Automatic deflation and injection oil return integrated device and method for engine fuel control system

Abstract

The invention discloses an automatic deflation and injection oil return integrated device and method for an engine fuel control system, and relates to the technical field of fuel adjustment. The device comprises a differential pressure valve, a minimum pressure parking valve, a steel ball, a spring and a deflation valve. The invention designs an integrated system structure which can realize automatic deflation before the engine is started and injection oil return after the engine is started. The mode that an independent deflation valve and an independent injection oil return valve are arranged to achieve the two functions in the prior art is improved, the functions are guaranteed, meanwhile, the number of parts of an engine metering device is reduced, the structure of a fuel oil system is more compact, and materials are saved. The function of automatic switching between deflation and injection oil return can be achieved, the manual deflation time is saved, and the reliability of a fuel system and the working efficiency of a product are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of fuel regulation, and in particular relates to an integrated device and method for automatic air venting and oil injection return of an engine fuel control system. Background Art

[0002] In the aviation engine fuel control system, starting bleed and induced oil return are important functions. The exhaust work before the traditional engine is usually done by a separate bleed valve, which is automatic or manual; the induced oil return function is usually composed of a parking valve and a pressure difference valve. Its function is to return the excess fuel after the fuel supply system provides the engine with metered fuel to the aircraft tank, ensuring that the fuel supply system inlet is filled while taking away excess heat, reducing the temperature rise of the engine metering device. The above two functions are generally composed of four to five structures, which increases the complexity of the engine metering device and reduces its reliability. To solve this problem, this patent proposes a method of integrating bleed before engine start and induced oil return after fuel supply. Summary of the invention

[0003] Based on the above background, in order to meet the design requirements of lightweight, miniaturization and automation of aircraft engines, an integrated system structure is designed to realize automatic air bleeding before engine start and oil return after start.

[0004] In view of this, according to one aspect of an embodiment of the present invention, an integrated device for automatic deflation and oil return injection of an engine fuel control system is provided, comprising: a pressure differential valve 1, a minimum pressure parking valve 2, a steel ball 3, a spring 4, and a deflation valve 5; wherein the steel ball 3 is installed in the spring cavity of the deflation valve 5 through the spring 4 to form an automatic deflation device, the diameter of the steel ball 3 matches the inner diameter of the spring cavity, the steel ball 3 can block the spring cavity and move axially therein, and the pressure differential valve 1 is used to ensure that the fuel pump is adjusted The pressure difference before and after the metering valve of the fuel pump is basically constant. The pressure difference valve 1A port is the oil inlet, and the fuel after the gear pump flows into the pressure difference valve through the pressure difference valve 1A port; the pressure difference valve 1B port is the oil return port, and part of the fuel after the pump returns to the front of the gear pump through the pressure difference valve 1B port, and the pressure difference valve 1C port is the oil outlet; the function of the minimum pressure parking valve 2 is to ensure that the fuel inside the fuel pump regulator has a certain pressure. The minimum pressure parking valve 2A port is the oil inlet, and the minimum pressure parking valve 2D port is the oil outlet. The fuel after the metering valve passes through the minimum pressure valve 1B port to return to the front of the gear pump. The fuel flows into the minimum pressure parking valve 2A port, pushes the valve core to move, and then flows out through the minimum pressure parking valve 2D port to the engine combustion chamber; the minimum pressure parking valve 2B port is the oil inlet, and the minimum pressure parking valve 2C port is the oil outlet. When the engine starts, the minimum pressure parking valve 2 opens, and the B port and the C port are connected only through the valve core annular cavity. The induced fuel enters the minimum pressure parking valve 2 through the minimum pressure parking valve 2B port, and flows out from the minimum pressure parking valve 2C port to the discharge chamber through the valve core annular cavity. The air valve and the bleed valve 5 are arranged on the passage between the front of the gear pump and the injection outlet. The bleed valve 5A port is the low-pressure fuel inlet, the bleed valve 5B port is the injection fuel inlet, and the bleed valve 5C port is the injection fuel outlet. When the minimum pressure parking valve 2 is not opened, the B port and the C port of the minimum pressure parking valve 2 are not connected, the injection passage is in a closed state, and the spring chamber of the bleed valve 5 has no pressure. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the dynamic flow passage through the bleed valve 5A port and returns to the fuel tank to bleed the system.

[0005] Optionally, the automatic bleeding device is installed at the uppermost part of the fuel pump regulator.

