies oil to the aircraft starting fuel system through the starting oil circuit; when the starting oil circuit switches to the main oil circuit, the pressure at the air outlet end of the aircraft engine compressor gradually increases as the aircraft engine starts, and a pressure difference is formed between the front chamber and the rear chamber, so that the second piston valve core moves backward, and the second piston valve core moves the first piston valve core backward through the connecting shaft, the fuel hole is connected with the fuel introduction channel, and the fuel hole is gradually opened, that is, the entire switching main oil circuit oil supply process is smooth, avoiding excessively fast oil inflow to the main oil circuit, preventing the starting oil circuit pressure from suddenly dropping, and improving the starting reliability of the aircraft engine; at the same time, a fuel filtering mechanism is provided in the oil inlet channel, so that the fuel flowing into the main oil circuit and the starting oil circuit is filtered, so that the fuel is clean, which is beneficial to the starting and operation of the aircraft engine.

[0006] In a possible implementation manner, a guide rod is provided on the first piston valve core, and a guide hole for the guide rod to move along the axial direction is provided on the valve body.

[0007] Compared with the prior art, the above technical solution can provide the first piston valve core with axial movement guidance, thereby improving the movement reliability of the first piston valve core.

[0008] In a possible implementation, a first spring is provided in the regulating chamber, a front end of the first spring is connected to the first piston valve core, a rear end of the first spring is connected to the valve body, and the first spring is sleeved on the guide rod to drive the first piston valve core to move forward.

[0009] Compared with the prior art, the above technical solution can make the first piston valve core be subjected to a certain extrusion force at the front end of the regulating valve, so as to delay the backward movement of the first piston valve core, avoid excessively fast oil inflow into the main oil circuit, and facilitate the oil inflow into the starting oil circuit.

[0010] In a possible implementation manner, a first annular groove is provided on the outer peripheral wall of the second piston valve core, a first sealing ring is provided in the first annular groove, and the first sealing ring is sealingly fitted with the inner peripheral wall of the control chamber.

[0011] Compared with the prior art, the above technical solution can seal and isolate the front cavity and the rear cavity, thereby improving the movement reliability of the second piston valve core.

[0012] In a possible implementation, an installation cavity is provided in the valve body, a detachable valve sleeve is provided in the installation cavity, and the valve sleeve is provided with the regulating cavity and the control cavity which are coaxially and spaced apart; the coupling is passed through the valve sleeve, the front end of the coupling is located in the control cavity, the rear end of the coupling is located in the regulating cavity, and a sealing ring is provided between the valve sleeve and the coupling.

[0013] Compared with the prior art, the above technical solution can facilitate the assembly of the entire valve, while ensuring stable structural connection and reliable use, and at the same time improving the separation and sealing between the regulating chamber and the control chamber.

[0014] In a possible embodiment, the fuel filtering mechanism includes an oil filter block, a fuel filter element and a second spring. The oil filter block is fixed in the oil inlet channel and arranged near the front end of the oil inlet channel. The oil filter block is annular in structure and the outer circumferential wall of the oil filter block is sealed with the inner circumferential wall of the oil inlet channel. A second sealing ring is provided on the rear end surface of the oil filter block. The fuel filter element is axially movable in the oil inlet channel. An oil gap is provided between the fuel filter element and the inner circumferential wall of the oil inlet channel. The rear end of the second spring is connected to the valve body, and the front end of the second spring is connected to the fuel filter element. The second spring is used to move the fuel filter element toward the oil filter block. When the fuel filter element squeezes the second sealing ring of the oil filter block, the fuel filter element filters the fuel in the oil inlet channel. When the fuel filter element is away from the oil filter block, the fuel in the oil inlet channel flows out from the rear end of the oil channel through the oil gap.

[0015] Compared with the prior art, the above technical solution can realize the filtering of the fuel in the oil inlet channel by the filtering mechanism. At the same time, when the fuel filter element is blocked, the oil can enter through the oil gap to avoid oil circuit blockage and ensure the normal operation of the main oil circuit and the starting oil circuit.

