APPARATUS AND METHOD FOR COOLING GAS TURBINE ENGINE COMPONENTS
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United States of America Patent
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Feb 16, 2017
app pub date -
Aug 14, 2015
filing date -
Aug 14, 2015
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Abstract
A rotor assembly for a gas turbine engine includes a rotor disc having an axially extending rotor disc arm and a plurality of rotor blades extending radially outwardly from the rotor disc. A cover plate is located at an axial face of the rotor disc and at least partially retained at a rotor disc arm. The rotor disc and cover plate define a rotor cavity. A plurality of airflow openings extend into the cavity to allow a flow of air into the rotor cavity to thermally condition the rotor disc and the cover plate at the rotor cavity.
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