机译:具有两个冷却剂入口的旋转后缘内部冷却通道中的传热特性
National Key laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
National Key laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
National Key laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
National Key laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
National Key laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, Collaborative Innovation Center of Advanced Aero-Engine, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
Blade trailing edge; Two-inlet inflow; Rotating heat transfer; Wedge-shaped channel;
机译:具有横向流体提取的旋转双入口后边缘通道的传热
机译:旋转后边缘楔形冷却通道中的传热,具有两个流入形式
机译:后缘冷却孔堵塞对后缘冷却通道传热影响的实验/数值研究
机译:尾缘冷却通道尾缘冷却孔堵塞对传热影响的实验/数值研究
机译:在高转数下在燃气涡轮叶片的前缘和后缘冷却通道中的热传递。
机译:后缘不同冷却方式的双通道梯形通道数值结果的验证和分析
机译:后缘喷射对涡轮叶片针翅冷却通道局部热(质量)传递的影响
机译:薄膜涡轮叶片的前缘冷却剂管道