通道参数对超声速叶栅性能的影响  

Effects of passage parameters on performance of supersonic cascade

作　　者：张疏影 周玲 季路成 ZHANG Shuying;ZHOU Ling;JI Lucheng(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Institute of Aero Engine,Tsinghua University,Beijing 100084,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]清华大学航空发动机研究院,北京100084

出　　处：《航空动力学报》2022年第4期836-847,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51976010);国家科技重大专项(2017-Ⅱ-0006-0020,2017-Ⅱ-0001-0013,J2019-Ⅱ-0003-0023)。

摘　　要：为了研究喉部面积比、喉部位置及稠度对超声速叶栅最小损失点性能的影响,基于直接控制通道的造型方法获得一系列设计马赫数为1.4且具有不同通道参数的平面叶栅。数值计算与流场分析结果表明:根据叶栅通道内激波系结构的不同可将其划分为启动态叶栅与过渡态叶栅。喉部参数主要通过改变激波系位置影响叶栅性能。启动态叶栅喉部面积比越小、喉部位置越靠前,其最小损失越小、静压比越高;过渡态叶栅则相反。稠度改变时叶栅通道中激波系结构发生变化,大稠度叶栅大多处于启动态,最小损失小且静压比高;小稠度叶栅大多处于过渡态,具有更大的裕度。In order to study the effects of throat-to-inlet area ratio,throat position and solidity on the performance of supersonic cascade at the minimum loss point,a series of planar cascades with designed Mach number 1.4 and different passage parameters were obtained based on a blading method of directly controlling the cascade passage.The results of numerical calculations and flow field analysis showed that the cascades can be divided into started and transitional ones according to different shock wave structures in cascade passages.Throat parameters mainly affected cascade performance by changing the location of the shock wave system.For a started cascade,the minimum total pressure loss decreased and the static pressure ratio increased when the throatto-inlet area ratio was smaller and the throat position moved further forward,just the opposite for a transitional cascade.The structure of the shock wave system changed with the solidity.A tight solidity made more cascades started,having lower minimum total pressure loss and higher static pressure ratio,while wider solidity made more cascades non-started,having lager margin.

关 键 词：超声速叶栅 叶栅通道 喉部 稠度 最小损失点 激波系 

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]