Aero-engine accessory casing high-altitude test system and method

Abstract

The invention belongs to the field of aero-engine design, and particularly relates to an aero-engine accessory casing high-altitude test system and method, and the system comprises a lubricating oil unit, an oil return unit, a drive unit, a ventilation pipeline, and a heater. The output end of the lubricating oil unit is connected with the driving unit, the oil return unit is connected with the driving unit, and the driving unit can extract lubricating oil in the lubricating oil unit and convey the lubricating oil to the oil return unit; one ends of the ventilation pipeline and the heater are connected with the oil return unit, and the other ends are connected with the lubricating oil unit; lubricating oil in the oil return unit is heated by a heater and then is conveyed into the lubricating oil unit, so that dynamic oil circulation is formed; the vent pipe can adjust the pressure between the lubricating oil tank and the accessory casing. The lubricating oil tank is connected with the accessory casing by adding the ventilation pipeline, so that a structural foundation for simulating the high-altitude working condition of the accessory casing is realized. The vacuum pump is added to realize the adjusting capability of additional casing cavity pressure, and simulation of working conditions at different heights can be realized.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to an aero-engine accessory casing high-altitude performance testing system and method. Background Technology

[0002] Within the accessory gearbox of an aero-engine, gears, bearings, and other transmission components rotate at high speeds. The lubricating oil within the gearbox is subjected to splashing and agitation, resulting in a complex two-phase oil-gas state at the pump inlet when drawing oil from the gearbox. Simultaneously, as the aero-engine's operating altitude increases, the air pressure within the accessory gearbox decreases, further reducing the capacity of the return oil pump. Therefore, during high-altitude operation, the combined effects of agitation and reduced air pressure can easily lead to an imbalance in the oil supply and return matching within the accessory gearbox, causing it to malfunction.

[0003] Currently, China lacks the capability to test the high-altitude performance of accessory gearboxes. Existing aero-engine accessory gearbox testers can only simulate basic ground conditions such as engine speed, fuel supply and return, and heating, and are mainly used to verify the service life and reliability of accessory gearboxes.

[0004] Existing aircraft engine accessory casing test systems are available in [link to relevant documentation]. Figure 1 As shown. This test system cannot simulate the high-altitude working state of the accessory housing, and mainly has the following technical shortcomings:

[0005] 1) The lubricating oil and air in the accessory housing are drawn away by the return oil pump, making it impossible to accurately adjust the pressure inside the accessory housing during the test;

[0006] 2) The pressure inside the accessory casing cannot stably simulate high-altitude conditions (i.e., vacuuming to the specified negative pressure).

[0007] Therefore, based on the existing accessory housing life and reliability tester, it is necessary to improve and adjust the flow path of the test system to obtain a test system that can simulate the high-altitude working conditions of the accessory housing. Summary of the Invention

[0008] To address the aforementioned issues, this application provides an aero-engine accessory casing high-altitude performance testing system and method, thereby resolving the problem of difficulty in simulating high-altitude operating conditions of accessory casings in the prior art.

[0009] The technical solution of this application is: an aero-engine accessory casing high-altitude performance test system, including a lubricating oil unit, an oil return unit, a drive unit, a ventilation duct and a heater;

[0010] The output end of the lubricating oil unit is connected to the drive unit, and the return oil unit is connected to the drive unit. The drive unit can extract the lubricating oil in the lubricating oil unit and deliver it to the return oil unit.

[0011] One end of the ventilation duct and heater is connected to the oil return unit, and the other end is connected to the lubricating oil unit;

[0012] The lubricating oil in the return oil unit is heated by the heater and then transported to the lubricating oil unit to form a dynamic circulation of oil; the ventilation pipe can regulate the pressure between the lubricating oil tank and the accessory casing.

[0013] Preferably, the lubricating oil unit includes an oil tank, a vacuum pump, and a level sensor;

[0014] The liquid level sensor is located inside the lubricating oil tank, and the vacuum pump is connected to the lubricating oil tank. The vacuum pump can draw negative pressure from the lubricating oil tank.

[0015] The oil return unit includes a second motor, an accessory housing, and an oil return pump; the second motor is connected to the accessory housing, one end of the oil return pump is connected to the accessory housing, and the other end is connected to the heater.

[0016] Preferably, the drive unit includes a first motor, an oil supply pump, and an oil filter; the oil supply pump and the oil filter are connected in series and between the liquid level sensor and the accessory housing, and the first motor is connected to the oil supply pump.

[0017] Preferably, a first regulating valve is provided between the lubricating oil tank and the oil supply pump, a lubricating oil flow meter is provided between the lubricating oil filter and the accessory housing, and a second regulating valve is provided between the heater and the lubricating oil tank.

