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Toward the Active Control of Heat Transfer in the Hot Gas Path of Gas TurbinesThe work at NASA this summer has focused on assisting the Professor's project, namely "Toward the Active Control of Heat Transfer in the Hot Gas Path of Gas Turbines." The mode of controlling the Heat Transfer that the project focuses on is film cooling. Film cooling is used in high temperature regions of a gas turbine and extends the life of the components exposed to these extreme temperatures. A "cool" jet of air is injected along the surface of the blade and this layer of cool air shields the blade from the high temperatures. Cool is a relative term. The hot gas path temperatures reach on the order of 1500 to 2000 K. The "coo" air is on the order of 700 to 1000 K. This cooler air is bled off of an appropriate compressor stage. The next parameter of interest is the jet s position and orientation in the flow-field.
Document ID
20040000968
Acquisition Source
Glenn Research Center
Document Type
Other
Authors
Oertling, Jeremiah E.
(Louisiana State Univ. LA, United States)
Date Acquired
August 21, 2013
Publication Date
January 1, 2003
Publication Information
Publication: NASA-OAI Collaborative Aerospace Research and Fellowship Program at NASA Glenn Research Center at Lewis Field
Subject Category
Spacecraft Propulsion And Power
Funding Number(s)
CONTRACT_GRANT: NCC3-979
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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