Heat transfer and pressure measurements in a lattice-cooled trailing edge of a turbine airfoil

Document Type

Conference Proceeding

Publication Date

12-1-2008

Abstract

An experimental study of the heat transfer distribution and pressure drop through a converging lattice-matrix structure has been performed. This structure represents a gas turbine blade trailing-edge cooling passage. Stationary tests were performed on a scaled up model under three Reynolds numbers (24000

Publication Source (Journal or Book title)

Proceedings of the ASME Turbo Expo

First Page

1117

Last Page

1125

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