CAJ | 학술논문

为减小涡轮机动叶顶部间隙泄漏造成的气动损失、提高叶顶冷却效率,提出在凹槽叶顶离散排布小隔板迷宫.根据某涡轮机动叶结构,设计了迷宫叶顶气膜冷却效率试验台,通过稳态液晶技术测量了间隙叶高比分别为1．0％,2．0％,3．0％和吹风比分别为1．0,1．5,2．0时隔板迷宫叶顶和凹槽叶顶的气膜冷却效率.结果表明：2种叶顶结构的平均冷却效率均随着叶顶间隙高度的增加而减小；在某间隙高叶比和吹风比范围内,隔板迷宫叶顶冷却效率最多比凹槽叶顶冷却效率高出63％；隔板迷宫显著扩大了叶顶的冷却范围,提高了冷却效率,使冷却效率的分布更加均匀.
위감소와륜궤동협정부간극설루조성적기동손실、제고협정냉각효솔,제출재요조협정리산배포소격판미궁.근거모와륜궤동협결구,설계료미궁협정기막냉각효솔시험태,통과은태액정기술측량료간극협고비분별위1．0％,2．0％,3．0％화취풍비분별위1．0,1．5,2．0시격판미궁협정화요조협정적기막냉각효솔.결과표명：2충협정결구적평균냉각효솔균수착협정간극고도적증가이감소；재모간극고협비화취풍비범위내,격판미궁협정냉각효솔최다비요조협정냉각효솔고출63％；격판미궁현저확대료협정적냉각범위,제고료냉각효솔,사냉각효솔적분포경가균균.
In order to reduce the aerodynamic loss caused by leakage in tip gap of the turbine rotor blade and improve the film cooling efficiency on the blade tip,discretely arranging the rib labyrinth at the squealer tip was proposed.According to the structure of a turbine's rotor blades,the cascade test bench was designed to detect the film cooling efficiency of the rib labyrinth gap.The gas film cooling efficiency of both the laby-rinth tip and the groove tip was measured by steady-state liquid crystal display technology,at blowing ratio of 1.0,1.5 and 2.0 and the gap height of 1.0%,2.0% and 3.0%.The results show that,with an increase in the blade tip height,the average film cooling efficiency of both the above two structures decreased.With-in a certain range of tip height and blowing ratio,the film cooling efficiency of the labyrinth tip can be 63%higher than that on the squealer tip at the most.The labyrinth dramatically increased the cooling range of the tip and enhanced the cooling efficiency,which made the cooling efficiency be more even.