Integrated fuel pump regulator and aeroengine

Abstract

The present invention discloses an integrated fuel pump regulator, which includes a fuel boosting and supply module for boosting and supplying fuel, a fuel regulation module communicated with the fuel boosting and supply module for measuring fuel flow rate and regulating fuel supply for guide vane actuation, a starting air release module connected to the fuel regulation module for air release during engine starting, an ejector module communicated with the fuel regulation module for ejecting fuel to the aircraft fuel tank during fuel return, and a shutdown module communicated with the fuel regulation module for cutting off fuel supply to stop the aircraft engine. The fuel boosting and supply module, the fuel regulation module, the starting air release module, the ejector module and the shutdown module are integrated into the same accessory. The fuel boosting and supply module includes a low-pressure pump and a high-pressure pump communicated with the low-pressure pump, and the high-pressure pump and the low-pressure pump are coaxially arranged. The fuel regulation module includes a guide vane electro-hydraulic servo valve communicated with the high-pressure pump. In addition, the present invention also discloses an aeroengine.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engine fuel system design, and in particular, to an integrated fuel pump regulator. In addition, the present invention also relates to an aero-engine including the above fuel pump regulator. Background Art

[0002] The fuel system is an important system of the engine. Its functional modules mainly include a fuel boosting and supply module, a low-pressure filtering module, a fuel regulation module, an ejector module, a starting air release module, a shutdown module, a fuel distribution module, etc. The required functional modules are determined according to the overall requirements, and each functional module is integrated into different fuel system accessories.

[0003] At present, the fuel distribution module and the low-pressure filtering module of the fuel system of medium and small aero-engines are generally separate accessories, and the remaining functional modules are integrated into one or two accessories. The fuel boosting and supply module is generally composed of a low-pressure pump and a high-pressure pump, and there are two design schemes: a split design and a combined design. In the split design, the low-pressure pump and the high-pressure pump are not in the same accessory and are driven by two transmission shafts driven by the accessory respectively. The low-pressure pump is a separate accessory, and the high-pressure pump is integrated into the fuel regulation module. In the combined design, the low-pressure pump and the high-pressure pump are integrated into one accessory and are driven by one transmission shaft driven by the accessory. The combined fuel pump is a separate accessory or integrated into the fuel regulation module.

[0004] However, in the existing fuel pump regulators, the starting air release module is integrated into the fuel regulation module in some cases, into the fuel distribution module in some cases, and onto the accessory case in some cases. The shutdown module is integrated into the fuel regulation module in some cases and into the fuel distribution module in some cases. And there is no design scheme with a guide vane control function and an integrated ejector module. As a result, the fuel pump regulator is composed of multiple accessories spliced together, which further leads to a large number of installation interfaces and external connection pipelines for the existing engine accessories, thus making the total weight of the existing fuel system accessories large, the structure complex, and once the ejector module is not integrated, according to the working principle of the high-pressure pump, under the condition of fixed modulus and number of teeth, its fuel supply only depends on the speed. Therefore, the fuel supply of the high-pressure pump under certain working conditions far exceeds the metering flow, and the excess fuel will all return to the inlet of the high-pressure pump, resulting in a large amount of internal fuel circulation, causing the fuel temperature to rise and the fuel inlet conditions to be poor. Summary of the Invention

[0005] The present invention provides an integrated fuel pump regulator and an aero-engine to solve the technical problems that the existing fuel pump regulator is composed of multiple accessories spliced together, with a large number of accessories, large weight, complex structure, and may not integrate the ejector module, which easily leads to a rise in fuel temperature and poor fuel inlet conditions.

[0006] According to one aspect of the present invention, an integrated fuel pump regulator is provided, which includes a fuel boosting and supply module for boosting fuel supply, a fuel regulation module communicated with the fuel boosting and supply module for measuring fuel flow rate and regulating fuel supply for guide vane actuation, a starting air release module connected to the fuel regulation module for air release during engine starting, an ejector module communicated with the fuel regulation module for ejecting fuel into the aircraft fuel tank during fuel return, and a shutdown module communicated with the fuel regulation module for cutting off fuel supply to stop the aircraft engine. The fuel boosting and supply module, the fuel regulation module, the starting air release module, the ejector module and the shutdown module are integrated into the same accessory. The fuel boosting and supply module includes a low-pressure pump for primary boosting of fuel and a high-pressure pump communicated with the low-pressure pump for further boosting of the primarily boosted fuel. The high-pressure pump and the low-pressure pump are coaxially arranged. The fuel regulation module includes a guide vane electro-hydraulic servo valve communicated with the high-pressure pump for controlling the fuel supply guide vane actuator to control the displacement of the guide vane actuator and thus control the guide vane angle.

