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原文请求
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题 名：
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Cooling of Gas Turbines. 2. Effectiveness of Rim Cooling of Blades
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并列题名：
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作 者：
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Wolfenstein, L.; Meyer, G. L.; McCarthy, J. S.
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作者机构：
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National Aeronautics and Space Administration, Cleveland, OH. NASA John H. Glenn Research Center at Lewis Field.
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团体作者：
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摘 要：
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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.
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分 类 号：
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关 键 词：
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Gas turbine blades ;Gas turbines
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出 版 年：
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报 告 号：
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NACA-MR-E5I20
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ISBN：
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NULL
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ISSN：
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NULL
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页 码：
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1-43
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页 数：
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语 种：
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eng
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馆 藏 号：
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NTIS-ADA800637
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