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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
Heat Transfer Research
Импакт фактор: 1.199 5-летний Импакт фактор: 1.155 SJR: 0.267 SNIP: 0.503 CiteScore™: 1.4

ISSN Печать: 1064-2285
ISSN Онлайн: 2162-6561

Выпуски:
Том 51, 2020 Том 50, 2019 Том 49, 2018 Том 48, 2017 Том 47, 2016 Том 46, 2015 Том 45, 2014 Том 44, 2013 Том 43, 2012 Том 42, 2011 Том 41, 2010 Том 40, 2009 Том 39, 2008 Том 38, 2007 Том 37, 2006 Том 36, 2005 Том 35, 2004 Том 34, 2003 Том 33, 2002 Том 32, 2001 Том 31, 2000 Том 30, 1999 Том 29, 1998 Том 28, 1997

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
National Key Laboratory of Science and Technology on Advanced Composites in Special Environments Center for Composite Materials and Structures, Harbin Institute of Technology, Harbin, 150080, China; School of Energy Science and Engineering, Harbin Institute of Technology, Harbin, 150001, China
Bengt Sunden
Division of Heat Transfer, Department of Energy Sciences, Lund University, P.O. Box 118, SE-22100, Lund, Sweden
Songtao Wang
School of Energy Science and Engineering, Harbin Institute of Technology, Harbin, 150001, China

Краткое описание

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.


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