Oil seal device of aircraft engine power system

Abstract

The invention provides an oil seal device of an aircraft engine power system, and belongs to the technical field of aircraft engine power guarantee. The aircraft engine power system oil seal device comprises a box body and an oil seal mechanism, a frame is installed on the inner wall of the box body, directional wheels are installed on the two sides of the left side of the bottom of the box body, universal wheels are installed on the two sides of the right side of the bottom of the box body, an oil tank is installed on the top of the frame, and a motor pump is installed on the top of the oil tank; the radiator is installed at the top of the frame, the oil tank communicates with the radiator, and an air filter is installed at the top of the frame. By arranging the oil seal mechanism, the oil seal mechanism can heat oil liquid, remove water in the oil liquid, prevent the oil liquid from going bad and guarantee the service life of an aircraft engine; lubricating oil is injected into the inner surface of the fuel system accessory for forced oil sealing, and hot oil sealing and unsealing can also be carried out on an engine rotor, so that the reliability and the safety of equipment are guaranteed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft engine power guarantee, and in particular, to an oil sealing device for an aircraft engine power system. Background Art

[0002] As a core sealing component, the oil seal of the aircraft engine power system undertakes the core functions of isolating lubricating media, preventing fuel / oil leakage, and blocking the intrusion of external pollutants, and its performance directly affects the reliability, fuel efficiency, and flight safety of the engine.

[0003] However, in the prior art, the operation of the aircraft engine oil seal has high requirements for the quality of the oil seal oil. In the case of water in the oil, it is easy to cause the oil to deteriorate, and it will also cause problems such as corrosion and rust of aircraft components, reducing the reliability and safety of the guarantee equipment. Summary of the Invention

[0004] To make up for the above deficiencies, the present invention provides an oil sealing device for an aircraft engine power system that overcomes the above technical problems or at least partially solves the above problems.

[0005] The present invention is implemented as follows: The present invention provides an oil sealing device for an aircraft engine power system, including a box body and an oil sealing mechanism. A frame is installed on the inner wall of the box body. Directional wheels are installed on both sides of the left side of the bottom of the box body, and universal wheels are installed on both sides of the right side of the bottom of the box body; The oil sealing mechanism includes; An oil tank, which is installed on the top of the frame, and a motor pump is installed on the top of the oil tank; A radiator, which is installed on the top of the frame, and the oil tank is communicated with the radiator. An air filter is installed on the top of the frame.

[0006] In a preferred solution, a liquid level viewing window is installed on the side of the oil tank, a fuel filling port is installed on the surface of the oil tank, and a temperature sensor is installed on the surface of the oil tank.

[0007] In a preferred solution, an electric heater is installed in the inner cavity of the oil tank, a liquid level switch is installed on the surface of the oil tank, and an oil drain port is communicated with the surface of the oil tank.

[0008] In a preferred solution, a manual reversing valve is installed on the surface of the oil tank, a suction rubber hose is communicated with the surface of the manual reversing valve, and the manual reversing valve is communicated with the motor pump. The other end of the motor pump is communicated with a first one-way valve.

[0009] In a preferred embodiment, one end of the first one-way valve away from the motor pump is connected to a coarse oil filter, the other end of the coarse oil filter is connected to a fine oil filter, and one end of the fine oil filter is connected to a logic spool valve. The end of the logic spool valve away from the fine oil filter is respectively connected to a first safety valve and a proportional overflow valve.

[0010] In a preferred embodiment, the other end of the fine oil filter is connected to a sampling interface, the end of the sampling interface away from the fine oil filter is connected to a pressure sensor, and the other end of the pressure sensor is connected to a flow meter.

[0011] In a preferred embodiment, one end of the flow meter is connected to an oil supply hose, one end of the oil supply hose is connected to an oil supply connector, a solenoid valve is installed on the surface of the oil supply connector, and the other end of the flow meter is connected to an oil supply valve.

[0012] In a preferred embodiment, the other end of the flow meter is connected to a second one-way valve, one end of the second one-way valve is connected to a second safety valve, the other end of the second one-way valve is connected to a secondary pressure reducer, and the end of the secondary pressure reducer away from the second one-way valve is connected to a primary pressure reducer.

[0013] In a preferred embodiment, the primary pressure reducer is connected to an air filter, and the other end of the air filter is connected to an inflation interface.

