某双级高压涡轮全三维计算  

Three-dimensional analysis of two-stage high pressure turbine

作　　者：曾军[1] 王彬[1] 卿雄杰[1] 

机构地区：[1]中国航空工业集团公司中国燃气涡轮研究院涡轮技术室,成都610500

出　　处：《航空动力学报》2012年第11期2553-2561,共9页Journal of Aerospace Power

摘　　要：采用自主研发的全三维黏性涡轮设计体系对某双级高压涡轮进行了反设计,并利用商业软件CFX12.0在采用二方程湍流模型SST(shear stress transportation)模型、考虑冷气和转捩等条件下对反设计得到的叶型进行了全三维计算分析,采用源项模拟技术处理气膜冷却流动.计算结果与试验数据进行了对比,结果表明计算得到的效率与试验值吻合,中等负荷高压涡轮气冷叶型采用后部加载设计技术可有效控制流动损失.The blade profiles of a two-stage high pressure turbine （HPT） were rede- signed using 3-D viscous turbine design system developed independently, and the 3-D analy- sis with cooling air and transition being considered was conducted by commercial software CFX 12.0. A two-equation turbulence model shear stress transportation （SST） was used. The film cooling flow was dealt with using source term modeling techniques. The compari- son of calculation results and the test data shows that the predicted efficiency agrees well with the test data, and aft-loaded technique can reduce loss effectively for the cooling blade profile of normal level HPT.

关 键 词：高压涡轮 三维计算 转捩 气冷叶型 后部加载 

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]