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International Symposium on Heat Transfer in Turbomachinery
August, 24-28, 1992 , Marathon, Greece

DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb


ISBN Print: 1-56700-016-9

ISBN Print: 978-1-56700-016-0

Integrated CAE System for Cooled Turbine Blade Design and Verification Tests of Analytical Codes

pages 73-84
DOI: 10.1615/ICHMT.1994.IntSympHetatTransTurb.60
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ABSTRACT

The purpose of the present paper is to offer an efficient integrated cooled blade design system based on a consistent philosophy of pursuing " accuracy " , " speed " and " flexibility " in order to produce optimized cooling design. Herein analytical codes of external and internal flow field of the blade and temperature of the solid blade are all originally organized, not a collection of separate code, using Finite Element Method. The mesh generation and boundary condition mapping of each FEM code is fully linked with blade geometry design code and is customized for each application.The present CAE code is capable of designing various type of cooling passages for both turbine nozzle vanes and rotor blades with internal heat transfer enhancement devices such as impinging jets, turbulated walls, pin fins etc. .combined with film cooling. Accuracy of each code is assessed by verification tests and a factory test of an actual gas turbine. The comparison of analytical results and experimental correlations is subsequently presented and discussed.

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