[0014] In a preferred embodiment, a control box is installed on the surface of the frame, a control panel is installed on the surface of the control box, an oil supply switch is installed on one side of the surface of the control box, a main power on button and a main power off button are respectively installed on the other side of the surface of the control box, and an emergency stop switch and an alarm lamp are respectively installed outside the main power on button and the main power off button.

[0015] The beneficial effects of an aircraft engine power system oil seal device provided by the present invention include: 1. By setting an oil seal mechanism, the oil seal mechanism can heat the oil liquid, remove the water in the oil liquid, avoid the deterioration of the oil liquid, ensure the service life of the aircraft engine, inject the lubricating oil into the inner surface of the fuel system accessories for forced oil seal, and can also perform hot oil seal and unsealing on the engine rotor, ensuring the reliability and safety of the equipment.

[0016] 2. By setting a second one-way valve, a safety valve, a secondary pressure reducer and a primary pressure reducer, when a series-type pressure reduction structure is adopted, the primary pressure reducer pre-reduces the inlet high pressure to an intermediate threshold, and the secondary pressure reducer performs secondary fine adjustment. By resolving the pressure shock in stages, the fluctuation range of the final output pressure is reduced to less than 1 / 3 of that of a single-stage pressure reduction, which is especially suitable for working conditions with high pressure difference and large flow rate, and can effectively avoid the sealing failure problem caused by diaphragm tremor. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention, and thus should not be regarded as limiting the scope. For those of ordinary skill in the art, without creative efforts, other related drawings can also be obtained based on these drawings; Figure 1 is a perspective view provided by an embodiment of the present invention; Figure 2 is a schematic diagram of a frame three-dimensional structure provided by an embodiment of the present invention; Figure 3 is a schematic diagram of a control box structure provided by an embodiment of the present invention; Figure 4 is a schematic flow chart provided by an embodiment of the present invention; In the figure: 1, fuel tank; 2, fuel filling port; 3, temperature sensor; 4, radiator; 5, first safety valve; 6, proportional overflow valve; 7, logic spool; 8, first check valve; 9, secondary pressure reducer; 10, primary pressure reducer; 11, air filter; 12, inflation interface; 13, second safety valve; 14, oil supply joint; 15, oil supply hose; 16, solenoid valve; 17, oil supply valve; 18, flow meter; 19, pressure sensor; 20, sampling interface; 21, essential oil filter; 22, coarse oil filter; 23, second check valve; 24, motor pump; 25, manual reversing valve; 26, suction hose; 27, liquid level switch; 28, drain port; 29, electric heater; 30, liquid level sight glass; 31, box body; 32, frame; 33, directional wheel; 34, universal wheel; 35, control box; 36, control panel. Specific Embodiments

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0019] Refer to Figures 1 - 4, the present invention provides a technical solution: an oil seal device for an aircraft engine power system, including a box body 31 and an oil seal mechanism. A frame 32 is installed on the inner wall of the box body 31. Two directional wheels 33 are installed on both sides of the left side of the bottom of the box body 31, and two universal wheels 34 are installed on both sides of the right side of the bottom of the box body 31. The oil seal mechanism can heat the oil fluid, remove the water in the oil fluid, avoid the deterioration of the oil fluid, ensure the service life of the aircraft engine, inject lubricating oil into the inner surface of the fuel system accessories for forced oil seal, and can also perform hot oil seal and unsealing on the engine rotor, ensuring the reliability and safety of the equipment.

[0020] Refer to Figures 1 - 4 , in a preferred embodiment, by setting the oil seal mechanism, the oil seal mechanism includes an oil tank 1 and a radiator 4. The oil tank 1 is installed on the top of the frame 32, and a motor pump 24 is installed on the top of the oil tank 1. The radiator 4 is installed on the top of the frame 32, and the oil tank 1 is communicated with the radiator 4. An air filter 11 is installed on the top of the frame 32. The oil fluid in the oil tank 1 can be transported through the motor pump 24, and the motor pump 24 transports the oil fluid to the radiator 4 for heat dissipation and then back to the oil tank 1. The air filter 11 can filter nitrogen and then fill nitrogen into the aircraft engine, and the fuel or lubricating oil in the engine is discharged to a specified container through the air release and oil discharge hoses.

