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CN-122016318-A - Aeroengine accessory case high altitude test system and method

CN122016318ACN 122016318 ACN122016318 ACN 122016318ACN-122016318-A

Abstract

The application belongs to the field of aeroengine design, and particularly relates to a high-altitude test system and method for an accessory case of an aeroengine, wherein the high-altitude test system comprises an lubricating oil unit, an oil return unit, a driving unit, a ventilation pipeline and a warmer; the output end of the lubricating oil unit is connected with the driving unit, the oil return unit is connected with the driving unit, the driving unit can extract lubricating oil in the lubricating oil unit and convey the lubricating oil to the oil return unit, one end of the ventilating pipeline and one end of the heater are connected with the oil return unit, the other end of the ventilating pipeline and the other end of the heater are connected with the lubricating oil unit, the lubricating oil in the oil return unit is conveyed into the lubricating oil unit after being heated by the heater to form dynamic circulation of the lubricating oil, and the ventilating pipeline can adjust the pressure between the lubricating oil tank and the accessory casing. By adding the ventilation pipeline, the lubricating oil tank is connected with the accessory case, so that the structural foundation for simulating the high-altitude working condition of the accessory case is realized. The additional casing cavity pressure adjusting capability is realized by adding the vacuum pump, and the simulation of working conditions with different heights can be realized.

Inventors

  • LENG GANG
  • XIN QI
  • DU JIAJIA
  • KONG LINGCHENG
  • ZHANG HEXUAN

Assignees

  • 中国航发沈阳发动机研究所

Dates

Publication Date
20260512
Application Date
20260316

Claims (7)

  1. 1. The aeroengine accessory case high altitude test system is characterized by comprising an lubricating oil unit, an oil return unit, a driving unit, a ventilation pipeline (11) and a heater (12); 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 end of the ventilation pipeline (11) and one end of the heater (12) are connected with the oil return unit, and the other end of the ventilation pipeline is connected with the oil slide unit; The lubricating oil in the oil return unit is conveyed into the lubricating oil unit after being heated by a heater (12) to form dynamic circulation of the lubricating oil, and the ventilation pipe can adjust the pressure between the lubricating oil tank (1) and the accessory casing (9).
  2. 2. The aeroengine accessory case high altitude test system according to claim 1, wherein the lubricating oil unit comprises a lubricating oil tank (1), a vacuum pump (2) and a liquid level sensor (3); The liquid level sensor (3) is arranged in the lubricating oil tank (1), the vacuum pump (2) is connected with the lubricating oil tank (1), and the vacuum pump (2) can extract negative pressure to the lubricating oil tank (1); The oil return unit comprises a second motor (8), an accessory casing (9) and an oil return pump (10), wherein the second motor (8) is connected with the accessory casing (9), one end of the oil return pump (10) is connected with the accessory casing (9), and the other end of the oil return pump is connected with the warmer (12).
  3. 3. The aeroengine accessory case high altitude test system according to claim 2, wherein the driving unit comprises a first motor (4), an oil supply pump (5) and an oil filter (6), wherein the oil supply pump (5) and the oil filter (6) are arranged in series and connected between the liquid level sensor (3) and the accessory case (9), and the first motor (4) is connected with the oil supply pump (5).
  4. 4. An aeroengine accessory case high altitude test system according to claim 3, wherein a first regulating valve (13) is arranged between the lubricating oil tank (1) and the oil supply pump (5), a lubricating oil flowmeter (7) is arranged between the lubricating oil filter (6) and the accessory case (9), and a second regulating valve (14) is arranged between the warmer (12) and the lubricating oil tank (1).
  5. 5. A method for high altitude testing of an aircraft engine accessory case, using the system of any one of claims 1-4, comprising: opening a first regulating valve (13) and a second regulating valve (14), and regulating the oil supply pressure P1, the oil return pressure P2 and the oil lubrication temperature T to test initial specified values for the first time; Starting a vacuum pump (2), adjusting the cavity pressure P3 of the accessory case (9) to be consistent with the cavity pressure of the corresponding test height, and collecting working state data of the accessory case (9); the oil supply pressure P1, the oil return pressure P2 and the lubricating oil temperature T are regulated again until the test specified value is reached; And adjusting the cavity pressure P3 of the accessory case (9) to another test height, collecting the working state data of the accessory case (9) again until the working state data of the accessory case (9) with all the test heights are collected, and completing the test.
  6. 6. The aircraft engine accessory case high altitude test method according to claim 5, wherein after the oil supply pressure P1, the oil return pressure P2 and the oil return temperature T reach the test specified values, the oil tank (1) liquid level and the oil return pressure P2 are recorded, and the operating state data of the accessory case (9) is determined according to the oil tank (1) liquid level and the oil return pressure P2.
  7. 7. The aeroengine accessory case high altitude test method according to claim 5, wherein the adjustment of the oil supply pressure P1 and the oil return pressure P2 is obtained by adjusting the rotation speeds of the first motor (4) and the second motor (8), and the adjustment of the oil temperature T is obtained by adjusting the opening degree of the second regulating valve (14).