[0016] In a possible embodiment, a second annular groove is provided on the rear end face of the oil filter block, and the second sealing ring is arranged in the second annular groove; a third annular groove is provided on the outer peripheral wall of the oil filter block, and a third sealing ring is provided in the third annular groove, and the third sealing ring is sealed with the inner peripheral wall of the oil inlet channel.

[0017] Compared with the prior art, the above technical solution can improve the sealing reliability of the oil filter block.

[0018] In a possible embodiment, the fuel filter element includes a support ring and a filter screen, the front end of the support ring is used to abut against the second sealing ring, and the rear end of the support ring is detachably connected to the filter screen; the outer diameter of the support ring is smaller than the inner diameter of the oil inlet channel, and the outer diameter of the support ring is larger than the outer diameter of the second sealing ring.

[0019] Compared with the prior art, the above technical solution can stabilize the filter support, facilitate the disassembly and assembly of the filter, and facilitate replacement. At the same time, it is beneficial for the oil flow through the oil gap and improves the stability of the first sealing ring.

[0020] In a possible implementation manner, the filter screen has a conical structure, and a large end of the filter screen is plugged into a support ring.

[0021] Compared with the prior art, the above technical solution can increase the contact area with the fuel and improve the filtering effect.

[0022] In a possible implementation manner, a retaining spring is provided at the front end of the oil inlet passage, and the retaining spring abuts against the oil filter block; an annular step is provided at the rear end of the oil inlet passage, and the annular step abuts against the second spring.

[0023] Compared with the prior art, the above technical solution can improve the setting stability of the oil filter pressure block and the second spring. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the overall structure of the present invention; Figure 2 The cross section of the present invention Figure 1 ; Figure 3 for Figure 2 A magnified image of point A; Figure 4 The cross section of the present invention Figure 2 ; Figure 5 It is a partial structural schematic diagram of the present invention; Description of reference numerals: 1. Valve body; 11. Guide hole; 12. Installation cavity; 13. Valve sleeve; 14. Sealing ring; 2. Oil inlet channel; 21. Circlip; 22. Annular step; 3. Main oil circuit; 31. Fuel introduction channel; 32. Adjustment cavity; 33. Fuel hole; 4. Starting oil circuit; 5. Fuel filtering mechanism; 51. Oil filter block; 511. Second ring groove; 512. Third ring groove; 52. Fuel filter element; 521. Support ring; 522. Filter screen; 53. Second spring; 54. Second sealing ring; 55. Oil clearance; 56. Third sealing ring; 6. First piston valve core; 61. Guide rod; 7. Control cavity; 71. Front cavity; 72. Rear cavity; 8. Second piston valve core; 81. First ring groove; 82. First sealing ring; 9. Connecting shaft; 10. First spring. DETAILED DESCRIPTION

[0025] First, those skilled in the art should understand that these implementations are only used to explain the technical principles of the embodiments of the present application, and are not intended to limit the protection scope of the embodiments of the present application. Those skilled in the art can make adjustments to them as needed to adapt to specific application scenarios.

[0026] In the description of the embodiments of the present application, it should be noted that, unless otherwise clearly specified and limited, the terms "connected" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in the embodiments of the present application can be understood according to specific circumstances.

