采用几何方式组合壁面压力/马赫数分布的弯曲压缩面  

Curved compression surface with wall pressure and Mach number distribution using geometric combination

作　　者：张林[1] 张堃元[2] 陈强洪[1] 邱勇[1] 李明海[1] 

机构地区：[1]中国工程物理研究院总体工程研究所,四川绵阳621999 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2017年第4期850-857,共8页Journal of Aerospace Power

基　　金：国家自然科学基金(90916029)

摘　　要：根据给定壁面参数分布规律反设计压缩面的方法,通过几何方式组合研究了壁面采用压力/马赫数复合分布规律的弯曲压缩面,分析了压缩面的参数分布和性能特点.在与参考二维进气道相同约束条件下,将弯曲压缩面应用于二维进气道,分析了其性能并与参考二维进气道进行了对比.数值研究结果表明:几何方式组合能充分发挥壁面按单一参数设计所得弯曲压缩面的优势,使壁面参数分布得到有效改善并趋于更加合理.同参考二维进气道相比,几何方式组合进气道的外压缩面长度有所增加,但在来流马赫数在4~6范围内它的喉道总压恢复系数均得到显著提高.来流马赫数为6时,几何方式组合进气道的喉道总压恢复系数提高10%;来流马赫数为4时其喉道总压恢复系数提高9.6%.The curved compression surface with wall pressure and Mach number distri- bution by geometric combination was investigated according to the reverse design method of compression surface with the given wall parameters distribution. The parameter distribution and performance of compression surface were analyzed. The curved compression surface was applied to design two-dimensional inlet under the same conditions as the reference inlet. And the performance was analyzed and compared with the reference inlet. Numerical results show that the advantages of curved compression surface designed by a single parameter were a- chieved using geometric combination. The wall parameter distributions were improved effec- tively and tended to be more reasonable. Compared with the reference two-dimensional inlet, the inlet length with combination compression surface was increased. But its throat total pressure recovery coefficient was improved significantly within the incoming Mach number range of 4-6. The throat total pressure recovery coefficient of inlet with combination com- pression surface was increased by 10% at incoming Mach number of 6, and increased by 9.6% at incoming Mach number of 4.

关 键 词：超燃冲压发动机进气道 弯曲压缩面 压升规律 马赫数线性分布规律 弯曲激波 

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]