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

摘要

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.

主权项

1. A gas turbine engine, comprising:
a core gas flow path; a secondary cooling flow path; and a gas turbine engine component, comprising:
a component body through which the core gas flow path extends;a radially-extending wall projecting from the component body into the secondary cooling flow path;one or more stress relief slots formed in the radially-extending wall and having interior surfaces; anda high temperature braze material infiltrated into the one or more stress relief slots and bonded to the interior surfaces thereof, the high temperature braze material impeding leakage between the secondary cooling flow path and the core gas flow path, and fracturing to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.