[0006] According to another aspect of an embodiment of the present invention, there is also provided an integrated method for automatic bleed and induced oil return of an engine fuel control system, using any of the above-mentioned devices, including: when the engine is started, the minimum pressure parking valve is opened, the B port of the minimum pressure parking valve is connected to the C port, an induced passage is established, and the induced fuel enters through the B port of the bleed valve, passes through the bleed valve spring chamber, and flows out from the C port to the aircraft mailbox. Since the induced fuel is high-pressure fuel, the induced fuel together with the spring will push the steel ball to the left, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve.

[0007] Optionally, the minimum pressure parking valve 2 opens when the pressure after metering reaches a specified value.

[0008] Optionally, before the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both low-pressure fuel, the low-pressure return oil is connected to the bleed valve 5A port, the steel ball 3 overcomes the spring force of the spring 4, and the gas is discharged through the bleed valve 5C port.

[0009] Optionally, after the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both high-pressure fuels. The metered fuel is connected to the engine combustion chamber through the minimum pressure parking valve 2 and is divided into two paths. One path returns to the front of the gear pump through the pressure difference valve 1B port, and the other path enters the low-pressure cavity of the minimum pressure parking valve 2 through the pressure difference valve 1C port, and then flows into the bleed valve 5B port through the minimum pressure parking valve 2C port. At this time, the spring cavity of the bleed valve 5 is under high pressure, pushing the steel ball 3 to move outward close to the end face of the bleed valve 5, and the low-pressure fuel cannot flow into the bleed valve 5C port, ending the automatic bleed stage, thereby realizing the automatic conversion of automatic bleed to induced oil return function.

[0010] Optionally, the pumped fuel returns to the aircraft fuel tank through the pressure differential valve 1, the minimum pressure valve 2, and the spring chamber of the bleed valve 5.

[0011] Optionally, when the engine is not started, since the minimum pressure parking valve is not opened, the B port of the minimum pressure parking valve is not connected to the C port, the priming passage is in a closed state, and the spring chamber of the bleed valve is basically pressure-free. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the flow passage through the A port of the bleed valve and returns to the fuel tank to bleed the system: when the engine is started, the minimum pressure parking valve is opened, the B port of the minimum pressure parking valve is connected to the C port, the priming passage is established, and the priming fuel enters through the B port of the bleed valve, passes through the spring chamber of the bleed valve, and flows out from the C port to the aircraft mailbox. Since the priming fuel is high-pressure fuel, the priming fuel together with the spring will push the steel ball to the left, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve.

[0012] The present invention adopts a method for realizing engine starting air release and oil injection return by means of a spring, a steel ball, a pressure difference valve and a parking valve. The innovation of the method is:

[0013] 1. The previous method of achieving the above two functions by setting a separate bleed valve and a separate injection return oil valve has been improved. While ensuring the functions, the number of parts of the engine metering device has been reduced, making the fuel system structure more compact and saving materials.

[0014] 2. The air bleeding and oil injection return can realize automatic switching function, which saves the time of manual air bleeding and improves the reliability of the fuel system and the working efficiency of the product. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1The present invention is a schematic structural diagram of an integrated device for automatic air venting and oil return injection in an engine fuel control system.

[0016] Description of reference numerals:

[0017] 1-pressure differential valve, 2-minimum pressure parking valve, 3-steel ball, 4-spring, 5-deflation valve. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] According to one aspect of an embodiment of the present invention, an integrated device for automatic deflation and oil return injection of an engine fuel control system is provided, comprising: a pressure differential valve 1, a minimum pressure parking valve 2, a steel ball 3, a spring 4, and a deflation valve 5; wherein the steel ball 3 is installed in a spring cavity of the deflation valve 5 through the spring 4 to form an automatic deflation device, the diameter of the steel ball 3 matches the inner diameter of the spring cavity, the steel ball 3 can block the spring cavity and move axially therein, and the pressure differential valve 1 is used to ensure that the metering activity of the fuel pump regulator The pressure difference before and after the valve is basically constant. The pressure difference valve 1A port is the oil inlet, and the fuel after the gear pump flows into the pressure difference valve through the pressure difference valve 1A port; the pressure difference valve 1B port is the oil return port, and part of the fuel after the pump returns to the front of the gear pump through the pressure difference valve 1B port, and the pressure difference valve 1C port is the oil outlet; the function of the minimum pressure stop valve 2 is to ensure that the fuel inside the fuel pump regulator has a certain pressure. The minimum pressure stop valve 2A port is the oil inlet, and the minimum pressure stop valve 2D port is the oil outlet. The fuel after the metering valve passes through the minimum pressure stop valve The oil flows into the minimum pressure parking valve from the valve 2A port, pushes the valve core to move, and then flows out through the minimum pressure parking valve 2D port to the engine combustion chamber; the minimum pressure parking valve 2B port is the oil inlet, and the minimum pressure parking valve 2C port is the oil outlet. When the engine starts, the minimum pressure parking valve 2 opens, and the B port and the C port are connected only through the valve core annular cavity. The injected fuel enters the minimum pressure parking valve 2 through the minimum pressure parking valve 2B port, passes through the valve core annular cavity, and flows out from the minimum pressure parking valve 2C port to the vent. Valve, the bleed valve 5 is set on the passage between the front of the gear pump and the injection outlet, the bleed valve 5A port is the low-pressure fuel inlet, the bleed valve 5B port is the injection fuel inlet, and the bleed valve 5C port is the injection fuel outlet. When the minimum pressure parking valve 2 is not opened, the B port and the C port of the minimum pressure parking valve 2 are not connected, the injection passage is in a closed state, and the spring chamber of the bleed valve 5 has no pressure. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the dynamic flow passage through the bleed valve 5A port and returns to the fuel tank to bleed the system.

