Film cooling of gas turbine blades

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Film cooling of gas turbine blades

An experimental apparatus was designed and built to study the film cooling effectiveness from a single row of holes at various angles and hole spacings, using a foreign gas technique. Mixtures of Freon 12 and air were injected into an air mainstream to give a range of density ratios encompassing the...

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Bibliographic Details
Main Author:	Foster, N.W.
Format:	Thesis (University of Nottingham only)
Language:	English
Published:	1976
Subjects:	Aircraft gas-turbine blades Effectiveness of film cooling Injection angles Hole spacing
Online Access:	https://eprints.nottingham.ac.uk/13600/

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