GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF
Embodiments of a gas turbine engine component (60) having sealed stress relief slots are provided, as are embodiments of a gas turbine engine (20) containing such a component. In one embodiment, the gas turbine engine includes a core gas flow path (92), a secondary cooling flow path (94), and a turb...
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Main Authors | , , , , |
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Format | Patent |
Language | English French German |
Published |
02.01.2019
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Subjects | |
Online Access | Get full text |
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Summary: | Embodiments of a gas turbine engine component (60) having sealed stress relief slots are provided, as are embodiments of a gas turbine engine (20) containing such a component. In one embodiment, the gas turbine engine includes a core gas flow path (92), a secondary cooling flow path (94), and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body (62, 64, 66) through which the core gas flow path extends, a radially-extending wall (70) projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots (74) formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material (104), 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 gas turbine engine operation. |
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Bibliography: | Application Number: EP20150154580 |