进气道旋流畸变地面模拟与测量试验  

Experiment on Simulation and Measurement of Inlet Swirl Distortion by Ground Tests

作　　者：赵海刚[1] 任丁丁 王俊琦[1] ZHAO Hai-gang;REN Ding-ding;WANG Jun-qi(Power-Plant Institute,Chinese Flight Test Establishment,Aviation Industry Corporation of China,Xi'an 710089,China)

机构地区：[1]中国航空工业集团公司,中国飞行试验研究院发动机所,西安710089

出　　处：《科学技术与工程》2021年第5期2093-2098,共6页Science Technology and Engineering

基　　金：装备预先研究项目(61901080202)。

摘　　要：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。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 by flight test data.By comparing some results of numerical simulation and flight test data,it was found the numerical results were in agreement with test data and the error was acceptable.Test results show that the different model and intensity of inlet swirl distortion can be gotten by setting different blade bend angle and different distribution of the swirl generator blades,and the intensity of the bulk swirl can be 17°.The pointed measurement method is accurate and available,and the different model and intensity of inlet swirl distortion can be showed by the evaluation method,both methods can apply to flight test.The research supplies technique identification foundation for inlet swirl in the flight test of subsequent edition of plane.

关 键 词：进气道旋流畸变 旋流发生器 整体涡旋流 地面车台试验 数值计算 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]