[0027] In the embodiments of the present application, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0028] The present application is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0029] See also Figures 1 to 5The embodiment of the present application discloses an aviation fuel valve, comprising a valve body 1, wherein an oil inlet passage 2, a main oil circuit 3 and a starting oil circuit 4 are arranged in the valve body 1, wherein the oil inlet passage 2 is communicated with the main oil circuit 3 and the starting oil circuit 4, wherein a fuel filtering mechanism 5 is arranged in the oil inlet passage 2, wherein the main oil circuit 3 is used to be connected with an aircraft main fuel system, wherein the starting oil circuit 4 is used to be connected with an aircraft starting fuel system, wherein the aircraft starting fuel system starts an aircraft engine; wherein the main oil circuit 3 comprises a fuel introduction passage 31, an adjusting chamber 32 and a fuel hole 33, wherein the front end of the fuel introduction passage 31 is communicated with the oil inlet passage 2, wherein the rear end of the fuel introduction passage 31 is connected to the front end of the adjusting chamber 32, wherein the adjusting chamber 32 is extended axially to form a cylindrical cavity, wherein the front end of the fuel hole 33 is arranged on the inner peripheral wall in the middle of the adjusting chamber 32, wherein the rear end of the fuel hole 33 is connected with the aircraft main fuel system, wherein the adjusting chamber 32 is provided with a first adjusting chamber 32 which moves axially. A piston valve core 6, the first piston valve core 6 is used to open and close the fuel hole 33; the valve body 1 is also provided with a control chamber 7, the control chamber 7 is provided with a movable second piston valve core 8, the second piston valve core 8 is connected to the first piston valve core 6 through a connecting shaft 9, the second piston valve core 8 seals and separates the control chamber 7 into a front chamber 71 and a rear chamber 72, the front chamber 71 is connected to the air outlet of the aircraft engine compressor, the pressure at the air outlet of the aircraft engine compressor gradually increases as the aircraft engine starts, and the rear chamber 72 is connected to the outside atmosphere; when the first piston valve core 6 is located at the front end of the regulating chamber 32, the fuel hole 33 is closed, that is, the first piston valve core 6 moves between the fuel introduction channel 31 and the fuel hole 33, when the first piston valve core 6 moves from front to back, the fuel hole 33 is gradually opened, that is, the fuel introduction channel 31 and the fuel hole 33 are both located at the front side of the first piston valve core 6. The aircraft main fuel system, aircraft starting fuel system, aircraft engine, and aircraft engine compressor are all prior art.

[0030] As can be known from the above, when the first piston valve core 6 is located at the front end of the regulating chamber 32, the fuel hole 33 is closed, that is, the fuel hole 33 is disconnected from the fuel introduction channel 31, so that the valve body 1 supplies oil to the aircraft starting fuel system through the starting oil circuit 4; when the starting oil circuit 4 switches to the main oil circuit 3, the pressure at the outlet end of the compressor of the aircraft engine gradually increases as the aircraft engine starts, and a pressure difference is formed between the front chamber 71 and the rear chamber 72, so that the second piston valve core 8 moves backward, and the second piston valve core 8 moves the first piston valve core 6 backward through the connecting shaft 9, and the fuel hole 33 is connected with the fuel introduction channel 31, and the fuel hole 33 is gradually opened, that is, the entire switching process of the main oil circuit 3 supplying oil is smooth, avoiding the main oil circuit 3 from entering too fast, preventing the pressure of the starting oil circuit 4 from dropping suddenly, and improving the starting reliability of the aircraft engine; at the same time, a fuel filtering mechanism 5 is provided in the oil inlet channel 2, so that the fuel flowing into the main oil circuit 3 and the starting oil circuit 4 is filtered, so that the fuel is clean, which is beneficial to the starting and operation of the aircraft engine.

[0031] In this embodiment, a guide rod 61 is provided on the first piston valve core 6, and a guide hole 11 is provided on the valve body 1 for the guide rod 61 to move axially. This enables the first piston valve core 6 to have axial movement guidance, thereby improving the movement reliability of the first piston valve core 6.

[0032] In this embodiment, a first spring 10 is provided in the regulating chamber 32, the front end of the first spring 10 is connected to the first piston valve core 6, and the rear end of the first spring 10 is connected to the valve body 1. The first spring 10 is sleeved on the guide rod 61 to drive the first piston valve core 6 to move forward, thereby enabling the first piston valve core 6 to be subjected to a certain extrusion force at the front end of the regulating valve to achieve delayed backward movement of the first piston valve core 6, thereby avoiding excessively fast oil inlet into the main oil circuit 3 and facilitating the oil inlet into the starting oil circuit 4.