[0020] Furthermore, the automatic air bleeding device is installed at the uppermost part of the fuel pump regulator.

[0021] According to another aspect of an embodiment of the present invention, there is also provided an integrated method for automatic bleed and induced oil return of an engine fuel control system, using any of the above-mentioned devices, including: when the engine is started, the minimum pressure parking valve is opened, the B port of the minimum pressure parking valve is connected to the C port, an induced passage is established, and the induced fuel enters through the B port of the bleed valve, passes through the bleed valve spring chamber, and flows out from the C port to the aircraft mailbox. Since the induced fuel is high-pressure fuel, the induced fuel together with the spring will push the steel ball to the left, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve.

[0022] Furthermore, the minimum pressure parking valve 2 opens when the metered pressure reaches a specified value.

[0023] Furthermore, before the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both low-pressure fuels, and the low-pressure return oil is connected to the bleed valve 5A port. The steel ball 3 overcomes the spring force of the spring 4, and the gas is discharged through the bleed valve 5C port.

[0024] Furthermore, after the fuel pump regulator is started, both the fuel after the pump and the fuel after metering are high-pressure fuels. The metered fuel is connected to the engine combustion chamber through the minimum pressure parking valve 2 and is divided into two paths. One path returns to the front of the gear pump through the pressure differential valve 1B port, and the other path enters the low-pressure cavity of the minimum pressure parking valve 2 through the pressure differential valve 1C port, and then flows into the bleed valve 5B port through the minimum pressure parking valve 2C port. At this time, the spring cavity of the bleed valve 5 is under high pressure, pushing the steel ball 3 to move outward close to the end face of the bleed valve 5, and the low-pressure fuel cannot flow into the bleed valve 5C port, ending the automatic bleed stage, thereby realizing the automatic conversion of automatic bleed to induced oil return function.

[0025] Furthermore, the pumped fuel returns to the aircraft fuel tank through the pressure differential valve 1, the minimum pressure valve 2, and the spring chamber of the bleed valve 5.

[0026] Furthermore, when the engine is not started, since the minimum pressure parking valve is not opened, the B port and the C port of the minimum pressure parking valve are not connected, the priming passage is in a closed state, and the spring chamber of the bleed valve is basically pressure-free. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the flow passage through the A port of the bleed valve and returns to the fuel tank to bleed the system: when the engine is started, the minimum pressure parking valve is opened, and the B port and the C port of the minimum pressure parking valve are connected, the priming passage is established, and the priming fuel enters through the B port of the bleed valve, passes through the spring chamber of the bleed valve, and flows out from the C port to the aircraft mailbox. Since the priming fuel is high-pressure fuel, the priming fuel together with the spring will push the steel ball to the left, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve.

[0027] Example

[0028] like Figure 1 As shown, the integrated assembly device of the present invention is composed of a pressure differential valve 1, a minimum pressure parking valve 2, a steel ball 3, a spring 4, and a bleed valve 5. The steel ball 3 and the spring 4 are installed in the bleed valve 5 to form an automatic bleed device, which is placed at the top of the fuel pump regulator to facilitate gas discharge. Before the fuel pump regulator is started, since the high-pressure pump is not started, the fuel after the pump and the fuel after metering are both low-pressure fuel. The low-pressure return oil enters through the bleed valve 5A port to push the steel ball 3 to overcome the spring force of the spring 4, and the gas is discharged through the bleed valve 5C port;

