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Computed Temperature Distribution and Cooling of Solid Gas-Turbine BladesComputations were made to determine the temperature distribution and cooling of solid gas-turbine blades.A range of temperatures was used from 1500 degrees to 2500 degrees F, blade-root temperatures from 100 degrees to 1000 degrees F, blade thermal conductivity from 8 to 220 BTU/(hr)(sq ft)(degrees F/ft), and net gas to metal heat transfer coefficients from 75 to 250 BTU/(hr)(sq ft)(degrees F).
Document ID
20030064303
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Reuter, J. George (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Gazley, Carl, Jr. (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
September 7, 2013
Publication Date
February 11, 1947
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NACA-RM-E7B11h
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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