[0021] Refer to Figures 1 - 4 , in a preferred embodiment, a liquid level sight glass 30 is installed on the side of the oil tank 1, a fuel filling port 2 is installed on the surface of the oil tank 1, and a temperature sensor 3 is installed on the surface of the oil tank 1. The storage amount of the oil fluid in the oil tank 1 can be observed through the liquid level sight glass 30, and the installed temperature sensor 3 can detect the temperature in the oil tank 1, and can timely judge the temperature of the oil fluid. An electric heater 29 is installed in the inner cavity of the oil tank 1, a liquid level switch 27 is installed on the surface of the oil tank 1, and an oil discharge port 28 is communicated with the surface of the oil tank 1. After the electric heater 29 is powered on, the oil fluid in the oil tank 1 can be heated, thereby removing the water in the oil fluid, avoiding the deterioration of the oil fluid, ensuring the service life of the aircraft engine, injecting lubricating oil into the inner surface of the fuel system accessories for forced oil seal, and can also perform hot oil seal and unsealing on the engine rotor, ensuring the reliability and safety of the equipment.

[0022] Refer to Figures 1 - 4, in a preferred embodiment, a manual reversing valve 25 is mounted on the surface of the fuel tank 1, and an oil suction hose 26 is connected to the surface of the manual reversing valve 25. The manual reversing valve 25 is connected to the motor pump 24. The other end of the motor pump 24 is connected to a first one-way valve 8. The end of the first one-way valve 8 away from the motor pump 24 is connected to a coarse oil filter 22. The other end of the coarse oil filter 22 is connected to a fine oil filter 21. One end of the fine oil filter 21 is connected to a logic spool 7. The end of the logic spool 7 away from the fine oil filter 21 is respectively connected to a first safety valve 5 and a proportional overflow valve 6. The coarse oil filter 22 and the fine oil filter 21 adopt a series layout to form a gradient filtration structure. Combined with the reverse cut-off function of the first one-way valve 8, it effectively prevents the filtered impurities from flowing back. The logic spool 7 automatically switches the filtration channel through a differential pressure sensor. When the differential pressure exceeds the limit, it triggers the bypass mode, reducing the system pressure drop while avoiding the risk of filter element rupture. The first safety valve 5 and the proportional overflow valve 6 form a dual-mode pressure regulation. The first safety valve 5 serves as the basic overload protection and responds preferentially when the system pressure suddenly rises. The proportional overflow valve 6 realizes dynamic pressure following through an algorithm and can match the flow requirements under different working conditions. The manual reversing valve 25 can adjust the flow direction of the oil according to the needs.

[0023] Referring to Figures 1 - 4 , in a preferred embodiment, the other end of the fine oil filter 21 is connected to a sampling interface 20. The end of the sampling interface 20 away from the fine oil filter 21 is connected to a pressure sensor 19. The other end of the pressure sensor 19 is connected to a flow meter 18. The provided sampling interface 20 can obtain the oil sample purified by the fine oil filter 21 during the operation state. The pressure sensor 19 and the flow meter 18 synchronously collect the differential pressure and flow fluctuation data, and establish a filter element clogging warning model through a neural network algorithm, improving the prediction accuracy of the filter element replacement cycle. The data of the pressure sensor 19 and the flow meter 18 form a cross-validation mechanism. When a non-linear relationship between pressure and flow is detected, the fault diagnosis program is automatically activated, which can accurately identify sensor drift or pipeline leakage. One end of the flow meter 18 is connected to an oil supply hose 15. One end of the oil supply hose 15 is connected to an oil supply joint 14. A solenoid valve 16 is mounted on the surface of the oil supply joint 14. The other end of the flow meter 18 is connected to an oil supply valve 17. The oil can be transported through the oil supply joint 14 and the oil supply hose 15. The installed solenoid valve 16 and the oil supply valve 17 can restrict the transportation of the oil.