[0007] As a further improvement of the above technical solution:

[0008] Further, the fuel regulation module includes a metering valve communicated with the high-pressure pump for measuring fuel flow rate, a differential pressure valve respectively communicated with the metering valve and the high-pressure pump for ensuring stable differential pressure before and after the metering valve and at the same time returning the excess fuel to the high-pressure pump, a metering electro-hydraulic servo valve communicated with the metering valve for controlling the movement of the metering valve to change the outlet flow rate of the fuel pump regulator, a constant pressure valve communicated with the metering valve for providing constant pressure oil for the metering valve and the metering electro-hydraulic servo valve, and an electronic controller respectively electrically connected to the metering valve, the metering electro-hydraulic servo valve and the guide vane electro-hydraulic servo valve for realizing coordinated control.

[0009] Further, the fuel regulation module further includes an after-pump oil filter disposed between the high-pressure pump and the metering valve for coarsely filtering the fuel.

[0010] Further, the fuel regulation module further includes a servo oil filter disposed between the after-pump oil filter, the constant pressure valve, the metering valve, the differential pressure valve, the metering electro-hydraulic servo valve and the guide vane electro-hydraulic servo valve for finely filtering the coarsely filtered fuel.

[0011] Further, the fuel regulation module further includes a return oil filter disposed between the high-pressure pump and the constant pressure valve for preventing impurities in the inlet fuel from reversely entering the constant pressure valve during inlet pressurization before engine starting.

[0012] Further, the fuel regulation module further includes a displacement sensor disposed on the metering valve and electrically connected to the electronic controller for obtaining the displacement signal of the metering valve spool and transmitting it into the electronic controller.

[0013] Furthermore, a temperature compensation structure for achieving a constant fuel flow rate at different medium temperatures is provided on the differential pressure valve.

[0014] Furthermore, the parking module includes a minimum pressure parking valve connected to the metering valve for ensuring a certain pressure of the fuel inside the fuel pump regulator during the engine starting phase, a dual-channel parking solenoid valve electrically connected to the electronic controller for cutting off the fuel supply to the combustion chamber after receiving the electrical parking signal from the electronic controller to achieve engine parking, and a single-channel emergency parking solenoid valve for connecting to the aircraft cockpit to cut off the fuel supply to the combustion chamber after receiving the emergency parking signal from the pilot to achieve engine parking.

[0015] The fuel boosting and supply module further includes a safety valve connected to the high-pressure pump for preventing damage to the fuel system caused by excessive fuel pressure after the high-pressure pump.

[0016] According to another aspect of the present invention, an aeroengine is further provided, which includes the integrated fuel pump regulator described above.

[0017] The present invention has the following beneficial effects:

[0018] For the integrated fuel pump regulator of the present invention, the external fuel first enters the fuel boosting and supply module for pressurization to have sufficient oil pressure to flow through the oil circuit. The fuel flow rate is metered by the fuel regulation module and the guide vane is actuated to supply fuel to ensure smooth fuel flow. The fuel supply guide vane actuator is controlled by the guide vane electro-hydraulic servo valve to control the displacement of the guide vane actuator and thus control the guide vane angle. The starting air release module releases air during engine starting to discharge the gas in front of the high-pressure pump in the fuel system of the engine to ensure smooth engine starting. The ejector module can eject fuel to the aircraft fuel tank during fuel return. Finally, the parking module cuts off the fuel supply to the combustion chamber to stop the aircraft engine. By integrating the fuel boosting and supply module, fuel regulation module, starting air release module, ejector module, and parking module into the same accessory, the number of accessories in the fuel system and the external fuel pipelines are reduced, and the total weight of the fuel system accessories is reduced. The fuel is pressurized by the low-pressure pump and high-pressure pump, and since the low-pressure pump and high-pressure pump are coaxially designed, they can be driven by the same transmission shaft of the accessory drive, simplifying the accessory drive. At the same time, compared with the prior art, the fuel pump regulator is provided with two types of fuel return paths through the ejector module. One path is low-pressure fuel return to the inlet of the high-pressure pump, and the other path is fuel return to the aircraft fuel tank. When the fuel supply of the high-pressure pump far exceeds the metering flow rate under certain conditions, the excess fuel can be ejected into the aircraft fuel tank through the ejector module while ensuring sufficient filling at the inlet of the high-pressure pump, thereby reducing the temperature rise of the fuel system and effectively improving the inlet conditions of the low-pressure pump.