[0029] After the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both high-pressure fuel. The metered fuel enters the engine combustion chamber through the minimum pressure parking valve. The fuel after the pump first meets the metered fuel use of the engine. The excess fuel is divided into two paths. One path returns to the front of the gear pump through the pressure differential valve 1B port to fill the gear pump inlet fuel. The other path enters the low-pressure chamber of the minimum pressure parking valve 2 through the pressure differential valve 1C port, and then flows into the bleed valve SB port through the minimum pressure parking valve 2D port. At this time, the bleed valve 5

[0030] The spring chamber is at high pressure, pushing the steel ball 3 to the left close to the end face of the bleed valve 5. The low-pressure fuel cannot flow into the bleed valve SC port, ending the automatic bleed stage, thereby realizing the automatic conversion of automatic bleed to induced oil return function. The pumped fuel returns to the aircraft fuel tank through the pressure differential valve 1, the minimum pressure valve 2, and the bleed valve S spring chamber. Because part of the pumped fuel flows out of the fuel pump regulator, the fuel pump regulator does not generate temperature rise, thereby reducing the temperature rise. At the same time, the induced fuel can reversely heat the fuel in the fuel tank, reducing the probability of fuel freezing during high-altitude flight of the aircraft.

[0031] The function of the pressure differential valve is to ensure that the pressure difference before and after the metering valve of the fuel pump regulator is basically constant. A total of 3 oil holes are set. Port A is the oil inlet, and the fuel after the gear pump flows into the pressure differential valve through port A; Port B is the oil return port, and part of the fuel after the pump returns to the front of the gear pump through port B: Port C is the oil outlet. During the operation of the engine, part of the oil after the pump is converted into induced return oil through port C, and flows into the aircraft fuel tank through the minimum pressure valve and the bleed valve.

[0032] The function of the minimum pressure parking valve is to ensure that the fuel inside the fuel pump regulator has a certain pressure to ensure the normal operation of the servo system. The minimum pressure parking valve opens when the pressure reaches the specified value after metering. A total of 4 oil holes are set, port A is the oil inlet, port D is the oil outlet, and the fuel after metering valve flows into the minimum pressure parking valve through port A, pushes the valve core to move and then flows out to the engine combustion chamber through port D; port B is the oil inlet, and port C is the oil outlet. When the engine starts, the minimum pressure parking valve opens, and ports B and C are connected only through the valve core annular cavity. The injected fuel enters the minimum pressure parking valve through port B, passes through the valve core annular cavity, and flows out from port C to the vent valve.

[0033] The bleed valve is set on the passage between the front of the gear pump and the ejection outlet, and a total of 3 oil holes are set. Port A is the low-pressure fuel inlet, port B is the ejection fuel inlet, and port C is the ejection fuel outlet. When the aircraft / vehicle booster pump is started and the engine is not started, since the minimum pressure parking valve is not opened, the port B of the minimum pressure parking valve is not connected to the port C, the ejection passage is in a closed state, and the spring chamber of the bleed valve is basically pressure-free. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the dynamic flow passage through the port A of the bleed valve to return to the fuel tank, and the system is bleed: when the engine is started, the minimum pressure parking valve is opened, the port B of the minimum pressure parking valve is connected to the port C, the ejection passage is established, and the ejection fuel enters through the port B of the bleed valve, passes through the spring chamber of the bleed valve, and flows out from the port C to the aircraft mailbox. Since the ejection fuel is high-pressure fuel, the ejection fuel together with the spring will push the steel ball to move to the left, close the low-pressure fuel from the port A, and realize the automatic closing of the bleed valve.

