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ISSN Online: 2377-424X

ISBN Print: 0-89116-909-1

International Heat Transfer Conference 9
August, 19-24, 1990 , Jerusalem, Israel

GROOVE COOLING OF TURBINE BLADES

Get access (open in a dialog) DOI: 10.1615/IHTC9.1510
pages 385-390

要約

The cooling efficiency of a novel method of cooling gas turbine blades is investigated. The method, termed as 'groove cooling' is expected to yield efficient cooling performance, besides permitting the use of well known fabrication methods for fabrication of the blade. The potential of the groove cooling method is examined through analysis as well as experiments in a hot gas cascade tunnel. Analysis indicates improved cooling effectiveness in case of groove cooling configuration in comparison with conventional radial hole convection cooling configuration for same coolant mass flow. The cooling effectiveness of a groove cooled configuration was obtained from tests in a 2-D static hot cascade tunnel. The measured surface temperature distributions, obtained using an infra-red thermographic system, were in satisfactory agreement with the predictions for the test conditions.