[0019] In addition to the purposes, features, and advantages described above, the present invention has other purposes, features, and advantages. The present invention will be further described in detail below with reference to the drawings. Description of the Drawings

[0020] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0021] Figure 1 is a structural block diagram of an integrated fuel pump regulator according to a preferred embodiment of the present invention.

[0022] Legend Explanation:

[0023] 1. Fuel Boosting and Supply Module; 11. Low-pressure Pump; 12. High-pressure Pump; 13. Safety Valve; 2. Fuel Regulation Module; 21. Metering Valve; 22. Differential Pressure Valve; 23. Metering Electro-hydraulic Servo Valve; 24. Constant Pressure Valve; 25. Guide Vane Electro-hydraulic Servo Valve; 26. Post-pump Oil Filter; 27. Servo Oil Filter; 28. Return Oil Filter; 3. Starting Air Bleed Module; 4. Ejector Module; 5. Stop Module; 51. Minimum Pressure Stop Valve; 52. Dual-channel Stop Solenoid Valve; 53. Single-channel Emergency Stop Solenoid Valve; 6. Fuel Distribution Module; 7. Guide Vane Actuating Cylinder; 8. Aircraft Fuel Tank; 9. Accessory Drive; 10. Filter and Heating Module. Detailed Embodiment

[0024] The embodiments of the present invention will be described in detail below with reference to the drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0025] Figure 1 is a structural block diagram of an integrated fuel pump regulator according to a preferred embodiment of the present invention.

[0026] As Figure 1As shown in the figure, the integrated fuel pump regulator of this embodiment includes a fuel pressurization and supply module 1 for pressurizing and supplying fuel, a fuel regulation module 2 connected to the fuel pressurization and supply module 1 for measuring the fuel flow rate and regulating the fuel supply for the guide vane actuation, a starting air release module 3 connected to the fuel regulation module 2 for releasing air during engine starting, an injection module 4 connected to the fuel regulation module 2 for injecting fuel into the aircraft fuel tank 8 during fuel return, and a shutdown module 5 connected to the fuel regulation module 2 for cutting off the fuel supply to stop the aircraft engine. The fuel pressurization and supply module 1, the fuel regulation module 2, the starting air release module 3, the injection module 4, and the shutdown module 5 are integrated into the same accessory. The fuel pressurization and supply module 1 includes a low-pressure pump 11 for primary pressurization of the fuel and a high-pressure pump 12 connected to the low-pressure pump 11 for further pressurization of the primary pressurized fuel. The high-pressure pump 12 and the low-pressure pump 11 are coaxially arranged. Specifically, for the integrated fuel pump regulator of the present invention, the external fuel first enters the fuel pressurization and supply module 1 for pressurization to have sufficient oil pressure to flow through the oil circuit. The fuel regulation module 2 measures the fuel flow rate and regulates the fuel supply to ensure smooth fuel flow. The starting air release module 3 releases air during engine starting to discharge the gas in front of the high-pressure pump 12 in the fuel system of the engine to ensure smooth engine starting. The injection module 4 can inject fuel into the aircraft fuel tank 8 during fuel return. Finally, the shutdown module 5 cuts off the fuel supply to the combustion chamber to stop the aircraft engine. By integrating the fuel pressurization and supply module 1, the fuel regulation module 2, the starting air release module 3, the injection module 4, and the shutdown module 5 into the same accessory, the number of accessories in the fuel system and the external fuel pipelines are reduced, and the total weight of the fuel system accessories is reduced. The fuel is pressurized by the low-pressure pump 11 and the high-pressure pump 12, and since the low-pressure pump 11 and the high-pressure pump 12 are coaxially designed, they can be driven by the same transmission shaft of the accessory drive 9, simplifying the accessory drive 9. At the same time, compared with the prior art, the fuel pump regulator is provided with two types of fuel return paths through the injection module 4. One path is low-pressure fuel return to the inlet of the high-pressure pump 12, and the other path is fuel return to the aircraft fuel tank 8. When the fuel supply amount of the high-pressure pump 12 far exceeds the metering flow rate under certain working conditions, and while ensuring sufficient filling at the inlet of the high-pressure pump 12, the excess fuel can be injected into the aircraft fuel tank 8 through the injection module 4, thereby reducing the temperature rise of the fuel system and effectively improving the inlet conditions of the low-pressure pump 11. It should be understood that the first outlet of the low-pressure pump 11 is connected to the first inlet of the high-pressure pump 12.

