RTX Corporation
COMPONENTS FOR GAS TURBINE ENGINES

Abstract:

Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and has a first metering flow aperture. At least one support element retention feature is located within the leading edge cavity and extends completely between a pressure side and a suction side of the leading edge cavity to form a full extension from the pressure side to the suction side. First and second axial extending ribs are formed on interior surfaces of the baffle portion and define axial extending flow channels between the baffle and an interior surface of the airfoil and extending from the aft end to the forward end in an axial direction. The first metering flow aperture is located proximate the aft end of the baffle to cause a forward flowing cooling flow.