Gas turbine engine airfoil cooling circuit arrangement
A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received with...
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Main Authors | , , , , |
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Format | Patent |
Language | English |
Published |
05.07.2022
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Subjects | |
Online Access | Get full text |
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Summary: | A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil. |
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Bibliography: | Application Number: US201715450087 |