航空发动机失速喘振辅助判别方法研究

Research on the Auxiliary Discriminant Method for Stall and Surge Conditions of Aero-Engine

目前,对脉动压力的监测主要以监测脉动压力幅值为主。发生失速、喘振现象时,脉动压力幅值一定会超过限制值。但有时由于测点安装位置、管腔效应等因素的影响,在发动机气动平稳状态下,脉动压力幅值也超过限制值。因此,脉动压力幅值超限不一定说明发动机发生了气动失稳。为了降低在试验中对失速、喘振的误报率,引入了紊流度值辅助判别的概念。

At present, detecting dynamic pressure amplitude is the most important part in detecting dynamic pres-sure. When stall or surge happens, dynamic pressure amplitude will exceed the limits. But, Sometimes because of the position of sensors or tube cavity effect, When the aero-engine works smoothly, the dynamic pressure amplitude will also exceed the limits. Accordingly, Exceeding the limits doesn, t always proof that aero-engine works with an unstable performance. In order to reduce the wrong judgment of stall or surge, this paper introduces the concept of turbulence intensity.