Patent ID: 8740557
Filing Date: 2014-06-03
Classification: F01D,F05D

Abstract:
1. A static vane ring for a gas turbine engine comprising: an annular duct defined between an annular outer duct wall and an annular inner duct wall, each of the outer and inner duct walls defining a gas path surface and a back surface opposed to the gas path surface; a circumferential array of aerodynamic struts extending radially across the duct and fixedly mounted to the outer and inner duct walls wherein each strut has a hollow configuration defined by a shell wail and opposed enlarged ends each including an enlarged hollow section extending laterally and outwardly from the shell wall of a transit radial portion, and at each enlarged end a fillet radius defined between the transit radial portion and the enlarged hollow section, the enlarged hollow section received in an opening defined in a corresponding one of the outer and inner duct walls, the enlarged end including a radial projection defined along an outer periphery of the enlarged hollow section and projecting radially from the enlarged hollow section, thereby defining an enlarged opening within the radial projection in communication with the hollow configuration of the strut, and wherein a welded or brazed joint extends between the corresponding back surface and the enlarged hollow section, and wherein an interior surface of the enlarged hollow section curves between the transit radial portion and the enlarged section.