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International Heat Transfer Conference 13

ISBN Imprimer: 1-56700-226-9 (CD)
ISBN En ligne: 1-56700-225-0

INTERNAL BLADE COOLING: THE CINDERELLA OF C&EFD RESEARCH IN GAS TURBINES

DOI: 10.1615/IHTC13.p30.170
page 32

Hector Iacovides
Turbulence Mechanics Group, School of Mechanical, Aerospace and Civil Engineering. The University of Manchester, Manchester M13 9PL, U.K.

Brian E. Launder
School of Mechanical, Aerospace & Civil Engineering, The University of Manchester, PO Box 88, Manchester M60 1QD, UK

Résumé

The paper reviews experimental and computational research directed at improving the internal cooling of gas-turbine blades. While not the most glamorous area of gas-turbine aerothermodynamics, the improvements in overall thermal efficiency directly attributable to internal blade cooling arguably outstrip those achieved in any other area of jet-engine research. The cooling arrangements within a blade adopt three cooling strategies: impinging leading-edge jets, serpentine passages for the mid-blade section and pin fins near the trailing edge. Progress in each of these areas is examined. While, in the second of these areas, CFD studies have now become an essential weapon in the designer's armoury, the other two still rely very heavily on experimental research. Possible further developments are discussed.

IHTC-13 Digital Library

Measurement of fluid temperature with an arrangement of three thermocouples FLOW BOILING OF A HIGHLY VISCOUS POLYMER SOLUTION