进气道旋流畸变地面模拟与测量试验

基于飞行试验的应用特点,提出了进气道旋流畸变测试方法和评定指标,以某发动机试车台为试验平台,搭建了旋流模拟与测量系统,进行了整体涡旋流、对涡旋流、局部涡旋流的模拟与测量试验,验证了旋流模拟、测量方法与评价指标的有效性.建立三维数值模型进行了相应工况数值计算,并将试验结果和数值计算结果进行分析对比,发现结果吻合良好,误差较小.研究结果表明:研制的旋流发生器可模拟出不同涡结构和强度的旋流畸变,其中整体涡强度可达17°;提出的旋流测量方法行之有效且精度较高,旋流评定指标合理可行,能够较为直观地反映出旋流流场的强弱和结构,可应用于飞行试验.研究结果为后续型号进气道旋流畸变试飞提供了技术储备.

Research on Simulation and Measurement of InletSwirl Distortion by Tests

Feasible evaluation criterion and measurement method for inlet swirl in flight test were pointed out. the system of Simulation and measurement method for inlet swirl distortion were designed and built in ground stand test. The typical bulk swirl and twin swirl and local swirl were generated and evaluated by pointed criterion. The validation of the simulation and measurement evaluation methods were also testified. The model of numerical simulation for the Inlet Swirl Distortion was established and modified using flight test data. By comparing some results of numerical simulation and flight test data, it was found the numerical results are in agreement with test data and the error can be acceptable. Test results show that: The different model and intensity of Inlet Swirl Distortion can be got by setting different blade bend angle and different distribution of the swirl generator blades, intensity of the bulk swirl was 17°. Pointed measurement method was accurate and available, the different model and intensity of Inlet Swirl Distortion can be showed by the evaluation method, the both methods can apply to flight test. The research supplied technique identification base for inlet swirl in the flight test of subsequent edition of plane.