Abstract: A turbine engine variable stator vane includes a platform having a circumference adjoining opposing surfaces. A trunnion extends from one of the opposing surfaces. An airfoil is supported on the other of the opposing surfaces opposite the trunnion. The airfoil includes leading and trailing edges. An overhanging portion of the airfoil, which includes the trailing edge, extends beyond the circumference. A fillet joins the airfoil and the other opposing surface and extends along the other opposing surface in a lateral direction beyond the circumference toward the trailing edge. In one example, the fillet is provided about the entire perimeter of the airfoil. The airfoil includes pressure and suction sides. The circumference includes a relief cut extending from the suction side and adjoining a notch in the circumference to form an apex overlying the end surface.

Abstract: A shroud for supporting a variable vane in a compressor section for a gas turbine engine includes a pair of components which are secured together by a threaded fastener extending into a blind hole in one of the two components. Additional material forms on the component which includes the blind hole extends beyond a pivot axis for the vane such that there is an increased length of engagement between the threaded fastener and the blind hole. The blind hole eliminates the need for multiple nuts and reduces the radial height of the shroud to save additional weight.

Abstract: A barbed tape includes a central supporting portion and a plurality of barb clusters disposed at spaced apart locations along the central supporting portion, each barb cluster having first and second pairs of oppositely extending substantially planar barbs disposed on opposite edges of the central supporting portion and connected thereto, the barbs having a cross section which is at least partially arcuate, whereby the barbs are substantially stiffened against bending.