机译:非轴对称端壁轮廓的实现对涡轮叶栅二次损耗的测量
Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, ON, K1S 5B6, Canada;
Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, ON, K1S 5B6, Canada;
Turbine Aerodynamics, United Technologies, Pratt & Whitney Aircraft, 400 Main Street, MS 169-29, East Hartford, CT 06108;
Turbine Aerodynamics, United Technologies, Pratt & Whitney Aircraft, 400 Main Street, MS 169-29, East Hartford, CT 06108;
Turbine Aerodynamics, United Technologies, Pratt & Whitney Aircraft, 400 Main Street, MS 169-29, East Hartford, CT 06108;
AVR: axial velocity ratio=u'_(MS_2)/U'_(MS_1); B_x: axial chord; C: true chord length; C_P: static pressure coefficient =(P-P_(CL_1))/q_(CL_1); C_(P0): total pressure coefficient=(Po-Po_(CL_1))/q_(CL_1); et al;
机译:研究非轴对称轮廓涡轮机端壁上的薄膜冷却的新测试设备-第二部分:传热和薄膜冷却测量
机译:端壁轮廓在跨音速涡轮叶栅中的应用:设计条件下的实验测量
机译:第一级喷嘴导向叶片级联薄膜冷却/传热和二次损耗的轴对称端壁轮廓的研究
机译:非轴对称端壁修整在高载荷涡轮涡轮叶栅中二次损失的测量
机译:燃气轮机第一级喷嘴导流叶片中的测量随着薄膜冷却和端壁轮廓而级联。
机译:湍流强度对燃气轮机叶片通道的阶梯形或光滑端壁处的交叉喷射薄膜冷却的影响
机译:涡轮机级联的二次流动场与3D翼型设计和端壁轮廓在非设计入射时