重型燃气轮机压气机多截面叶型优化设计  

Optimization design of multi-section airfoils for heavy-duty gas turbine compressor

作　　者：丁骏[1] 王松涛[1] 刘勋[2] 徐皓[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发动机气体动力研究中心,哈尔滨150001 [2]中国船舶重工集团公司哈尔滨船舶锅炉涡轮机研究所,哈尔滨150078

出　　处：《航空动力学报》2017年第3期549-557,共9页Journal of Aerospace Power

基　　金：国家自然科学基金(51206035;51436002);国家自然科学基金创新研究群体项目(51121004)

摘　　要：出于对叶型沿叶高方向的不同以及不同叶高处气动边界的不同两方面考虑,开发了一套叶片多截面叶型优化的设计流程.以单级高负荷压气机的进口导叶和大折转角静叶为优化对象,以多截面关联的性能参数为优化目标,采用考虑附面层转捩的MISES计算程序对叶型气动性能进行分析,并通过遗传算法对叶片进行优化.结果显示:在有效工作范围内,各截面叶型经优化后,前部负荷提高,中部及后部负荷降低,性能得到一定提升.三维数值模拟结果显示,在无大尺度二次流动的条件下,多截面叶型优化方法对提升叶片性能切实可行.Considering the spanwise difference of both airfoil and aerodynamics bounda- ry, an optimization design process of multi-section airfoils was developed. Inlet guide vane and large camber angle stator of a single-stage highly loaded compressor were taken as opti- mization subjects, and multi-section associated performance was taken as optimization tar- get. MISES considering boundary layer transition was adopted to analyze the aerodynamic performance of airfoils, and genetic algorithm was also adopted to optimize the multi-section airfoils. The results show that, within the valid operating range, the front loading of multi- section airfoils increases after optimization, while the central and rear loading decreases, bring about performance improvement. Three-dimensional numerical simulation results show that, without large scale secondary flow, the optimization method of multi-section airfoils is practicable.

关 键 词：重型燃气轮机 压气机叶型 优化设计 多截面优化 附面层转捩 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]