一种涡轮发动机加速控制规律设计的新方法

A New Method of Acceleration Control Law Design for Turbine Engines

提出了一种涡喷、涡扇发动机加速控制规律快速设计的新方法:在发动机稳态特性计算模型的基础上,通过额外增加转子提取功率,使得发动机稳态工作点(线)靠近喘振边界,在同时考虑燃烧室富油熄火边界、涡轮进口总温限制以及压气机喘振裕度限制的条件下,利用适当的控制规律描述形式并结合发动机工程研制中的经验,能够快速而准确地获得涡喷、涡扇发动机加速控制规律。对某型涡喷发动机加速控制规律的改进的计算结果表明,提出的加速控制规律的设计方法准确而有效。

A new method of acceleration control law design for turbojet and turbofan is proposed. Based on the steady-state performance computing model, an extra power extraction of spool is induced so that the steadystate operating points （line） are approached to the surge limit. Taking the fuel-rich flameout limit of combustot, total temperature limit of turbine inlet and surge margin limit of compressor into account, and using appropriate form to describe the acceleration control law and combining with the experiences of research and development of turbine engine, the acceleration control law for turbojet and turbofan is designed fast and accurately. The computing results of improved design of acceleration control law of some turbojet engine indicate that the new method is accurate and effective.