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Heat Transfer Research

Impact factor: 0.930

ISSN Print: 1064-2285
ISSN Online: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.2015012370
pages 599-629

OPTIMIZATION OF THE BLADE PROFILE AND COOLING STRUCTURE IN A GAS TURBINE STAGE CONSIDERING BOTH THE AERODYNAMICS AND HEAT TRANSFER

Lei Luo
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin, 150001, China; Division of Heat Transfer, Department of Energy Sciences, Lund University, Box 118, Lund, SE-2 2 100, Sweden
Bengt Sunden
Energy Sciences Heat Transfer Division, Box 118, SE-22100 Lund, Sweden
Songtao Wang
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin, 150001, China

ABSTRACT

The need to design high performance of a cooled gas turbine is considered with emphasis made on coupled aerodynamic and heat transfer optimization of the vane, blade, and single stage cooled gas turbine by using a multiobjective optimization method. The aerodynamic profile is designed to have three sections and the cooling structure to consist of a serpentine passage, with a tail transverse channel and trailing edge slots. The optimization platform is built up in an in-house code using a cooling structure parametric method based on MATLAB, as well as automatic grid generation methods, a blade profile parametric program in FORTRAN, the software ISIGHT and ANSYS-CFX. The optimization platform evaluates the aerodynamic effects through the aerodynamic efficiency and presents the cooling effect by the high-temperature coefficient. The pressure drop is described by a pressure drop function. The multiobjective optimization method is accomplished by optimizing the inlet flow angle, installation angle, and the post-corner angle of the vane and blade profiles, while the position of partition is the optimized variable of the cooling structure. The results show that there exists an optimum case in aerodynamic efficiency, high-temperature coefficient, and pressure drop in a Pareto-optimal front.