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Cooling of Gas Turbines (1945)

Wolfenstein, Lincoln ; McCarthy, John S. ; Meyer, Gene L.

In: CASI

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Publication Date: 2019-07-12

Description: An 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.

Keywords: Aircraft Propulsion and Power

Type: AD-A800637 , NACA-MR-E5I20

Format: application/pdf

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