Aeroengine test device
A technology of aero-engine and test device, applied in the field of aero-engine, can solve the problems of many parameters, difficult to simulate the actual working condition of aero-engine, high test cost, etc., and achieve the effect of less test points, less test bearing cavity, and lower test cost.
Active Publication Date: 2020-10-23
AECC HUNAN AVIATION POWERPLANT RES INST
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AI Technical Summary
Problems solved by technology
[0004] The attitude test at the accessory level can only assess and judge whether a single accessory meets the requirements of the flight attitude, and it is difficult to simulate the actual working conditions of the aero-engine
For the attitude test of the whole machine level, usually there are many parameters to be tested, and the test cost is relatively high
Method used
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[0032] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.
[0033] Although relative terms such as "upper" and "lower" are used in this specification to describe the relative relationship of one component of an icon to another component, these terms are used in this specification only for convenience, for example, according to the description in the accompanying drawings directions for the example described above. It will be appreciated that if the illustrated device is turned over so...
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The invention relates to an aero-engine test device. The aero-engine test device is used for a test part; the test part is provided with at least one test bearing cavity; a connecting shaft is arranged in the test bearing cavity; the connecting shaft is installed in the test bearing cavity through a test bearing; the aero-engine test device comprises a power device, a grease tank, a simulation cavity and a temperature detection device; the test part is provided with at least one test bearing cavity; the test bearing and the connecting shaft are arranged in the test bearing cavity; the connecting shaft is installed in the test bearing cavity through the test bearing; the power device is connected with the connecting shaft, and drives the connecting shaft to rotate; the grease tank and the test bearing cavity are in bidirectional communication, so that grease can circularly flow in the grease tank and the test bearing cavity; the simulation cavity is communicated with the grease tank; apressure adjusting device is arranged between the simulation cavity and the bearing test cavity; and the temperature detection device is used for detecting the oil supply temperature of the grease tank, the return oil temperature of the test cavity and the temperature of the outer ring of the test bearing in a test process.
Description
technical field [0001] The present disclosure relates to the technical field of aero-engines, in particular, to an aero-engine test device. Background technique [0002] The aeroengine lubrication system not only needs to ensure the normal oil supply and return and ventilation of the bearing cavity, but also needs to meet the requirements of the flight attitude. In practical applications, it is usually necessary to conduct aero-engine attitude adaptability tests. [0003] The test of the attitude adaptability of the aero-engine is mainly carried out by using the test device of the accessory level or the whole machine level. The object of the attitude test at the accessory level is mainly for the lubricating oil tank. By observing the working conditions of the lubricating oil tank within the envelope of the full attitude, it can be judged whether the structure and layout of the oil suction port, oil return port and vent are reasonable. The attitude test at the whole machine...
Claims
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IPC IPC(8): G01M15/14
CPCG01M15/14
Inventor 黄潜雷墩财王亮云江平郭晖薛筱萌
Owner AECC HUNAN AVIATION POWERPLANT RES INST