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Cooling of Gas TurbinesA theoretical analysis of the radial temperature distribution through the rotor and constant cross sectional area blades near the coolant passages of liquid cooled gas turbines was made. The analysis was applied to obtain the rotor and blade temperatures of a specific turbine using a gas flow of 55 pounds per second, a coolant flow of 6.42 pounds per second, and an average coolant temperature of 200 degrees F. The effect of using kerosene, water, and ethylene glycol was determined. The effect of varying blade length and coolant passage lengths with water as the coolant was also determined. The effective gas temperature was varied from 2000 degrees to 5000 degrees F in each investigation.
Document ID
20030064253
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Brown, W. Byron (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Livingood, John N. B. (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-E7B11c
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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