Computation and assessment of aerodynamic stability of turbofan engine for missile

A basic method and flow chart was presented for assessment of aerodynamic stability of turbine engine for missile. The considered factors decreasing surge margin of turbine engine consist of inlet distortion, power extraction, additional bleed and acceleration. A quasi one-dimensional, time dependent system model based on the parallel compressor theory was used to compute the effect of inlet distortion on turbine engine stability; Through Modifying steady state continuum equation, momentum equation and energy equation, the effect of power extraction and additional bleed on turbine engine running line was computed. Unsteady state continuum equation, momentum equation and energy equation were solved for computing the effect of acceleration on turbine engine running line. At last, cumulative method was used to synthetic assessment of the effect of all decreasing factors on turbine engine stability.