Library Subscription: Guest
Home Archives Thermal Letter Officers Future meetings Assembly for International Heat Transfer Conferences
International Heat Transfer Conference 9

ISSN: 2377-424X (online)
ISSN: 2377-4371 (flashdrive)

GROOVE COOLING OF TURBINE BLADES

V. Krishnamoorthy
Propulsion Division, National Aeronautical Laboratory Bangalore 560017, India

R. Lakshminarayanan
The University of Texas at Arlington; Propulsion Division, National Aeronautical Laboratory Bangalore 560017, India

B. Ramachandra Pai
Propulsion Division, National Aeronautical Laboratory Bangalore 560017, India

DOI: 10.1615/IHTC9.1510
pages 385-390

Abstract

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.

Purchase $25.00 Check subscription Publication Ethics and Malpractice Recommend to my Librarian Bookmark this Page