[0024] Referring to Figures 1 - 4, in a preferred embodiment, the other end of the flow meter 18 is connected to a second one-way valve 23. One end of the second one-way valve 23 is connected to a second safety valve 13, and the other end of the second one-way valve 23 is connected to a secondary pressure reducer 9. Moreover, the end of the secondary pressure reducer 9 away from the second one-way valve 23 is connected to a primary pressure reducer 10. The primary pressure reducer 10 is connected to an air filter 11, and the other end of the air filter 11 is connected to an inflation interface 12. A series-type pressure reduction structure can be adopted. When connecting the inflation interface 12 to the equipment providing nitrogen, the primary pressure reducer 10 can pre-reduce the inlet high pressure to an intermediate threshold value, and the secondary pressure reducer 9 performs secondary fine adjustment. By resolving the pressure shock in stages, the fluctuation range of the final output pressure can be reduced to less than 1 / 3 of that of a single-stage pressure reduction, which is particularly suitable for working conditions with high pressure differences and large flow rates, and can effectively avoid the sealing failure problem caused by diaphragm tremors.

[0025] Refer to Figures 1 - 4 , in a preferred embodiment, a control box 35 is installed on the surface of the frame 32. A control panel 36 is installed on the surface of the control box 35. An oil supply switch is installed on one side of the surface of the control box 35. A main power on button and a main power off button are respectively installed on the other side of the surface of the control box 35. An emergency stop switch and an alarm light are respectively installed outside the main power on button and the main power off button. The main power on button is a function button for connecting the external power supply of the oil seal device, which can introduce the external power supply into the oil seal device. The main power off button is a function button for disconnecting the external power supply of the oil seal device, which can disconnect the external power supply. The emergency stop switch can be an emergency manual stop button used in case of an emergency. After pressing it, the whole vehicle cuts off power and does not work. After the fault is eliminated, rotate this button clockwise to restore. The alarm light is an alarm device that can emit a beeping sound and a flash when any fault occurs in the whole vehicle. The oil supply switch is a regulating valve for the hydraulic system of the oil seal device.

[0026] Specifically, the working process or working principle of the aircraft engine power system oil seal device is as follows: During use, the oil supply system mainly provides lubricating oil with a certain flow rate, pressure, temperature, pollution degree level, and water content to the engine and turbine starter on the aircraft for oil sealing work. The oil seal device adopts a heating and water removal method, that is, when the heater heats the lubricating oil to 105 °C, the water becomes gaseous and is discharged to achieve the water removal effect. The nitrogen filling and oil removal system mainly provides nitrogen for the engine. The usage process is as follows: Self-circulation, heat dissipation, and heating and water removal working principle: The lubricating oil in the fuel tank 1 passes through the manual reversing valve 25, motor pump 24, second one-way valve 23, coarse oil filter 22, fine oil filter 21, logic valve core 7, and radiator 4 and returns to the fuel tank 1. The oil is heated by the electric heater 29. The heated oil is exposed in a vacuum environment for oil and water vapor separation, and the separated water vapor is pumped out by the motor pump 24 to complete the water removal of the oil.

[0027] The refueling of the equipment fuel tank 1 is divided into two methods: gravity refueling and automatic refueling. Gravity refueling means opening the cover of the fuel filling port 2 of the fuel tank 1 and pouring lubricating oil into the fuel tank 1 using a funnel.

[0028] When the aircraft engine rotor rotates, the engine is subjected to oil sealing work. Before the oil sealing work of the engine, oil cleaning and water removal must be carried out. The oil sealing work can only be carried out when the oil pollution degree and water content meet the requirements. The lubricating oil in the oil sealing device fuel tank 1 passes through the manual reversing valve 25, motor pump 24, check valve, coarse oil filter 22, fine oil filter 21, sampling interface 20, pressure sensor 19, flowmeter 18, supply oil valve 17, and enters the aircraft engine through the hot oil sealing hose. The fuel in the aircraft is discharged into a designated container through the fuel discharge hose to complete the hot oil sealing work.

[0029] When the aircraft engine rotor does not rotate, lubricating oil is injected into the inner surface of the fuel system accessories for forced oil sealing, that is, cold oil sealing. Before the oil sealing work of the engine, oil cleaning and water removal must be carried out. The oil sealing work can only be carried out when the oil pollution degree and water content meet the requirements. The lubricating oil in the oil sealing device fuel tank 1 passes through the manual reversing valve 25, motor pump 24, second check valve 23, coarse oil filter 22, fine oil filter 21, sampling interface 20, pressure sensor 19, flowmeter 18, solenoid valve 16, and enters the aircraft engine through the cold oil sealing hose to fill the aircraft engine with lubricating oil and complete the cold oil sealing work.