[0027] As Figure 1As shown in the figure, in this embodiment, the fuel regulation module 2 includes a metering valve 21 for measuring the fuel flow rate and communicating with the high-pressure pump 12, a differential pressure valve 22 for ensuring the stable differential pressure before and after the metering valve 21 and returning the excess fuel to the high-pressure pump 12 while communicating with both the metering valve 21 and the high-pressure pump 12, a metering electro-hydraulic servo valve 23 for controlling the movement of the metering valve 21 to change the outlet flow rate of the fuel pump regulator and communicating with the metering valve 21, a constant pressure valve 24 for providing constant pressure oil for the metering valve 21 and the metering electro-hydraulic servo valve 23 and communicating with the metering valve 21, and an electronic controller for realizing coordinated control and electrically connected to the metering valve 21, the metering electro-hydraulic servo valve 23, and the guide vane electro-hydraulic servo valve 25 respectively. Specifically, the first outlet of the high-pressure pump 12 is communicated with the first inlet of the metering valve 21, the first outlet of the metering valve 21 is communicated with the first inlet of the differential pressure valve 22, the first outlet of the differential pressure valve 22 is communicated with the second inlet of the high-pressure pump 12, the second outlet of the metering valve 21 is communicated with the first inlet of the metering electro-hydraulic servo valve 23, the third outlet of the metering valve 21 is communicated with the second inlet of the metering electro-hydraulic servo valve 23, the first outlet of the constant pressure valve 24 is communicated with the second inlet of the metering valve 21, the first outlet of the high-pressure pump 12 is communicated with the first inlet of the guide vane electro-hydraulic servo valve 25. The fuel is pressurized again by the high-pressure pump 12 and then enters the metering valve 21 successively through the first outlet of the high-pressure pump 12 and the first inlet of the metering valve 21. The metering valve 21 accurately measures the fuel flow rate of the engine according to the signal of the electronic controller. The fuel then enters the differential pressure valve 22 successively through the first outlet of the metering valve 21 and the first inlet of the differential pressure valve 22. The differential pressure valve 22 keeps the differential pressure before and after the metering valve 21 stable to ensure smooth fuel flow, and at the same time, the excess fuel returns to the high-pressure pump 12 successively through the first outlet of the differential pressure valve 22 and the second inlet of the high-pressure pump 12 to assist in fuel metering. The metering electro-hydraulic servo valve 23 modulates the control chamber pressure of the metering valve 21 according to the given current of the electronic controller to control the movement of the metering valve 21 to the desired equilibrium position, thereby changing the outlet flow rate of the fuel pump regulator. The constant pressure oil in the constant pressure valve 24 enters the metering valve 21 successively through the first outlet of the constant pressure valve 24 and the second inlet of the metering valve 21 to provide constant pressure oil for the metering valve 21, and then enters the metering electro-hydraulic servo valve 23 successively through the third outlet of the metering valve 21 and the second inlet of the metering electro-hydraulic servo valve 23 to provide constant pressure oil for the metering electro-hydraulic servo valve 23. The fuel pressurized again in the high-pressure pump 12 also flows through the first outlet of the high-pressure pump 12 and the first inlet of the guide vane electro-hydraulic servo valve 25 into the guide vane electro-hydraulic servo valve 25 successively. The guide vane electro-hydraulic servo valve 25 modulates the fuel supply to the rod chamber and the rodless chamber of the guide vane actuator 7 according to the control instruction of the electronic controller, and then controls the displacement of the guide vane actuator 7, thereby controlling the guide vane angle.It should be understood that the specific structures of the metering valve 21, differential pressure valve 22, metering electro-hydraulic servo valve 23, constant pressure valve 24 and guide vane electro-hydraulic servo valve 25 are well-known technologies to those skilled in the art, and will not be elaborated here. Optionally, the electronic controller is a PLC controller. It should be understood that the specific structure of the PLC controller is well-known to those skilled in the art and will not be elaborated here.

