| 本文已被：浏览 1545次 下载 637次 |
码上扫一扫！ |
|
|
| 涡轮叶片表面气膜冷却效率的实验研究 |
|
朱惠人1,2, 向安定1,2, 许都纯1,2, 刘松龄1,2, 郭文3,4
|
|
1.西北工业大学动力与能源学院;2.陕西西安710072;3.中国燃气涡轮研究院;4.四川成都610500
|
|
| 摘要: |
| 采用放大的叶片模型,利用大尺寸低速线性叶栅风洞进行实验,测量了涡轮导向叶片表面不同位置单排气膜孔的气膜冷却效率,研究了孔排位置、吹风比及来流雷诺数的影响。风洞实验段由3个叶片组成,其中中间的叶片为试验叶片,由优质木材制成。试验叶片表面上开有15排气膜孔,其中吸力面3排,前缘区6排,压力面6排。实验的参数变化范围是:基于叶片弦长的来流雷诺数250000～450000,吹风比0 5～2 5。结果表明,由于气膜孔排位置的不同,其下游冷却效率受来流雷诺数及吹风比影响的变化趋势也有所不同。 |
| 关键词: 涡轮叶片 气体冷却 薄膜冷却 实验 |
| DOI： |
| 分类号:V232 |
| 基金项目:航空科学基金资助项目 (0 0C53 0 2 8)。 |
|
| An experimental investigation of film cooling effectiveness on the surface of turbine blade |
|
ZHU Hui-ren,XIANG An-ding,XU Du-chun,LIU Song-ling,GUO Wen
|
|
1.Coll. of Propulsion and Energy, Northwestern Polytechnical Univ., Xi’an 710072, China;2.Gas Turbine Establishment of China, Chengdu 610500, China
|
| Abstract: |
| Film cooling effectiveness of single film row at different locations on turbine blade surface was studied experimentally. A three-blade liner cascade in a large-scale low-speed opening wind tunnel was used in the experiment. There were 15 rows of film cooling holes at the surface of middle blade which was made of high quality wood and three rows on the suction surface, six rows on the leading edge and six rows on the pressure surface. Film cooling effectiveness on the blade surface was measured for the cases with mainstream Reynolds number from 250000 to 450000 and blowing ratio from 0.5 to 2.5. The influences of Reynolds number, blowing ratio and the location of film cooling holes on film cooling effectiveness were described. |
| Key words: Turbine blade Gas cooling Film cooling Experimentation |