[0018] Another technical solution of this application is: a method for high-altitude performance testing of an aircraft engine accessory casing, comprising:

[0019] Open the first and second regulating valves, and adjust the oil supply pressure P1, oil return pressure P2 and lubricating oil temperature T to the initial specified values ​​for the test for the first time.

[0020] Start the vacuum pump, adjust the accessory housing chamber pressure P3 to match the chamber pressure at the corresponding test height, and collect the working status data of the accessory housing;

[0021] Readjust the oil supply pressure P1, oil return pressure P2, and lubricating oil temperature T until the test values ​​are reached.

[0022] Adjust the accessory housing chamber pressure P3 to another test height, and collect the working status data of the accessory housing again; continue until the working status data of the accessory housing at all test heights are collected to complete the test.

[0023] Preferably, when the oil supply pressure P1, return oil pressure P2 and lubricating oil temperature T reach the test specified values, the lubricating oil tank level and return oil pressure P2 are recorded, and the working status data of the accessory housing are determined based on the lubricating oil tank level and return oil pressure P2.

[0024] Preferably, the oil supply pressure P1 and return pressure P2 are adjusted by adjusting the speed of the first motor and the second motor, and the lubricating oil temperature T is adjusted by adjusting the opening of the second regulating valve.

[0025] The high-altitude performance testing system and method for aircraft engine accessory casings disclosed in this application have the following advantages:

[0026] By adding ventilation ducts and connecting the lubricating oil tank to the accessory housing, a structural foundation simulating the high-altitude working conditions of the accessory housing was achieved.

[0027] The addition of a vacuum pump enables the adjustment of the chamber pressure, allowing for the simulation of different working conditions at various heights.

[0028] By adjusting the motor speed and valve opening, the actual working conditions of the engine accessories at high altitude, such as the casing speed, lubricating oil flow, lubricating oil temperature, and return oil pressure, were simulated.

[0029] Adding a level sensor to the lubricating oil tank can be used to determine the working stability of the accessory casing under different height conditions. Attached Figure Description

[0030] Figure 1 The background diagram shows the accessory casing test system.

[0031] Figure 2 The attached diagram shows the high-altitude simulation test system diagram of the casing.

[0032] 1. Oil tank; 2. Vacuum pump; 3. Liquid level sensor; 4. First motor; 5. Oil supply pump; 6. Oil filter; 7. Oil flow meter; 8. Second motor; 9. Accessory housing; 10. Return pump; 11. Ventilation duct; 12. Heater; 13. First regulating valve; 14. Second regulating valve. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0034] The first aspect of this application provides a high-altitude performance testing system for an aircraft engine accessory casing, such as... Figure 2 It includes a lubricating oil unit, an oil return unit, a drive unit, a ventilation duct 11, and a heater 12.

[0035] The output of the lubricating oil unit is connected to the drive unit, and the return oil unit is connected to the drive unit. The drive unit can draw lubricating oil from the lubricating oil unit and deliver it to the return oil unit.

[0036] One end of the ventilation duct 11 and the heater 12 is connected to the oil return unit, and the other end is connected to the lubricating oil unit.

[0037] The lubricating oil in the return oil unit is heated by the heater 12 and then transported to the lubricating oil unit to form a dynamic circulation of oil; the ventilation pipe can regulate the pressure between the lubricating oil tank 1 and the accessory casing 9.

[0038] When conducting the high-altitude test of accessory housing 9, the first motor 4 drives the oil supply pump 5 to supply the lubricating oil in the lubricating oil tank 1 into the test system pipeline and the test piece of accessory housing 9. Impurities are filtered through the lubricating oil filter 6, and the flow rate through the lubricating oil flow meter 7 is adjusted by the speed of the first motor 4.

[0039] The second motor 8 then drives the accessory housing 9 and its associated return oil pump 10 to simulate the test engine speed. The return oil pump 10 on the accessory housing 9 draws the lubricating oil in the accessory housing 9 back to the lubricating oil tank 1, forming a dynamic circulation of the oil.

[0040] The lubricating oil temperature in the test system is adjusted by the heater 12, and the outlet pressure of the lubricating oil return pump 10 is adjusted by the second regulating valve 14. The real-time oil volume in the lubricating oil tank 1 is recorded by the level sensor 3 inside the lubricating oil tank 1 during the test. The pressure inside the lubricating oil tank 1 is adjusted to the specified negative test pressure by the vacuum pump 2, and the pressure inside the accessory housing 9 is also adjusted to the specified pressure through the ventilation pipe between the lubricating oil tank 1 and the accessory housing 9.

