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本文介绍进气压力畸变对涡喷发动机压气机特性和稳定性影响的初步试验研究结果.本研究是在一台第一级为跨音级的九级压气机的涡喷发动机(台架上)上进行的.进气有畸变和无畸变的试验结果的对比表明:进气畸变对发动机压气机特性有极显著的影响,不但影响失速边界,而且影响等转速线的位置和形状.进气畸变使压气机转速绂左移和变得平坦,而且使工作绂向失速线移动.减小涡轮第一级导向器出口面积(以后称小Ⅰ导)的影响与进气畸变相类似.压气机级间参数测量表明:进气畸变度在第一级是放大的,在后面几级则迅速衰减,特别是2、3、4级.根据不稳定点的脉动气流参数的时间历程分析发现:3×36目网条件下不稳定的性态为古典喘振,即气流以大幅度振荡,并在部分循环中存在旋转失速;小Ⅰ导条件下为深喘振.试验还表明:带3×36目网的情况下(90%设计转速,畸变指数 D 为(P_1~*-p~*min)/p_1~*=0.173),发动机加速到93.3%设计转速,没有出现不稳定.
This paper introduces the preliminary experimental results of the influence of intake pressure distortion on the performance and stability of the turbojet compressor.This study is a turbojet engine (on the bench) with a nine- The comparison of the experimental results with distorted and undistorted air inlets shows that the air intake distortion has a very significant effect on the characteristics of the engine compressor, which not only affects the stall boundary but also affects the position and shape of the isosphere. So that the compressor speed 绂 left and flattened, but also to work 绂 stall line to move the reduction of the first stage turbine outlet area (hereinafter referred to as small Ⅰ lead) and intake air distortion similar effect.Compressor-class The inter-parameter measurement shows that the distortion of intake air is magnified in the first stage and decayed rapidly in the latter stages, especially in grades 2, 3 and 4. According to the time history analysis of the pulsating airflow parameters at unstable points, it is found that 3 × Under the condition of 36 mesh, the instability state is the classical surge, that is, the air flow oscillates greatly, and there is rotation stall in some circulation, and the deep surge under the condition of small guide I. The experiment also shows that with 3 × 36 mesh In the case of the net (90% design speed, distortion D is the number (P_1 ~ * -p ~ * min) /p_1~*=0.173), the engine accelerates to the design speed of 93.3%, no instability occurs.