Airfoil having built-up surface with embedded cooling passage

摘要

A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

主权项

1. A method of servicing an airfoil of a gas turbine engine comprising:
building up a surface adjacent to a leading edge of the airfoil at an intersection between the airfoil and a platform associated with the airfoil by applying a high heat tolerant material to the surface; and forming at least one cooling passage at least partially within the built-up surface at the intersection between the airfoil and the platform, the at least one cooling passage in fluid communication with a main cooling channel within the airfoil, extending radially inwardly from the main cooling channel and having an outlet at a radially outer side of the platform for providing cooling fluid directly from the main cooling channel to the platform.