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	Multi-point design optimization of a transonic compressor blade by using an adjoint method
	Luo, Jiaqi ; Zhou, Chao ; Liu, Feng
	2013
DOI	10.1115/GT2013-95155
英文摘要	This paper presents the application of a viscous adjoint method to the multi-point design optimization of a rotor blade through blade profiling. The adjoint method requires about twice the computational effort of the flow solution to obtain the complete gradient information at each operating condition, regardless of the number of design parameters. NASA Rotor 67 is redesigned through blade profiling. A single point design optimization is first performed to verify the effectiveness and feasibility of the optimization method. Then in order to improve the performance for a wide range of operating conditions, the blade is redesigned at three operating conditions: near peak efficiency, near stall, and near choke. Entropy production through the blade row combined with the constraints of mass flow rate and total pressure ratio is used as the objective function. The design results are presented in detail and the effects of blade profiling on performance improvement and shock/tip-leakage interaction are examined. ? 2013 ASME.; EI; 0
语种	英语
内容类型	会议论文
源URL	[http://ir.pku.edu.cn/handle/20.500.11897/316718]
专题	工学院
推荐引用方式 GB/T 7714	Luo, Jiaqi,Zhou, Chao,Liu, Feng. Multi-point design optimization of a transonic compressor blade by using an adjoint method[C]. 见:.

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