Description

Aeroengine accessory case high altitude test system and method Technical Field The application belongs to the field of aeroengine design, and particularly relates to a high-altitude test system and method for an accessory case of an aeroengine. Background Transmission components such as an inner gear of an accessory case of the aeroengine, a bearing and the like rotate at a high speed, and lubricating oil is in a splashing and stirring state in the accessory case, so that when the lubricating oil pump sucks the lubricating oil in the accessory case, the working condition of a pump inlet presents a complex oil-gas two-phase state. Meanwhile, as the use height of the aero-engine is increased, the air pressure in the accessory case is reduced, and the capability of the oil return pump is further reduced. Therefore, in the high-altitude operation of the accessory case, under the combined action of stirring and air pressure reduction, the matching property of lubricating oil supply and oil return in the accessory case is easy to be unbalanced, so that the accessory case cannot work normally. At present, the domestic test capability for the high altitude of the accessory case still belongs to the blank, and the existing aircraft engine accessory case tester can only simulate the ground state basic working conditions such as rotating speed, oil supply and return, heating and the like, and is mainly used for verifying the working life and reliability of the accessory case. The existing aircraft engine accessory case test system is shown in fig. 1. The test system can not simulate the high-altitude working state of the accessory case, and mainly has the following technical defects: 1) The lubricating oil in the accessory case is pumped by the oil return pump together with air, so that the pressure of the inner cavity of the accessory case cannot be accurately regulated in the test process; 2) The pressure in the inner cavity of the accessory case cannot be stably simulated in a high-altitude state (namely, the accessory case is vacuumized to a specified negative pressure). Therefore, on the basis of the existing accessory case life and reliability testers, the flow path of the test system is improved and adjusted, so that the test system capable of simulating the high-altitude working condition of the accessory case is obtained. Disclosure of Invention In order to solve the problems, the application provides a high-altitude test system and a high-altitude test method for an accessory case of an aeroengine, which are used for solving the problem that the high-altitude working condition of the accessory case is difficult to simulate in the prior art. The high-altitude test system for the aircraft engine accessory case comprises an lubricating oil unit, an oil return unit, a driving unit, a ventilation pipeline and a warmer; 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 end of the ventilation pipeline and one end of the warmer are connected with the oil return unit the other end is connected with the lubricating oil unit; the lubricating oil in the oil return unit is heated by the heater and then is conveyed into the lubricating oil unit to form dynamic circulation of the lubricating oil, and the ventilation pipe can adjust the pressure between the lubricating oil tank and the accessory casing. Preferably, the lubricating oil unit comprises a lubricating oil tank, a vacuum pump and a liquid level sensor; The liquid level sensor is arranged in the lubricating oil tank, the vacuum pump is connected with the lubricating oil tank, and the vacuum pump can extract negative pressure to the lubricating oil tank; the oil return unit comprises a second motor, an accessory casing and an oil return pump, wherein the second motor is connected with the accessory casing, one end of the oil return pump is connected with the accessory casing, and the other end of the oil return pump is connected with the warmer. Preferably, the driving unit comprises a first motor, an oil supply pump and an oil filter, wherein the oil supply pump and the oil filter are arranged in series and connected between the liquid level sensor and the accessory casing, and the first motor is connected with the oil supply pump. Preferably, a first regulating valve is arranged between the lubricating oil tank and the oil supply pump, a lubricating oil flowmeter is arranged between the lubricating oil filter and the accessory casing, and a second regulating valve is arranged between the warmer and the lubricating oil tank. The application also provides a high altitude test method for an aircraft engine accessory case, which comprises the following steps: Opening a first regulating valve and a second regulating valve, and regulating the oil suppl