[0041] In simulated high-altitude conditions, when the return oil capacity in accessory housing 9 decreases or is interrupted, the oil level in lubricating oil tank 1 will continuously decrease, and the return oil pressure P2 will continuously decrease. At this time, the simulated ambient altitude is the height capability boundary of accessory housing 9.

[0042] In summary, by integrating the lubricating oil unit, the oil return unit, the drive unit, the ventilation pipeline 11, and the heater 12 to form an integrated test system, a basic structure for dynamic circulation of lubricating oil is constructed, realizing the continuous circulation and supply of lubricating oil within the system and meeting the lubricating oil usage requirements of the accessory casing 9 during the test process.

[0043] Preferably, the lubricating oil unit includes an oil tank 1, a vacuum pump 2, and a liquid level sensor 3;

[0044] The level sensor 3 is located inside the lubricating oil tank 1, and the vacuum pump 2 is connected to the lubricating oil tank 1. The vacuum pump 2 can draw negative pressure from the lubricating oil tank 1.

[0045] The oil return unit includes a second motor 8, an accessory housing 9, and an oil return pump 10; the second motor 8 is connected to the accessory housing 9, and one end of the oil return pump 10 is connected to the accessory housing 9 and the other end is connected to the heater 12.

[0046] The level sensor 3 in the lubricating oil unit can monitor the change in oil volume in the lubricating oil tank 1 in real time, accurately capture the consumption and backflow abnormalities of lubricating oil during the test, and provide direct data basis for judging the working status of the accessory casing 9. The vacuum pump 2 is connected to the lubricating oil tank 1 and can perform precise negative pressure operation on the lubricating oil tank 1, realize the controllable adjustment of the internal pressure of the lubricating oil tank 1, and provide a pressure source for the subsequent simulation of the high-altitude negative pressure working condition of the accessory casing 9.

[0047] Preferably, the drive unit includes a first motor 4, an oil supply pump 5, and an oil filter 6; the oil supply pump 5 and the oil filter 6 are connected in series and connected between the liquid level sensor 3 and the accessory housing 9, and the first motor 4 is connected to the oil supply pump 5.

[0048] The first motor 4 in the drive unit is linked with the oil supply pump 5. The oil supply flow rate of the oil supply pump 5 can be precisely controlled by adjusting the motor speed, so as to realize stepless adjustment of the lubricating oil supply and match the oil supply flow rate requirements under different test conditions.

[0049] Preferably, a first regulating valve 13 is provided between the lubricating oil tank 1 and the oil supply pump 5, an oil flow meter 7 is provided between the lubricating oil filter 6 and the accessory housing 9, and a second regulating valve 14 is provided between the heater 12 and the lubricating oil tank 1. Based on the motor speed adjustment, the oil supply flow rate and oil supply pressure can be precisely adjusted a second time, achieving refined control of the oil supply pressure P1 and meeting the high-precision requirements for oil supply pressure in experiments.

[0050] Another technical solution of this application is: a high-altitude performance test method for an aircraft engine accessory casing 9, comprising:

[0051] Step 1: Open the first regulating valve 13 and the second regulating valve 14, and adjust the oil supply pressure P1, return oil pressure P2 and lubricating oil temperature T to the initial specified values ​​for the test for the first time.

[0052] Step 2: Start vacuum pump 2, adjust the chamber pressure P3 of accessory housing 9 to match the chamber pressure at the corresponding test height, and collect the working status data of accessory housing 9;

[0053] Step 3: Readjust the oil supply pressure P1, oil return pressure P2, and lubricating oil temperature T until the test values ​​are reached;

[0054] Step 4: Adjust the chamber pressure P3 of accessory housing 9 to another test height, and collect the working status data of accessory housing 9 again; until the working status data of accessory housing 9 at all test heights are collected, the test is completed.

[0055] In summary, this application adopts the test process of "initial parameter adjustment - cavity pressure simulation - parameter readjustment - multi-altitude verification", following the logic of first calibrating the ground basic working condition and then simulating the high-altitude negative pressure working condition. This effectively avoids the interference of cavity pressure adjustment on parameters such as oil temperature and pressure, and ensures the accuracy of various parameters during the high-altitude working condition simulation.

[0056] Preferably, when the oil supply pressure P1, the return oil pressure P2, and the lubricating oil temperature T reach the specified test values, the oil level in the lubricating oil tank 1 and the return oil pressure P2 are recorded, and the working status data of the accessory housing 9 are determined based on the oil level in the lubricating oil tank 1 and the return oil pressure P2.

[0057] The oil level in the lubricating oil tank 1 and the return oil pressure P2 are used as the core indicators for determining the working status of the accessory housing 9. The two form a complementary monitoring dimension: the change in oil level directly reflects the overall balance of the lubricating oil return, and the return oil pressure P2 reflects the pressure stability of the return oil pipeline. It can accurately detect abnormal working conditions such as the decrease in the return oil capacity of the accessory housing 9 and the interruption of the return oil.