[0028] As Figure 1 shown, in this embodiment, the fuel regulation module 2 further includes a post-pump oil filter 26 disposed between the high-pressure pump 12 and the metering valve 21 for roughly filtering the fuel. Specifically, the first outlet of the high-pressure pump 12 is communicated with the first inlet of the post-pump oil filter 26, and the first outlet of the post-pump oil filter 26 is communicated with the first inlet of the metering valve 21. The fuel pressurized again in the high-pressure pump 12 flows through the first outlet of the high-pressure pump 12 and the first inlet of the post-pump oil filter 26 in sequence and enters the post-pump oil filter 26. The post-pump oil filter 26 can filter out larger contaminants generated by the wear of the high-pressure pump 12 to roughly filter the pressurized fuel and ensure the cleanliness of the fuel supplied to the metering valve 21 and the differential pressure valve 22. It should be understood that the specific structure of the post-pump oil filter 26 is well-known to those skilled in the art and will not be elaborated here.

[0029] As Figure 1 shown, in this embodiment, the fuel regulation module 2 further includes a servo oil filter 27 disposed between the post-pump oil filter 26, constant pressure valve 24, metering valve 21, differential pressure valve 22, metering electro-hydraulic servo valve 23 and guide vane electro-hydraulic servo valve 25 for finely filtering the roughly filtered fuel. Specifically, the second outlet of the post-pump oil filter 26 is communicated with the first inlet of the servo oil filter 27, and the first outlet of the servo oil filter 27 is respectively communicated with the third inlet of the metering valve 21, the first inlet of the constant pressure valve 24, the second inlet of the differential pressure valve 22 and the first inlet of the guide vane electro-hydraulic servo valve 25. The roughly filtered fuel in the post-pump oil filter 26 flows through the second outlet of the post-pump oil circuit and the first inlet of the servo oil filter 27 in sequence and enters the servo oil circuit. The servo oil filter 27 finely filters the roughly filtered fuel to ensure the high cleanliness of the fuel supplied to the constant pressure valve 24, metering valve 21, differential pressure valve 22 and guide vane electro-hydraulic servo valve 25. It should be understood that the specific structure of the servo oil filter 27 is well-known to those skilled in the art and will not be elaborated here.

[0030] As Figure 1As shown, in this embodiment, the fuel regulation module 2 further includes an oil return filter 28 disposed between the high-pressure pump 12 and the constant-pressure valve 24, which is used to prevent impurities in the inlet fuel from flowing back into the constant-pressure valve 24 when the inlet is pressurized before the engine starts. Specifically, the second outlet of the constant-pressure valve 24 is connected to the second inlet of the high-pressure pump 12. The oil return filter 28 prevents impurities in the inlet fuel from flowing back into the constant-pressure valve 24 when the fuel pump regulator inlet is pressurized before the engine starts, thereby preventing the constant-pressure valve 24 from jamming and even causing blockages in the metering valve 21, differential pressure valve 22, metering electro-hydraulic servo valve 23, and guide vane electro-hydraulic servo valve 25. It should be understood that the specific structure of the oil return filter 28 is well-known to those skilled in the art and will not be elaborated here.

[0031] As Figure 1 shown, in this embodiment, the fuel regulation module 2 further includes a displacement sensor disposed on the metering valve 21 and electrically connected to the electronic controller, which is used to obtain the displacement signal of the metering valve 21 and transmit it to the electronic controller. Specifically, the displacement sensor measures and calculates the spool position of the metering valve 21 to convert the physical displacement of the metering valve 21 into an electrical signal and feedback it to the electronic controller, so as to cooperate with the metering electro-hydraulic servo valve 23 to achieve closed-loop control of the movement of the metering valve 21. It should be understood that the specific structure of the displacement sensor is well-known to those skilled in the art and will not be elaborated here.

[0032] As Figure 1 shown, in this embodiment, a temperature compensation structure for keeping the fuel flow rate constant at different medium temperatures is arranged on the differential pressure valve 22. Specifically, through the temperature compensation structure, the fuel flow rate is kept constant at different medium temperatures, thereby improving the accuracy of the metering throttle for metering the fuel flow rate. It should be understood that the specific structure of the temperature compensation structure is well-known to those skilled in the art and will not be elaborated here.

