旋转状态下气膜冷却效率试验研究  

Experimental Research of Film-Hole Cooling Efficiency in Rotation Status

作　　者：潘炳华[1] 任芳[1] 郭文[1] 陶智[2] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]北京航空航天大学,北京100191

出　　处：《燃气涡轮试验与研究》2013年第1期30-34,57,共6页Gas Turbine Experiment and Research

摘　　要：以某型发动机高压涡轮转子叶片吸力面腮区气膜孔为研究对象,通过模拟发动机状态的模型试验,研究了旋转数、吹风比和主流雷诺数对气膜孔冷却效率的影响。结果表明,旋转会导致气膜覆盖区域向高半径方向偏转,且旋转数越大,偏转角度越大,气膜冷却效率越低;同时,旋转会弱化吹风比、主流雷诺数等对气膜冷气效率的影响。研究获得的旋转状态下涡轮转子叶片型面典型区域气膜冷却特性的试验数据,可为发动机转子叶片冷却设计提供参考。Experimental investigations were carried out to study the influence of rotation number, blowing ratio and mainstream Reynolds number on film cooling efficiency by simulating engine working condition. The results show that rotation will make the film coverage region lean to higher radial direction, the deflec- tion angle will become larger and the film cooling efficiency lower as the rotation number gets greater. At the same time, rotation will weaken the effect of blowing ratio and mainstream Reynolds number on film cooling efficiency. The test data of film-hole cooling characteristics at the typical regions of HPT surface gained through the study could be referential to the experiment database of the engine blade cooling design.

关 键 词：航空发动机 涡轮叶片 气膜冷却 吹风比 旋转数 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]