Patent ID: 8596965
Filing Date: 2013-12-03
Classification: F01D,F05D

Abstract:
1. A compressor case support arrangement for a gas turbine engine comprising: a fan section having a central axis; a compressor case for housing a compressor; an inlet case for guiding air to said compressor, said compressor case positioned axially further from said fan section than said inlet case; and a support member extending between said fan section and said compressor case, wherein said support member restricts movement of said compressor case relative to said inlet case, wherein said compressor case includes a front compressor case portion and a rear compressor case portion, said rear compressor case portion being axially further from said inlet case than said front compressor case portion, wherein said support member extends between said fan section and said front compressor case portion, wherein said inlet case is removable from said gas turbofan engine separately from said compressor case.