航空发动机防喘控制系统设计和热扰动参数研究

Design of Anti-Surge Control System and Research on Heat Disturbance Parameters for Aeroengine

提出了航空发动机防喘控制系统设计和研制方法,分析了当战斗机发射导弹时热扰动参数对发动机的影响。通过试验和数据分析,得出了发动机防喘控制系统的有效性评价准则,而某型发动机防喘控制系统的研制和飞行试验证明了该有效性评价准则的正确性。

The design and development methods of aeroengine anti - surge control system are presented. Effects of heat disturbance parameters on the engine are analyzed during missile launch. The design criteria of engine anti - surge control system are concluded by means of tests and data analysis. The validity of the design criteria has been demonstrated by the development and flight test of a turbojet engine anti - surge control system.