[0033] As Figure 1As shown in the figure, in this embodiment, the parking module 5 includes a minimum pressure parking valve 51 that communicates with the metering valve 21 and is used to ensure a certain pressure of the fuel inside the fuel pump regulator during the engine starting stage, a dual-channel parking solenoid valve 52 that is electrically connected to the electronic controller and is used to cut off the fuel supply to the combustion chamber after receiving the electrical parking signal from the electronic controller to achieve engine shutdown, and a single-channel emergency parking solenoid valve 53 that is used to connect with the aircraft cockpit to cut off the fuel supply to the combustion chamber after receiving the emergency parking signal from the pilot and then achieve engine shutdown. Specifically, the fourth outlet of the metering valve 21 communicates with the first inlet of the minimum pressure parking valve 51, the first outlet of the metering valve 21 also communicates with the first inlet of the dual-channel parking solenoid valve 52 and the first inlet of the single-channel emergency parking solenoid valve 53 respectively, the first outlet of the minimum pressure parking valve 51 communicates with the second inlet of the dual-channel parking solenoid valve 52 and the second inlet of the single-channel emergency parking solenoid valve 53 respectively. By receiving the parking signal from the electronic controller through the dual-channel parking solenoid valve 52 or the emergency parking signal from the pilot in the aircraft cockpit through the single-channel emergency parking solenoid valve 53, the fuel supply to the combustion chamber is cut off to achieve engine shutdown. The minimum pressure parking valve 51 opens when the pressure of the fuel after metering reaches the specified value to ensure a certain pressure of the fuel inside the fuel pump regulator during the starting stage, so that the fuel system can work properly.

[0034] As Figure 1 shown in the figure, in this embodiment, the fuel boosting and supply module 1 further includes a safety valve 13 that communicates with the high-pressure pump 12 and is used to prevent damage to the fuel system caused by excessive fuel pressure after the high-pressure pump 12. Specifically, the second outlet of the high-pressure pump 12 communicates with the first inlet of the safety valve 13, the first outlet of the safety valve 13 communicates with the first inlet of the post-pump fuel filter 26. The safety valve 13 opens when the pressure at the outlet of the high-pressure pump 12 reaches the design value to guide the fuel at the outlet of the high-pressure pump 12 to the inlet of the high-pressure pump 12, preventing damage to the fuel system due to excessive pressure at the outlet of the high-pressure pump 12.

[0035] As Figure 1As shown, the aero-engine of this embodiment includes the above-mentioned integrated fuel pump regulator. Specifically, by adopting the integrated fuel pump regulator, the number of fuel system accessories and external fuel pipelines are reduced, the total weight of the fuel system accessories is reduced, while the accessory drive 9 is simplified, and an ejector module 4 is added to reduce the temperature rise of the fuel system, effectively improving the inlet conditions of the low-pressure pump 11, that is, reducing the internal pressure of the low-pressure pump 11 to achieve negative pressure oil suction. Optionally, the aero-engine further includes a fuel distribution module 6 connected to the fuel pump regulator for distributing fuel, a guide vane actuator 7 connected to the guide vane electro-hydraulic servo valve 25 for controlling the guide vane angle, an accessory drive 9 connected to the low-pressure pump 11 for driving the low-pressure pump 11 to work, and an aircraft fuel tank 8 connected to the fuel pump regulator. Optionally, the aero-engine further includes a filter heating module 10 connected to the low-pressure pump 11 for filtering and heating fuel.

