Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof

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United States of America Patent

PATENT NO 9506365
APP PUB NO 20150300192A1
SERIAL NO

14257485

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Abstract

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Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.

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Patent Owner(s)

Patent OwnerAddress
HONEYWELL INTERNATIONAL INC101 COLUMBIA ROAD MORRISTOWN NJ 07962

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
MirzaMoghadam, Alexander Phoenix, US 8 64
Riahi, Ardeshir Scottsdale, US 33 192
Smoke, Jason Phoenix, US 35 190
Tucker, Bradley Reed Chandler, US 15 68
Zurmehly, Ed Phoenix, US 6 8

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