Patent ID: 8616854
Filing Date: 2013-12-31
Classification: F01D,F02C,F05C,F05D,Y10T

Abstract:
1. A nose cone assembly for a gas turbine engine comprising: a spinner body having an outer surface and extending axially between an upstream portion generally tapering to a truncated first end and a base portion generally cylindrical in cross-section at a second end; a flange positioned radially inward of said outer surface and axially adjacent to said base portion; a plurality of first apertures defined in said flange for removably connecting said spinner body to a fan of a gas turbine engine; and a second aperture defined in said spinner body through which all of said plurality of first apertures can be accessed for attaching or removing said nose cone assembly from the fan, wherein the second aperture forms a tip opening of the spinner body, wherein a central axis of one of the plurality of first apertures extends in an unimpeded direction through the second aperture such that the central axis does not cross a supporting structure of the spinner body.