[0033] In this embodiment, a first annular groove 81 is provided on the outer circumferential wall of the second piston valve core 8, and a first sealing ring 82 is provided in the first annular groove 81. The first sealing ring 82 is sealed in contact with the inner circumferential wall of the control chamber 7, thereby enabling the front chamber 71 and the rear chamber 72 to be sealed and isolated, thereby improving the movement reliability of the second piston valve core 8.

[0034] In this embodiment, the valve body 1 is provided with an installation cavity 12, and the installation cavity 12 is provided with a detachable valve sleeve 13, and the valve sleeve 13 is provided with the regulating cavity 32 and the control cavity 7 which are coaxially and spaced apart; the connecting shaft 9 is passed through the valve sleeve 13, and the front end of the connecting shaft 9 is located in the control cavity 7, and the rear end of the connecting shaft 9 is located in the regulating cavity 32, and a sealing ring 14 is provided between the valve sleeve 13 and the connecting shaft 9, thereby facilitating the assembly of the entire valve, and at the same time, the structural connection is stable and reliable to use, and at the same time, the separation and sealing between the regulating cavity 32 and the control cavity 7 are improved.

[0035] In this embodiment, the fuel filter mechanism 5 includes an oil filter block 51, a fuel filter element 52 and a second spring 53. The oil filter block 51 is fixed in the oil inlet channel 2 and arranged near the front end of the oil inlet channel 2. The oil filter block 51 is annular in structure and the outer peripheral wall of the oil filter block 51 is sealed with the inner peripheral wall of the oil inlet channel 2. A second sealing ring 54 is provided on the rear end surface of the oil filter block 51. The fuel filter element 52 is axially movable in the oil inlet channel 2. An oil gap 55 is provided between the fuel filter element 52 and the inner peripheral wall of the oil inlet channel 2. The rear end of the second spring 53 is connected to the valve body 1. The front end of the second spring 53 The second end is connected to the fuel filter element 52, and the second spring 53 is used to move the fuel filter element 52 toward the oil filter pressure block 51. When the fuel filter element 52 squeezes the second sealing ring 54 of the oil filter pressure block 51, the fuel filter element 52 filters the fuel in the oil inlet channel 2. When the fuel filter element 52 is away from the oil filter pressure block 51, the fuel in the oil inlet channel 2 flows out from the rear end of the oil channel through the oil gap 55, thereby enabling the filtering mechanism to filter the fuel in the oil inlet channel 2. At the same time, when the fuel filter element 52 is blocked, oil can flow in through the oil gap 55 to avoid oil circuit blockage, thereby ensuring the normal operation of the main oil circuit 3 and the starting oil circuit 4.

[0036] In this embodiment, a second annular groove 511 is provided on the rear end face of the oil filter block 51, and the second sealing ring 54 is arranged in the second annular groove 511; a third annular groove 512 is provided on the outer peripheral wall of the oil filter block 51, and a third sealing ring 56 is provided in the third annular groove 512, and the third sealing ring 56 is sealed with the inner peripheral wall of the oil inlet channel 2, thereby improving the sealing reliability of the oil filter block 51.

[0037] In this embodiment, the fuel filter element 52 includes a support ring 521 and a filter screen 522, the front end of the support ring 521 is used to abut against the second sealing ring 54, and the rear end of the support ring 521 is detachably connected to the filter screen 522; the outer diameter of the support ring 521 is smaller than the inner diameter of the oil inlet channel 2, and the outer diameter of the support ring 521 is larger than the outer diameter of the second sealing ring 54, thereby enabling the filter screen 522 to be supported stably, and convenient for disassembly and assembly of the filter screen 522, and convenient for replacement, while facilitating the smooth passage of oil through the oil gap 55 and improving the stability of the use of the first sealing ring 82.

[0038] In this embodiment, the filter screen 522 is in a conical structure, and the large end of the filter screen 522 is plugged into the support ring 521, thereby increasing the contact area with the fuel and improving the filtering effect.

