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	Numerical Study of Improving Aerodynamic Performance of Low Solidity LPT Cascade through Increasing Trailing Edge Thickness
	Li, C., Yan, P. G., Wang, X. F., Han, W. J. and Wang, Q. C.1
	2016
关键词	Aircraft engine low pressure turbine trailing edge thickness profile loss flow control vortex-generator jets separation control local variables
中文摘要	As one of the most important developments in air cooling technology for hot parts of the aero-engine, film cooling technology has been widely used. Film cooling hole structure exists mainly in areas that have high temperature, uneven cooling effectiveness issues when in actual use. The first stage turbine vanes of the aero-engine consume the largest portion of cooling air, thereby the research on reducing the amount of cooling air has the greatest potential. A new stepped slot film cooling vane with a high cooling effectiveness and a high cooling uniformity was researched initially. Through numerical methods, the affecting factors of the cooling effectiveness of a vane with the stepped slot film cooling structure were researched. This paper focuses on the cooling effectiveness and the pressure loss in different blowing ratio conditions, then the most reasonable and scientific structure parameter can be obtained by analyzing the results. The results show that 1.0 mm is the optimum slot width and 10.0 is the most reasonable blowing ratio. Under this condition, the vane achieved the best cooling result and the highest cooling effectiveness, and also retained a low pressure loss.
内容类型	期刊论文
源URL	[http://ir.etp.ac.cn/handle/311046/113067]
专题	工程热物理研究所_Journal of Thermal Science_期刊论文
作者单位	1.[Li Chao 2.Yan Peigang 3.Wang Xiangfeng 4.Han Wanjin 5.Wang Qingchao] Harbin Inst Technol, Sch Energy Sci & Engn, Harbin 150001, Peoples R China.
推荐引用方式 GB/T 7714	Li, C., Yan, P. G., Wang, X. F., Han, W. J. and Wang, Q. C.. Numerical Study of Improving Aerodynamic Performance of Low Solidity LPT Cascade through Increasing Trailing Edge Thickness[J],2016.
APA	Li, C., Yan, P. G., Wang, X. F., Han, W. J. and Wang, Q. C..(2016).Numerical Study of Improving Aerodynamic Performance of Low Solidity LPT Cascade through Increasing Trailing Edge Thickness..
MLA	Li, C., Yan, P. G., Wang, X. F., Han, W. J. and Wang, Q. C.."Numerical Study of Improving Aerodynamic Performance of Low Solidity LPT Cascade through Increasing Trailing Edge Thickness".(2016).

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