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导叶冷却对涡轮级性能影响的数值研究
引用本文:钟易成,张村元,徐伟祖,潘尚能.导叶冷却对涡轮级性能影响的数值研究[J].航空动力学报,2014,29(4):907-916.
作者姓名:钟易成  张村元  徐伟祖  潘尚能
作者单位:南京航空航天大学 能源与动力学院, 南京 210016;南京航空航天大学 能源与动力学院, 南京 210016;南京普国科技有限公司 技术部, 南京 210016;中国航空工业集团公司 中国航空动力机械研究所, 湖南 株洲 412002
摘    要:针对某高压燃气三维扭转涡轮导叶全叶身冷气射流进行了数值模拟,详细分析了在设计转速下改变冷气流量对叶片气动性能、冷却效率和叶栅通道损失的影响;对比分析了在冷气流量相同的条件下,改变转速对涡轮级性能影响.结果表明:不同冷气流量对导叶冷却孔附近区域的静压影响较为明显,而对下游转子的型面静压影响不大;导叶冷气射流对叶栅通道内主流气流角影响较小;冷气流量占主流流量由2.50%增加至6.25%,叶片绝热壁温降幅达11.19%,导叶叶栅通道总压损失和能量损失分别增加了12.95%和12.01%,而涡轮级功率和级效率分别降低了2.39%和1.51%.

关 键 词:冷气射流  气动性能  冷却效率  涡轮级性能  总压损失  能量损失
收稿时间:2013/2/27 0:00:00

Numerical study guide vane coolant on performance of turbine stage
ZHONG Yi-cheng,ZHANG Cun-yuan,XU Wei-zu and PAN Shang-neng.Numerical study guide vane coolant on performance of turbine stage[J].Journal of Aerospace Power,2014,29(4):907-916.
Authors:ZHONG Yi-cheng  ZHANG Cun-yuan  XU Wei-zu and PAN Shang-neng
Institution:College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Technical Department, the Limited Company of Nanjing Puguo Technology, Nanjing 210016, China;Chinese Avation Powerplant Research Institution, Aviation Industry Corporation of China, Zhuzhou Hunan 412002, China
Abstract:Numerical simulation on a three-dimensional twisty high-pressure gas turbine guide vane with the whole body coolant injection was conducted. Detailed analysis of different coolant injection rate affect the blade aerodynamic performance, cooling efficiency and cascade channel loss was performed at the condition of design speed. Comparative analysis was made to learn the influence of changed rotational speed on the performance of turbine stage at the same coolant injection rate. The results show: different coolant injection rate affect static pressure near holes area more obviously, while the impact on the downstream of rotor surface static pressure is very little. Guide vane coolant injection has less influence on the mainstream flow angle in the cascade channel. Coolant injection rate increased from 2.50% of main flow rate to 6.25%, the adiabatic temperature of the blade surface dropped by 11.19%, total pressure loss and energy loss of guide vane's cascade channel increased 12.95% and 12.01% respectively, while the turbine stage's power and efficiency dropped by 2.39% and 1.51% respectively.
Keywords:coolant injection  aerodynamic performance  cooling efficiency  turbine stage performance  total pressure loss  energy loss
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