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Heat transfer measurements on an intermediate-pressure nozzle guide vane tested in a rotating annular turbine facility, and the modifying effects of a non-uniform inlet temperature profile

Abstract:

In modern gas turbine engines there exist significant temperature gradients in the combustor exit flow. These gradients arise because both fuel and dilution air are introduced within the combustor as discrete jets. The effects of this non-uniform temperature field on the aerodynamics and heat transfer rate distributions of nozzle guide vanes and turbine blades is difficult to predict, although an increased understanding of the effects of temperature gradients would enhance the accuracy of est...

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Publication status:
Published

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Publisher copy:
10.1243/095765003322315487

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Institution:
University of Oxford
Department:
Oxford, MPLS, Engineering Science
Role:
Author
Volume:
217
Issue:
A4
Pages:
421-431
Publication date:
2003-01-01
DOI:
EISSN:
2041-2967
ISSN:
0957-6509
URN:
uuid:b037a657-21da-4783-b052-1b127678e58a
Source identifiers:
64489
Local pid:
pubs:64489

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