Test on Engine Containment and Rotor Unbalance of Turbofan Engine
In this study,the test methods of casing containment and rotor unbalance after the loss of fan blades are explored and verified following the tests to reveal the blade inclusiveness and rotor system unbalance ability of a turbofan engine with high bypass ratio.With the test method of preset explosive fracture blade at the root of the fracture blade and the designed test system,the fan blade is broken at the predetermined position by remote control blasting explosive technology at the specified engine speed.The test process is recorded by the high-speed camera from different directions,and the nonlinear transient dynamic response results are obtained by the special parameter measurement system.The number of damaged blades caused by blade loss is about 1.48,all of which fly out axially along the engine inlet or tail nozzle.This satisfies the casing containment requirements.Additionally,the instantaneous impact load on the casing and rotor system is more than 1 000g.The load-bearing structure on the rotor force transmission line is complete,and the installation system is stable.Owing to the unbalanced load of the rotor,the low-pressure rotor fulcrum bearing loses the locking function of the connect-ing bolt with the load-bearing casing.The engine stops 18 seconds after detonating the explosive.Test results meet the requirements and demonstrat that the airworthiness of the blade containment and rotor unbalance of a high bypass ratio engine are consistent.
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