Improving acceleration dynamic performance of a two-spool turbojet using variable nozzle area controls

A digital computer method was given for simulating aero-engine acceleration dynamic performance based on the engine component characteristics The simulations of a twin-spool turbojet were presented The two layer iterations for predicting the effects of variable nozzle area on acceleration dynamic response of the engine were developed It was found that the transient operating time during accelerations could be considerably reduced enlarging nozzle area Numerical simulations also show that the acceleration dynamic operations of the engine can be optimised using proper nozzle area controls