Active load reduction device for aero-engine experimental device after sudden load

Abstract

The invention discloses an active load reducing device for a sudden load of an aero-engine tester. According to the device, a pneumatic chuck is fixed on the upper surface of a chuck support; a working sleeve at one end of a variable stiffness elastic support is arranged in the inner surface of the pneumatic chuck; a flange at the other end of the variable stiffness elastic support is connected with a simulation tester; a three-jaw chuck at one end face of the pneumatic chuck is in a clamping state when the three-jaw chuck is powered on and is in a release state when the three-jaw chuck is powered off; and the variable rigidity elastic support is clamped by adjusting the distance between chuck jaws. The device disclosed by the invention has the beneficial effects that by utilizing the variable stiffness elastic support, the support stiffness is adaptively changed and the critical rotation speed of a rotor system is significantly changed, thereby reducing an impact load of a blade flying off the rotor system and providing experimental support for the safety design of the rotor system when a sudden imbalance occurs; and the device has the characteristics of low cost, good repeatability and implementation convenience.

Description

technical field [0001] The invention relates to the field of aeroengines, in particular to the safety design of a turbofan engine with a large bypass ratio. Background technique [0002] As the blades of modern high-bypass turbofan engines become larger and larger, once the fan blades fall off (FanBlade Off) in the engine, there will be a sudden increase in imbalance, which will seriously affect the normal operation of the engine and cause a major threat to personnel and property , causing incalculable consequences to the flight safety of the aircraft. According to China's airworthiness safety requirements, the engine must be able to accommodate damaged parts and run for at least 15 seconds without igniting, and the installation joints will not fail. The US Federal Aviation Administration and the European Aviation Safety Agency have similar requirements. GJB / Z 101-97 clearly requires that when the blades fly out at the maximum allowable steady-state speed, the engine shall...

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the deficiencies in the prior art that cannot meet the needs of the fan blade flying off load, vibration reduction and load reduction of the large bypass ratio turbofan engine, the present invention proposes an active load reduction device for the sudden load of the aero-engine tester

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