[0036] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. An integrated fuel pump regulator, characterized in that, It includes a fuel boosting and supply module (1) for boosting fuel supply, a fuel regulating module (2) connected to the fuel boosting and supply module (1) for measuring fuel flow rate and regulating the fuel supply for guide vane actuation, a starting air release module (3) connected to the fuel regulating module (2) for air release during engine starting, an ejector module (4) connected to the fuel regulating module (2) for ejecting fuel to the aircraft fuel tank (8) during fuel return, and a shutdown module (5) connected to the fuel regulating module (2) for cutting off fuel supply to stop the aircraft engine. The fuel boosting and supply module (1), the fuel regulating module (2), the starting air release module (3), the ejector module (4) and the shutdown module (5) are integrated into the same accessory. The fuel boosting and supply module (1) includes a low-pressure pump (11) for primary boosting of fuel and a high-pressure pump (12) connected to the low-pressure pump (11) for secondary boosting of the primarily boosted fuel. The high-pressure pump (12) and the low-pressure pump (11) are arranged coaxially. The fuel regulating module (2) includes a guide vane electro-hydraulic servo valve (25) connected to the high-pressure pump (12) for controlling the fuel supply guide vane actuator (7) to control the displacement of the guide vane actuator (7) and thus control the guide vane angle. The ejector module (4) enables the fuel pump regulator to have two types of fuel return passages. One is for low-pressure fuel return to the inlet of the high-pressure pump (12), and the other is for fuel return to the aircraft fuel tank (8). When the fuel supply of the high-pressure pump (12) far exceeds the metering flow rate under certain conditions, the ejector module (4) can eject the excess fuel into the aircraft fuel tank (8) while ensuring sufficient filling at the inlet of the high-pressure pump (12), thereby reducing the temperature rise of the fuel system and effectively improving the inlet conditions of the low-pressure pump (11). The fuel regulating module (2) includes a metering valve (21) connected to the high-pressure pump (12) for measuring fuel flow rate, a differential pressure valve (22) connected to both the metering valve (21) and the high-pressure pump (12) for ensuring stable differential pressure before and after the metering valve (21) and returning the excess fuel to the high-pressure pump (12), a metering electro-hydraulic servo valve (23) connected to the metering valve (21) for controlling the movement of the metering valve (21) to change the outlet flow rate of the fuel pump regulator, a constant pressure valve (24) connected to the metering valve (21) for providing constant pressure oil for the metering valve (21) and the metering electro-hydraulic servo valve (23), and an electronic controller electrically connected to the metering valve (21), the metering electro-hydraulic servo valve (23) and the guide vane electro-hydraulic servo valve (25) for realizing coordinated control.

2. The integrated fuel pump regulator according to claim 1, characterized in that, The fuel regulating module (2) further includes an after-pump oil filter (26) disposed between the high-pressure pump (12) and the metering valve (21) for rough filtering of fuel.

3. The integrated fuel pump regulator according to claim 2, characterized in that, The fuel regulating module (2) further includes a servo oil filter (27) disposed between the after-pump oil filter (26), the constant pressure valve (24), the metering valve (21), the differential pressure valve (22), the metering electro-hydraulic servo valve (23) and the guide vane electro-hydraulic servo valve (25) for fine filtering of the roughly filtered fuel.

4. The integrated fuel pump regulator according to claim 1, characterized in that, The fuel regulation module (2) further includes a return oil filter (28) disposed between the high-pressure pump (12) and the constant-pressure valve (24) for preventing impurities in the inlet fuel from reversely entering the constant-pressure valve (24) during inlet pressurization before engine startup.

5. The integrated fuel pump regulator according to claim 1, characterized in that, The fuel regulation module (2) further includes a displacement sensor disposed on the metering valve (21) and electrically connected to the electronic controller for obtaining the displacement signal of the valve core of the metering valve (21) and transmitting it to the electronic controller.

6. The integrated fuel pump regulator according to claim 1, characterized in that, A temperature compensation structure for keeping the fuel flow rate constant at different medium temperatures is disposed on the differential pressure valve (22).

7. The integrated fuel pump regulator according to claim 1, characterized in that, The shutdown module (5) includes a minimum pressure shutdown valve (51) communicating with the metering valve (21) for ensuring a certain pressure of the fuel inside the fuel pump regulator during the engine startup phase, a dual-channel shutdown solenoid valve (52) electrically connected to the electronic controller for cutting off the fuel supply to the combustion chamber after receiving the electrical shutdown signal from the electronic controller to achieve engine shutdown, and a single-channel emergency shutdown solenoid valve (53) for connecting to the aircraft cockpit to cut off the fuel supply to the combustion chamber after receiving the emergency shutdown signal from the pilot to achieve engine shutdown.

8. The integrated fuel pump regulator according to any one of claims 1-7, characterized in that, The fuel boosting and supply module (1) further includes a safety valve (13) communicating with the high-pressure pump (12) for preventing damage to the fuel system caused by excessive fuel pressure after the high-pressure pump (12).

9. An aero-engine, characterized in that, It includes the integrated fuel pump regulator according to any one of claims 1-8.

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