Inscrição na biblioteca: Guest
Portal Digital Begell Biblioteca digital da Begell eBooks Diários Referências e Anais Coleções de pesquisa
Heat Transfer Research
Fator do impacto: 0.404 FI de cinco anos: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN Imprimir: 1064-2285
ISSN On-line: 2162-6561

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

RESUMO

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.


Articles with similar content:

SHAPE OPTIMIZATION TO IMPROVE FILM-COOLING PERFORMANCE FOR LAIDBACK FAN-SHAPED FILM COOLING HOLE ON THE SUCTION SURFACE OF A TURBINE VANE
International Heat Transfer Conference 16, Vol.10, 2018, issue
Ying Huang, Chun-hua Wang , Jingzhou Zhang , Xing-dan Zhu
Local heat/mass transfer characteristics in a square duct with various rib arrangements
International Heat Transfer Conference 12, Vol.47, 2002, issue
Y. Y. Kim, Chung Choi, Dong Ho Rhee, Sei Young Lee, Hyung-Hee Cho, S. J. Wu
Optimal Solutions of Pin-Fin Type Heat Sinks for Different Fin Shapes
Journal of Enhanced Heat Transfer, Vol.14, 2007, issue 2
Kyoungwoo Park, Jeong-Tae Kwon, Keun-Ho Rew, Byeong-Sam Kim
DESIGN OF INTEGRAL CONTROL ALGORITHMS FOR THE LATERAL CHANNEL OF THE FLY-BY-WIRE CONTROL SYSTEM OF ADVANCED HIGH-SPEED HELICOPTERS
TsAGI Science Journal, Vol.47, 2016, issue 8
Vladimir Mikhailovich Kuvshinov
THE EFFECT OF COOLING CHANNEL CROSSFLOW ON FILM COOLING EFFECTIVENESS AND HEAT TRANSFER COEFFICIENT
International Heat Transfer Conference 13, Vol.0, 2006, issue
Jens von Wolfersdorf, H. P. Kissel, A. Ungewickell