Hot wire measurements and flow visualization are presented for studying the turbulent flow field over a flat gas turbine film cooling blade with lateral expanded holes.
报道了用热线风速仪和流动可视化技术对带有横向扩展型孔的燃气轮机气膜冷却叶片紊流流场进行的研究。
This study can be useful in turbine blade cooling design.
为涡轮叶片的冷却结构设计提供了依据。
The cooling technique of the blade inner passage plays a significant role in the design of blades for gas turbine.
叶片内部通道冷却技术在航空发动机叶片的设计中占有重要的位置。
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