[0034] The above is only a specific embodiment of the present invention, and the present invention is described in detail. The unexplained part is a conventional technology. However, the protection scope of the present invention is not limited to this. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. The protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. An integrated device for automatic air release and oil return injection of an engine fuel control system, characterized in that: include: A pressure differential valve (1), a minimum pressure parking valve (2), a steel ball (3), a spring (4), and a deflation valve (5); wherein the steel ball (3) is installed in the spring cavity of the deflation valve (5) through the spring (4) to form an automatic deflation device, the diameter of the steel ball (3) matches the inner diameter of the spring cavity, the steel ball (3) can block the spring cavity and move axially therein, the pressure differential valve (1) is used to ensure that the pressure differential before and after the metering valve of the fuel pump regulator is basically constant, the pressure differential valve (1) A port is the oil inlet, and the gear pump afterburner The oil flows into the differential pressure valve (1) through the differential pressure valve (1) port A; the differential pressure valve (1) port B is the oil return port, and part of the fuel after the pump returns to the front of the gear pump through the differential pressure valve (1) port B, and the differential pressure valve (1) port C is the oil outlet; the minimum pressure stop valve (2) is used to adjust the fuel pressure inside the fuel pump regulator. The minimum pressure stop valve (2) port A is the oil inlet, and the minimum pressure stop valve (2) port D is the oil outlet. The fuel after the metering valve flows into the minimum pressure stop valve through the minimum pressure stop valve (2) port A, pushing After the moving valve core moves, the fuel flows out through the D port of the minimum pressure stop valve (2) to the engine combustion chamber; the B port of the minimum pressure stop valve (2) is the oil inlet, and the C port of the minimum pressure stop valve (2) is the oil outlet. When the engine is started, the minimum pressure stop valve (2) is opened, and the B port and the C port are connected only through the valve core annular cavity. The injected fuel enters the minimum pressure stop valve (2) through the B port of the minimum pressure stop valve (2), passes through the valve core annular cavity, and flows out from the C port of the minimum pressure stop valve (2) to the vent valve. The vent valve (5) The device is arranged on the passage between the front of the gear pump and the injection outlet, wherein the A port of the bleed valve (5) is the low-pressure fuel inlet, the B port of the bleed valve (5) is the injection fuel inlet, and the C port of the bleed valve (5) is the injection fuel outlet. When the minimum pressure parking valve (2) is not opened, the B port and the C port of the minimum pressure parking valve (2) are not connected, the injection passage is in a closed state, the spring chamber of the bleed valve (5) has no pressure, and the low-pressure fuel in front of the gear pump overcomes the spring force and enters the dynamic flow passage through the A port of the bleed valve (5) and returns to the oil tank, thereby bleeding the system.

2. The device according to claim 1, characterized in that The automatic air bleed device is installed at the uppermost part of the fuel pump regulator.

3. An integrated method for automatic air bleed and oil return injection of an engine fuel control system, characterized in that: Using any of the devices as described in claims 1-2, comprising: when the engine is started, the minimum pressure parking valve (2) is opened, the B port of the minimum pressure parking valve (2) is connected to the C port, an induced passage is established, and the induced fuel enters through the B port of the bleed valve (5), passes through the spring chamber of the bleed valve (5), and flows out from the C port to the aircraft mailbox. Since the induced fuel is high-pressure fuel, the induced fuel together with the spring will push the steel ball to move outward, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve (5).

4. The method according to claim 3, characterized in that The minimum pressure stop valve (2) opens when the pressure after metering reaches a specified value.

5. The method according to claim 3, characterized in that: Before the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both low-pressure fuel, and the low-pressure return oil is connected to the A port of the bleed valve (5). The steel ball (3) overcomes the spring force of the spring (4), and the gas is discharged through the C port of the bleed valve (5).

6. The method according to claim 3, characterized in that After the fuel pump regulator is started, the fuel after the pump and the fuel after metering are both high-pressure fuel. The metered fuel is connected to the engine combustion chamber through the minimum pressure stop valve (2) and is divided into two paths. One path returns to the front of the gear pump through the B port of the pressure difference valve (1), and the other path enters the low-pressure cavity of the minimum pressure stop valve (2) through the C port of the pressure difference valve (1), and then flows into the B port of the bleed valve (5) through the C port of the minimum pressure stop valve (2). At this time, the spring cavity of the bleed valve (5) is high pressure, pushing the steel ball (3) outward to move close to the end surface of the bleed valve (5), and the low-pressure fuel cannot flow into the C port of the bleed valve (5), ending the automatic bleed stage, thereby realizing the automatic conversion of automatic bleed to induced oil return function.

7. The method according to claim 3, characterized in that After the pump, the fuel returns to the aircraft fuel tank through the pressure differential valve (1), the minimum pressure valve (2) and the spring chamber of the air release valve (5).

8. The method according to claim 3, characterized in that When the engine is not started, since the minimum pressure parking valve is not opened, the B port and C port of the minimum pressure parking valve are not connected, the priming passage is in a closed state, and the spring chamber of the bleed valve is basically pressure-free. The low-pressure fuel in front of the gear pump overcomes the spring force and enters the flow passage through the A port of the bleed valve and returns to the fuel tank to bleed the system. When the engine is started, the minimum pressure parking valve opens, and the B port and C port of the minimum pressure parking valve are connected. The priming passage is established, and the priming fuel enters through the B port of the bleed valve, passes through the spring chamber of the bleed valve, and flows out from the C port to the aircraft mailbox. Since the priming fuel is high-pressure fuel, the priming fuel together with the spring will push the steel ball to the left, closing the low-pressure fuel from the A port, thereby realizing the automatic closing of the bleed valve.

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