[0039] In this embodiment, a retaining spring 21 is provided at the front end of the oil inlet channel 2, and the retaining spring 21 abuts against the oil filter pressure block 51; an annular step 22 is provided at the rear end of the oil inlet channel 2, and the annular step 22 abuts against the second spring 53, thereby improving the setting stability of the oil filter pressure block 51 and the second spring 53.

[0040] In this embodiment, the starting oil circuit 4 of the aviation fuel valve is in an operating state: the first spring 10 drives the first piston valve core 6 to move forward, squeezing the first piston valve core 6 at the front end of the regulating chamber 32, and at this time, the fuel hole 33 is disconnected from the fuel introduction channel 31, that is, the valve body 1 supplies fuel to the aircraft starting fuel system through the starting oil circuit 4.

[0041] In this embodiment, the main oil circuit 3 of the aviation fuel valve switches its operating state: the pressure at the outlet end of the aircraft engine compressor gradually increases as the aircraft engine starts, a pressure difference is formed between the front chamber 71 and the rear chamber 72, and the squeezing force of the first spring 10 is overcome, so that the second piston valve core 8 moves backward, and the second piston valve core 8 moves the first piston valve core 6 backward through the connecting shaft 9, the fuel hole 33 is connected to the fuel introduction channel 31, and the fuel hole 33 is gradually opened, that is, the slow oil supply switching of the main oil circuit 3 is realized.

[0042] In the description of the embodiments of the present application, it should be noted that in the description of the present application, terms such as "inside" and "outside" indicating directions or positional relationships are based on the directions or positional relationships shown in the drawings. This is only for the convenience of description, and does not indicate or imply that the device or component must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it cannot be understood as a limitation on the present application.

[0043] In the description of the present application, the description with reference to the terms "one embodiment", "some embodiments", "in the present embodiment", "specific example", or "some examples" etc. means that the specific features, mechanisms, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, mechanisms, materials or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0044] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aviation fuel valve, characterized in that: The invention comprises a valve body (1), wherein an oil inlet passage (2), a main oil circuit (3) and a starting oil circuit (4) are arranged in the valve body (1), wherein the oil inlet passage (2) is communicated with the main oil circuit (3) and the starting oil circuit (4), wherein a fuel filter mechanism (5) is arranged in the oil inlet passage (2), wherein the main oil circuit (3) is used to be connected with an aircraft main fuel system, wherein the starting oil circuit (4) is used to be connected with an aircraft starting fuel system, wherein the aircraft starting fuel system starts an aircraft engine; wherein the main oil circuit (3) comprises a fuel introduction passage (31), a regulating chamber (32) and a fuel hole (33), wherein the front end of the fuel introduction passage (31) is communicated with the oil inlet passage (2), wherein the rear end of the fuel introduction passage (31) is connected to the front end of the regulating chamber (32), wherein the regulating chamber (32) is a cylindrical chamber, wherein the front end of the fuel hole (33) is arranged on the inner peripheral wall in the middle of the regulating chamber (32), and wherein the fuel hole (33) is provided on the inner peripheral wall in the middle of the regulating chamber (32). ) is connected to the main fuel system of the aircraft, and a first piston valve core (6) movable in the axial direction is arranged in the regulating chamber (32); a control chamber (7) is also arranged in the valve body (1), and a movable second piston valve core (8) is arranged in the control chamber (7), and the second piston valve core (8) is connected to the first piston valve core (6) through a connecting shaft (9), and the second piston valve core (8) seals and separates the control chamber (7) into a front chamber (71) and a rear chamber (72), the front chamber (71) is connected to the air outlet of the aircraft engine compressor, and the pressure at the air outlet of the aircraft engine compressor gradually increases as the aircraft engine is started, and the rear chamber (72) is connected to the outside atmosphere; when the first piston valve core (6) is located at the front end of the regulating chamber (32), the fuel hole (33) is closed, and when the first piston valve core (6) moves from front to rear, the fuel hole (33) is gradually opened.

