MULTI-OBJECTIVE OPTIMIZATION OF TURBINE BLADE TIP WITH FILM COOLING HOLES

被引:0
作者
Yang, Shuai [1 ]
Zhang, Min [1 ]
Liu, Yan [1 ]
Yang, Jinguang [1 ]
机构
[1] Dalian Univ Technol, Sch Energy & Power Engn, Dalian, Peoples R China
来源
PROCEEDINGS OF ASME TURBO EXPO 2021: TURBOMACHINERY TECHNICAL CONFERENCE AND EXPOSITION, VOL 2D | 2021年
基金
中国国家自然科学基金;
关键词
Tip cooling; Multi-objective optimization; Injection source term; Numerical simulation;
D O I
暂无
中图分类号
TH [机械、仪表工业];
学科分类号
0802 ;
摘要
Tip leakage flow is inevitable due to the tip clearance over rotor blades in turbines. This phenomenondeteriorates blade aerodynamic performance and induces severe thermal damage to the tip surface.Introduction of cooling jets to the tip can effectively controls the tip leakage flow and improves the tip heat transfer. Therefore, this paper aims to optimize film cooling holes on a flat tip of a subsonic cascade and an topology-optimized tip of a transonic cascade. A design variable is a material parameter defined at each grid node along the blade camber line. This idea is based on the topology optimization method. The objective is to minimize blade energy loss and maximize tip heat transfer intensity. A response surface optimization based on the design of experiment (DOE) analysis is employed, and a multi-objective Genetic Algorithm is used to get Pareto optimum solutions. During the DOE process, a CFD method using injection source terms is integrated for numerical simulations to reduce computational costs. Optimized tip film cooling holes are finally re-constructed. The influence of the newly designed tip cooling holes configuration on blade aerothermal performance is evaluated via CFD simulations using body-fitted mesh. Results show that compared with the uniform arrangement of cooling film holes along the axial direction, all the optimized film cooling holes can improve both blade aerodynamic performance and tip heat transfer performance.
引用
收藏
页数:11
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