| 摘要: |
| 为了认识气膜孔喷气对涡轮叶栅气动性能和流场结构的影响,应用涡轮平面叶栅风洞,实验测量和分析了在叶片表面不同位置气膜孔喷气情况下涡轮叶栅流场与性能,实验中气膜孔气流采用与涡轮叶栅相同的空气介质。实验结果表明,前缘气膜孔喷气使得涡轮叶栅损失随喷气流量增大而单调增大;但是,叶片压力面和吸力面气膜孔喷气对涡轮叶栅损失影响规律是复杂的,由于叶片表面不同位置流动特点的不同,在叶片表面不同位置的气膜孔喷气对涡轮叶栅流动损失和流动结构等的影响也是不相同的。 |
| 关键词: 薄膜冷却 总压损失+ 边界层 气动特性 平面叶栅实验+ |
| DOI： |
| 分类号:V235 |
| 基金项目:国家自然科学基金(10377011) |
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| Experimental studies for the aerodynamic loss in gas turbine with film cooling |
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QIAO Wei-yang,ZENG Jun,ZENG Wen-yan,HUANG Kang-cai,SUN Da-wei,ZHANG Man
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1.School of Power and Energy,Northwestern Polytechnical Univ.,Xi’an 710072,China;2.China Gas Turbine Establishment,Chengdu 610500,China
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| Abstract: |
| Detailed experiments were performed to measure the total pressure loss and boundary layer of the flow through planar turbine cascade with air injection from a signal row of holes on the leading-edge,the pressure side or suction side.The tests were performed in a low speed high-pressure turbine cascade tunnel.The results show that total pressure loss is increased with the increase of the coolant flow mass from leading edge film holes.However,the effects of the air from the film holes in pressure side or suction side on the turbine loss and flow field are complex.It is found that the flow configuration on the blade surface influences the mixing between the coolant and the mainstream of turbine cascade. |
| Key words: Film cooling Total pressure loss+ Boundary layer Aerodynamic characteristic Planar cascade experiment+ |