2. The aviation fuel valve according to claim 1, characterized in that: The first piston valve core (6) is provided with a guide rod (61), and the valve body (1) is provided with a guide hole (11) for the guide rod (61) to move along the axial direction.

3. The aviation fuel valve according to claim 2, characterized in that: A first spring (10) is provided in the regulating chamber (32), the front end of the first spring (10) is connected to the first piston valve core (6), the rear end of the first spring (10) is connected to the valve body (1), and the first spring (10) is sleeved on the guide rod (61) to drive the first piston valve core (6) to move forward.

4. The aviation fuel valve according to claim 1, characterized in that: A first annular groove (81) is provided on the outer peripheral wall of the second piston valve core (8), a first sealing ring (82) is provided in the first annular groove (81), and the first sealing ring (82) is in sealing contact with the inner peripheral wall of the control chamber (7).

5. The aviation fuel valve according to claim 1, characterized in that: The valve body (1) is provided with an installation cavity (12), the installation cavity (12) is provided with a detachable valve sleeve (13), the valve sleeve (13) is provided with the regulating cavity (32) and the control cavity (7) which are coaxially and spaced apart; the connecting shaft (9) is passed through the valve sleeve (13), the front end of the connecting shaft (9) is located in the control cavity (7), and the rear end of the connecting shaft (9) is located in the regulating cavity (32), and a sealing ring (14) is provided between the valve sleeve (13) and the connecting shaft (9).

6. The aviation fuel valve according to claim 1, characterized in that: The fuel filter mechanism (5) comprises an oil filter block (51), a fuel filter element (52) and a second spring (53). The oil filter block (51) is fixed in the oil inlet passage (2) and arranged close to the front end of the oil inlet passage (2). The oil filter block (51) is an annular structure and the outer peripheral wall of the oil filter block (51) is sealed with the inner peripheral wall of the oil inlet passage (2). A second sealing ring (54) is arranged on the rear end surface of the oil filter block (51). The fuel filter element (52) is arranged in the oil inlet passage (2) in an axially movable manner. A clearance is arranged between the fuel filter element (52) and the inner peripheral wall of the oil inlet passage (2). The second spring (53) is connected to the valve body (1) at its rear end, and connected to the fuel filter element (52) at its front end. The second spring (53) is used to move the fuel filter element (52) toward the oil filter block (51). When the fuel filter element (52) squeezes the second sealing ring (54) of the oil filter block (51), the fuel filter element (52) filters the fuel in the oil inlet channel (2). When the fuel filter element (52) moves away from the oil filter block (51), the fuel in the oil inlet channel (2) flows out from the rear end of the oil channel through the oil gap (55).

7. The aviation fuel valve according to claim 6, characterized in that: A second annular groove (511) is provided on the rear end surface of the oil filter block (51), and the second sealing ring (54) is arranged in the second annular groove (511); a third annular groove (512) is provided on the outer peripheral wall of the oil filter block (51), and a third sealing ring (56) is arranged in the third annular groove (512), and the third sealing ring (56) is in sealing cooperation with the inner peripheral wall of the oil inlet passage (2).

8. The aviation fuel valve according to claim 6, characterized in that: The fuel filter element (52) comprises a support ring (521) and a filter screen (522); the front end of the support ring (521) is used to abut against the second sealing ring (54), and the rear end of the support ring (521) is detachably connected to the filter screen (522); the outer diameter of the support ring (521) is smaller than the inner diameter of the oil inlet channel (2), and the outer diameter of the support ring (521) is larger than the outer diameter of the second sealing ring (54).

9. The aviation fuel valve according to claim 8, characterized in that: The filter screen (522) has a conical structure, and the large end of the filter screen (522) is plugged into the support ring (521).

10. The aviation fuel valve according to claim 6, characterized in that: A retaining spring (21) is provided at the front end of the oil inlet passage (2), and the retaining spring (21) abuts against the oil filter pressure block (51); an annular step (22) is provided at the rear end of the oil inlet passage (2), and the annular step (22) abuts against the second spring (53).

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