...
机译:涡轮叶片吸入侧前缘附近的圆柱孔的薄膜冷却
Beihang Univ, Collaborat Innovat Ctr Adv Aeroengine China, Sch Energy & Power Engn, Natl Key Lab Sci & Technol Aeroengines Aerothermo, Beijing, Peoples R China;
Beihang Univ, Collaborat Innovat Ctr Adv Aeroengine China, Sch Energy & Power Engn, Natl Key Lab Sci & Technol Aeroengines Aerothermo, Beijing, Peoples R China;
Beihang Univ, Collaborat Innovat Ctr Adv Aeroengine China, Sch Energy & Power Engn, Natl Key Lab Sci & Technol Aeroengines Aerothermo, Beijing, Peoples R China;
Beihang Univ, Collaborat Innovat Ctr Adv Aeroengine China, Sch Energy & Power Engn, Natl Key Lab Sci & Technol Aeroengines Aerothermo, Beijing, Peoples R China;
Beihang Univ, Collaborat Innovat Ctr Adv Aeroengine China, Sch Energy & Power Engn, Natl Key Lab Sci & Technol Aeroengines Aerothermo, Beijing, Peoples R China;
Film cooling; Turbine blade; Rotation; Blowing ratio; Reynolds number; Injection angle;
机译:汽轮机叶片吸入侧圆柱孔的薄膜冷却靠近前缘
机译:涡轮叶片前缘形状对圆柱孔薄膜冷却的影响
机译:旋转对具有三排薄膜冷却孔的燃气轮机叶片前缘区域薄膜冷却的影响
机译:旋转膜冷却性能靠近涡轮叶片吸入侧的前缘附近的孔
机译:涡轮叶片前缘的脉冲薄膜冷却
机译:燃气轮机叶片前缘旋流膜冷却的共轭传热研究
机译:汽轮机叶片薄膜冷却研究:第1次报告,通过前沿附近注射孔的薄膜冷却试验
机译:涡轮喷气发动机空气冷却涡轮叶片的实验研究Ⅵ - 转子叶片牵引和牵引边缘的导热和薄膜冷却