A method for testing an interruption of lubricating oil in an aeroengine

By directly monitoring parameters such as the gas generator speed, output power, and turbine inlet temperature of the aero-engine, and combining this with closed-loop control of the oil supply, the problem of inaccurate bearing failure detection in existing technologies has been solved, enabling more efficient and accurate lubricating oil interruption testing.

CN115615706BActive Publication Date: 2026-06-23AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Application Number
CN202211242238.6
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2022-10-11
Publication Date
2026-06-23
Estimated Expiration
2042-10-11

AI Technical Summary

Technical Problem

Existing testing methods for lubricating oil interruption in aero gas turbine engines cannot accurately and efficiently determine signs of bearing failure by monitoring abnormal phenomena such as sudden changes in vibration values, compressor stall, and exhaust flame.

Method used

By directly monitoring parameters such as gas generator speed, output power, power turbine inlet temperature, and ball bearing wall temperature, combined with a closed-loop control mode for oil supply, bearing failure can be determined by monitoring parameters, avoiding manual judgment of abnormal phenomena and reducing test risks.

Benefits of technology

It improves the efficiency of identifying bearing failure symptoms, avoids errors caused by abnormal phenomenon judgments, reduces testing risks, and prevents further damage to the engine.

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Abstract

The application discloses an aero-engine lubricating oil interruption test method, sets monitoring parameters in the S1 step, records the monitoring parameters of the engine in the S2 step to the S4 step, obtains monitoring parameter alarm values through the monitoring parameters, interrupts the lubricating oil supply of the engine in the S7 step, and monitors whether the second current gas generator rotating speed, the second current output power, the second current power turbine inlet temperature and the second current ball bearing wall temperature exceed the corresponding first alarm values within the second preset time. Since the signs of bearing failure are directly judged through the monitoring parameters, the situation that the signs of bearing failure are judged by artificial through abnormal phenomena is avoided, the efficiency and accuracy of judging the signs of bearing failure are improved, the monitoring parameters of the engine are obtained through the S2 step to the S4 step, the monitoring parameter alarm values are obtained according to the monitoring parameters, the monitoring parameter alarm values correspond to the actual situation of the engine, and the inaccurate test results caused by the differences between different engines are avoided.
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