[0058] Preferably, the oil supply pressure P1 and return pressure P2 are adjusted by adjusting the speed of the first motor 4 and the second motor 8, and the lubricating oil temperature T is adjusted by adjusting the opening of the second regulating valve 14, thereby achieving efficient control.

[0059] In summary, this application has the following advantages:

[0060] By adding ventilation ducts and connecting the lubricating oil tank to the accessory housing, a structural foundation simulating the high-altitude working conditions of the accessory housing was achieved.

[0061] The addition of a vacuum pump enables the adjustment of the chamber pressure, allowing for the simulation of different working conditions at various heights.

[0062] By adjusting the motor speed and valve opening, the actual working conditions of the engine accessories at high altitude, such as the casing speed, lubricating oil flow, lubricating oil temperature, and return oil pressure, were simulated.

[0063] Adding a level sensor to the lubricating oil tank can be used to determine the working stability of the accessory casing under different height conditions.

[0064] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A high-altitude performance testing system for an aircraft engine accessory casing, characterized in that, It includes a lubricating oil unit, an oil return unit, a drive unit, a ventilation duct (11), and a heater (12); The output end of the lubricating oil unit is connected to the drive unit, and the return oil unit is connected to the drive unit. The drive unit can extract the lubricating oil in the lubricating oil unit and deliver it to the return oil unit. One end of the ventilation duct (11) and the heater (12) are connected to the oil return unit and the other end is connected to the lubricating oil unit; The lubricating oil in the return oil unit is heated by the heater (12) and then transported to the lubricating oil unit to form a dynamic circulation of oil; the ventilation pipe can regulate the pressure between the lubricating oil box (1) and the accessory casing (9).

2. The high-altitude performance testing system for aero-engine accessory casings as described in claim 1, characterized in that, The lubricating oil unit includes an oil tank (1), a vacuum pump (2), and a liquid level sensor (3); The liquid level sensor (3) is installed in the lubricating oil tank (1), and the vacuum pump (2) is connected to the lubricating oil tank (1). The vacuum pump (2) can draw negative pressure from the lubricating oil tank (1). The oil return unit includes a second motor (8), an accessory housing (9), and an oil return pump (10); the second motor (8) is connected to the accessory housing (9), and one end of the oil return pump (10) is connected to the accessory housing (9) and the other end is connected to the heater (12).

3. The high-altitude performance testing system for aero-engine accessory casings as described in claim 2, characterized in that, The drive unit includes a first motor (4), an oil supply pump (5), and an oil filter (6); the oil supply pump (5) and the oil filter (6) are connected in series and connected between the liquid level sensor (3) and the accessory housing (9), and the first motor (4) is connected to the oil supply pump (5).

4. The high-altitude performance testing system for aero-engine accessory casings as described in claim 3, characterized in that, A first regulating valve (13) is provided between the lubricating oil tank (1) and the oil supply pump (5), a lubricating oil flow meter (7) is provided between the lubricating oil filter (6) and the accessory casing (9), and a second regulating valve (14) is provided between the heater (12) and the lubricating oil tank (1).

5. A method for high-altitude performance testing of an aircraft engine accessory casing, employing the system described in any one of claims 1-4, characterized in that, include: Open the first regulating valve (13) and the second regulating valve (14), and adjust the oil supply pressure P1, oil return pressure P2 and lubricating oil temperature T to the initial specified values ​​for the test for the first time; Start the vacuum pump (2), adjust the chamber pressure P3 of the accessory housing (9) to match the chamber pressure at the corresponding test height, and collect the working status data of the accessory housing (9); Readjust the oil supply pressure P1, oil return pressure P2, and lubricating oil temperature T until the test values ​​are reached. Adjust the cavity pressure P3 of the accessory housing (9) to another test height, and collect the working status data of the accessory housing (9) again; until the working status data of the accessory housing (9) at all test heights are collected, the test is completed.

6. The high-altitude performance test method for aero-engine accessory casing as described in claim 5, characterized in that, When the oil supply pressure P1, return oil pressure P2 and lubricating oil temperature T reach the test specified values, record the oil level in the lubricating oil tank (1) and the return oil pressure P2, and determine the working status data of the accessory casing (9) based on the oil level in the lubricating oil tank (1) and the return oil pressure P2.

7. The high-altitude performance test method for aero-engine accessory casing as described in claim 5, characterized in that, The oil supply pressure P1 and return pressure P2 are adjusted by adjusting the speed of the first motor (4) and the second motor (8), and the lubricating oil temperature T is adjusted by adjusting the opening of the second regulating valve (14).

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