Film cooling effectiveness of hole rows on leading edge of turbine blade has been studied experimentally. The model is a blunt body with a half cylinder leading edge with two flat side walls.
采用放大的半圆柱状表面模拟涡轮叶片前缘的形状，对叶片前缘单排及两排圆柱形孔的气膜冷却效率进行了测量。
Film cooling effectiveness of hole rows on leading edge of turbine blade has been studied experimentally. The model is a blunt body with a half cylinder leading edge with two flat side walls.
采用放大的半圆柱状表面模拟涡轮叶片前缘的形状，对叶片前缘单排及两排圆柱形孔的气膜冷却效率进行了测量。
应用推荐