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Cooling of Gas TurbinesAn analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade life. Dependence of rim cooling on heat-transfer coefficient, blade dimensions, and thermal conductivity is determined by a single parameter.
Document ID
20090033674
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Wolfenstein, Lincoln
(National Advisory Committee for Aeronautics. Aircraft Engine Research Lab. Cleveland, OH, United States)
Meyer, Gene L.
(National Advisory Committee for Aeronautics. Aircraft Engine Research Lab. Cleveland, OH, United States)
McCarthy, John S.
(National Advisory Committee for Aeronautics. Aircraft Engine Research Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
September 20, 1945
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AD-A800637
NACA-MR-E5I20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
ATI COLLECTION
ATI-015346
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