Patent ID: 8920117
Filing Date: 2014-12-30
Classification: F01D

Abstract:
1. A gas turbine engine vane structure comprising: an annular duct defined between outer and inner shrouds, at least the outer shroud including a single-piece annular skin of sheet metal, the skin having an inner surface exposed to the duct and an outer surface surrounding the duct; a plurality of circumferentially spaced vanes extending from the inner shroud radially outwardly to a radial outer end which is affixed to the inner surface of the skin by one of welding and brazing; a plate affixed by one of welding and brazing to the outer surface of the skin at a location corresponding to each vane, the plate having an outer periphery which extends at least on one direction beyond an outer periphery of the respective vane; and wherein at least a number of the plates define two openings which are in fluid communication with a number of the vanes which are hollow, said communication through an opening defined in the skin in a corresponding one of the locations, the two openings separated by a bridge of said plates extending from a pressure side to a suction side of the plate.