Patent ID: 8511983
Filing Date: 2013-08-20
Classification: F01D

Abstract:
1. A vane for a gas turbine engine, the vane comprising: An airfoil portion having first and second ends spaced apart in a radial direction, Wherein the first end of the airfoil portion defines an unshrouded tip; a platform integrally formed at the second end of the airfoil, wherein the platform is configured to define a flowpath boundary segment; and a first flange extending from the platform away from the airfoil portion substantially in the radial direction, the first flange defining a first circumferential extension and an adjacent second circumferential extension, wherein the first and second circumferential extensions each define forward and aft faces, and wherein the first and second circumferential extensions are offset in an axial direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the axial direction; and wherein the first circumferential extension joins the platform along an entire side of the first circumferential extension; and wherein the second circumferential extension joins the first circumferential extension in a cantilevered configuration.