Patent ID: 8894361
Filing Date: 2014-11-25
Classification: F01D,F02C,F04D

Abstract:
1. A gas turbine engine compressor comprising: a compressor case comprising spaced apart inner and outer walls; an axial rotor positioned within said outer wall; a bearing structure for supporting said axial rotor for rotation; a plurality of inlet guide vanes coupled to said outer wall of said compressor case and radially extending inwardly, wherein each of at least a sub-set of said inlet guide vanes comprises a radial bore; and a plurality of tie members, each of said tie members being received within a respective one of said inlet guide vane radial bores, each said tie member comprising an outward end attached to said compressor case outer wall so as to be non-rotational relative to said compressor case outer wall and an inward end attached to said compressor case inner wall, wherein said tie members are held in tension between said compressor case inner and outer walls and function to transfer load forces from said compressor case inner wall to said compressor case outer wall.