模拟板全尺寸吹风试验技术  

Air Intake Test Technology of Full-scale Simulating Plates

作　　者：张鑫 高超 马庆岩 张宝华 刘德权 王靖宇 杨闯 ZHANG Xin;GAO Chao;MA Qing-yan;ZHANG Bao-hua;LIU De-quan;WANG Jing-yu;YANG Chuang(AECC Shenyang Engine Research Institute,S henyang 110015,China;Chinese People's Liberation Army Unit 31434,Shenyang 110034,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]中国人民解放军31434部队,沈阳110034

出　　处：《航空发动机》2022年第5期149-154,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了对某航空发动机流场畸变模拟板进行设计验证和修型,需要对其进行吹风试验,测取其在一定板后马赫数下的压力分布。为此,通过进气和引射相结合的方式,在某试验设备上开展了模拟板全尺寸吹风试验,并进行了模拟板全尺寸畸变吹风试验技术研究。针对模拟板板后马赫数计算方法、板后AIP稳态总压测点布局、板后测点小角度偏斜、板后测点轴向位置以及物理/换算流量对畸变度的影响进行了试验。结果表明:在非回流区内板后马赫数采用总静压法进行计算的结果更接近真实值;板后AIP稳态总压测点布局、测点轴向位置对畸变度测量有影响;板后测点小角度偏斜对畸变度测量基本无影响;综合压力畸变指数随着换算流量的增大逐渐增大;在换算流量相同时,综合压力畸变指数不随物理流量的变化而变化。In order to verify and improve the design of a flow field distortion simulating plate an aeroengine,it was necessary to conduct an air intake test to measure the pressure distribution behind the plate at a certain Mach number.Leveraging the combination of inlet air supply and outlet ejection,a full-scale air intake test of the simulating plate was conducted,and test techniques were explored.The influence of following factors on distortion descriptors were investigated during the test,namely,the calculation method of Mach number behind the simulating plate,the layout of AIP steady-state total pressure measuring points behind the plate,the small angular displacement of the measuring points behind the plate,the axial position of the measuring points behind the plate and the physical/corrected flow rate.The results show that the Mach number behind the plate in the non-recirculation region is closer to the true value by using the total/static pressure method.The layout of AIP steady-state total pressure measuring points behind the plate and the axial position of measuring points have influence on the steady-state circumferential distortion descriptor.The small angular displacement of the measuring point behind the plate has little effect on the steady-state circumferential distortion descriptor.The complex pressure distortion descriptor increases with corrected flow rate.as long as the corrected flow is the same,the complex total-pressure distortion descriptor does not change with physical flow rate.

关 键 词：模拟板 畸变 全尺寸 吹风试验 试验技术 航空发动机 

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]