EFFECT OF ABRUPT INLET DISTORTION ON ENGINE STABILITY

The unsteady response of a compressor to abrupt change of inlet temperature has been calculated by numerical integration with the“actuator-volume”and the second order delay models.The calculated results are compared with flight test data favourably.The unsteady response of the compressor to abrupt change of inlet pressure(or combined with inlet temperature)has also been calculated in the same manner.The calculated results show that the effects of the abrupt inlet pressure on compressor stability cannot be ignored.