COOLED TURBINE RUNNER, IN PARTICULAR FOR AN AIRCRAFT ENGINE
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United States of America Patent
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Jul 19, 2016
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Jul 20, 2015
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Abstract
A cooled turbine runner, in particular a high-pressure turbine runner for an aircraft engine, with turbine blades that are radially arranged at a circumferential surface of a rotor disk, wherein respectively one turbine blade with a profiled blade root is inserted into a correspondingly profiled disk finger groove at the circumferential surface of the rotor disk,
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