涡轮导向叶片表面气膜孔流量系数的实验研究

推进技术 ›› 2003, Vol. 24 ›› Issue (3): 216-218.

涡轮导向叶片表面气膜孔流量系数的实验研究

向安定,朱惠人,刘松龄,许都纯,郭文

西北工业大学航空动力与热力工程系;陕西西安710072;西北工业大学航空动力与热力工程系;陕西西安710072;西北工业大学航空动力与热力工程系;陕西西安710072;西北工业大学航空动力与热力工程系;陕西西安710072;中国燃气涡轮研究院 ;四川成都610500

发布日期:2021-08-15
基金资助:
航空科学基金 (0 0C53 0 2 8)

Discharge coefficient measurements for film cooling holes on blade surface in a turbine cascade

Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Gas Turbine Establishment of China, Chengdu 610500, China

Published:2021-08-15

摘要/Abstract

摘要： 对表面布置有多排气膜孔的涡轮导向叶片进行了流量系数实验研究,在不同吹风比和雷诺数下测得了流量系数值。并分析了各种因素对流量系数的影响程度。结果表明:在不同位置气膜孔流量系数分布规律有较大区别,孔排位置一定时,流量系数主要由吹风比决定。该实验结果对涡轮叶片表面气膜冷却的设计研究有重要意义。

关键词: 涡轮叶片;薄膜冷却;气孔;实验;流量系数

Abstract: Discharge coefficients of film cooling holes were investigated on the turbine blade surface with a large-scale low speed turbine cascade. Discharge coefficients with coolant injection were determined at different blowing ratio and Reynolds number. Results show that turbine blade surface film holes discharge coefficients are different greatly in different hole array position. The distribution of discharge coefficients is mainly determined by blowing ratio for same geometry.

Key words: Turbine blade;Film cooling;Gas hole;Experiment;Flow coefficient

向安定,朱惠人,刘松龄,许都纯,郭文. 涡轮导向叶片表面气膜孔流量系数的实验研究[J]. 推进技术, 2003, 24(3): 216-218.