Rotor blade and gas turbine engine comprising a corresponding rotor assembly
A rotor blade (52) for a gas turbine engine includes a platform (62), an airfoil (60) extending radially outward from the platform, a shank (64) extending radially inward from the platform, a dovetail (66) extending from the shank, and a cooling circuit (130) extending through a portion of the shank...
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Main Authors | , , |
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Format | Patent |
Language | English French German |
Published |
10.03.2010
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Subjects | |
Online Access | Get full text |
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Summary: | A rotor blade (52) for a gas turbine engine includes a platform (62), an airfoil (60) extending radially outward from the platform, a shank (64) extending radially inward from the platform, a dovetail (66) extending from the shank, and a cooling circuit (130) extending through a portion of the shank for supplying cooling air for impingement cooling at least a portion of the rotor blade and for channeling purge air downstream from the rotor blade into a cavity defined within the gas turbine engine. |
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Bibliography: | Application Number: EP20040255280 |