[0030] The nitrogen filling vehicle or the ground nitrogen cylinder provides 15 MPa high-pressure nitrogen, which passes through the inflation interface 12, air filter 11, first-stage pressure reducer 10, second-stage pressure reducer 9, first safety valve 5, first check valve 8, and enters the aircraft engine through the cold oil sealing hose to fill the aircraft engine with nitrogen. The fuel or lubricating oil in the engine is discharged into a designated container through the air release and fuel discharge hoses, thereby realizing oil sealing.

Claims

1. An oil seal device for an aircraft engine power system, comprising a box body (31) and an oil seal mechanism, characterized in that; The inner wall of the box body (31) is provided with a frame (32). On both sides of the left side of the bottom of the box body (31), directional wheels (33) are installed. On both sides of the right side of the bottom of the box body (31), universal wheels (34) are installed. The oil seal mechanism includes: An oil tank (1), which is installed on the top of the frame (32), and a motor pump (24) is installed on the top of the oil tank (1). A radiator (4), which is installed on the top of the frame (32), and the oil tank (1) is communicated with the radiator (4). An air filter (11) is installed on the top of the frame (32).

2. The oil seal device for an aircraft engine power system according to claim 1, characterized in that, A liquid level window (30) is installed on the side of the oil tank (1). A fuel filling port (2) is installed on the surface of the oil tank (1), and a temperature sensor (3) is installed on the surface of the oil tank (1).

3. The oil seal device for an aircraft engine power system according to claim 2, characterized in that, An electric heater (29) is installed in the inner cavity of the oil tank (1). A liquid level switch (27) is installed on the surface of the oil tank (1), and an oil drain port (28) is communicated with the surface of the oil tank (1).

4. The oil seal device for an aircraft engine power system according to claim 3, wherein, A manual reversing valve (25) is installed on the surface of the oil tank (1), and an oil suction rubber hose (26) is communicated with the surface of the manual reversing valve (25). The manual reversing valve (25) is communicated with the motor pump (24), and the other end of the motor pump (24) is communicated with a first one-way valve (8).

5. The oil seal device for an aircraft engine power system according to claim 4, characterized in that, The end of the first one-way valve (8) away from the motor pump (24) is communicated with a coarse oil filter (22). The other end of the coarse oil filter (22) is communicated with a fine oil filter (21). One end of the fine oil filter (21) is communicated with a logic valve core (7). The end of the logic valve core (7) away from the fine oil filter (21) is respectively communicated with a first safety valve (5) and a proportional overflow valve (6).

6. The oil seal device for an aircraft engine power system according to claim 5, wherein, The other end of the fine oil filter (21) is communicated with a sampling interface (20). The end of the sampling interface (20) away from the fine oil filter (21) is communicated with a pressure sensor (19). The other end of the pressure sensor (19) is communicated with a flow meter (18).

7. The oil seal device for an aircraft engine power system according to claim 6, characterized in that, One end of the flow meter (18) is communicated with an oil supply rubber hose (15). One end of the oil supply rubber hose (15) is communicated with an oil supply joint (14). A solenoid valve (16) is installed on the surface of the oil supply joint (14). The other end of the flow meter (18) is communicated with an oil supply valve (17).

8. An oil seal device for an aircraft engine power system according to claim 7, characterized in that, The other end of the flow meter (18) is communicated with a second one-way valve (23). One end of the second one-way valve (23) is communicated with a second safety valve (13). The other end of the second one-way valve (23) is communicated with a secondary pressure reducer (9). The end of the secondary pressure reducer (9) away from the second one-way valve (23) is communicated with a primary pressure reducer (10).

9. The oil seal device for an aircraft engine power system according to claim 8, wherein, The primary pressure reducer (10) is communicated with the air filter (11). The other end of the air filter (11) is communicated with an inflation interface (12).

10. A kind of oil seal device for the power system of an aircraft engine according to claim 9, characterized in that, A control box (35) is surface-mounted on the frame (32). A control panel (36) is surface-mounted on the control box (35). An oil supply switch is mounted on one side of the surface of the control box (35). A main power on button and a main power off button are respectively mounted on the other side of the surface of the control box (35). An emergency stop switch and an alarm lamp are respectively mounted outside the main power on button and the main power off button.

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