动静叶干扰下跨声压气机级性能与叶片型面静压研究  

Study of performance and profile pressure distribution of transonic compressor under rotor-stator interaction condition

作　　者：李绍斌[1] 苏杰先[1] 冯国泰[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2007年第7期1153-1160,共8页Journal of Aerospace Power

基　　金：国家自然科学基金重点项目(50236020);国防科工委基础项目

摘　　要：采用数值方法对某型高负荷跨声速压气机在工作点的非定常流场进行了模拟,对级内动静叶的气动干扰进行了深入分析.通过总压比和等熵效率分析了级性能总参数的非定常性,结合静压系数分析了叶片型面静压的分布及其非定常波动性,研究了尾迹和势流干扰对叶片型面静压非定常波动的影响规律.结果表明气动干扰对级内动静叶片有不同的影响,研究结果增加了对高负荷跨声速压气机内动静叶非定常气动干扰的认识.The unsteady flow field of a high-load transonic compressor was numerically simulated at its working site, while the aerodynamic interaction of rotor-stator was analyzed in detail. Moreover, the unsteady global performance of this stage was discussed through the total pressure ratio and isentropic efficiency. Based on the static pressure coefficient, the profile pressure distribution and unsteadiness of rotor-stator interaction were analyzed to study the influence of trail and potential flow interference on the unsteady fluctuation for different blades. The results show that aerodynamic interaction has different influences on rotor-stator interaction, providing a further insight into the unsteady aerodynamic interaction of rotor-stator in a high-load transonic compressor.

关 键 词：航空 航天推进系统 非定常 气动干扰 静压系数 跨声速压气机 

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]