Patent ID: 9121367
Filing Date: 2015-09-01
Classification: F02C,F02K,F05D

Abstract:
1. An 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 the compressor, the compressor case positioned axially further from the fan section than the inlet case; a support member extending between the fan section and the compressor case wherein the support member restricts movement of the compressor case relative to the inlet case; the compressor case includes an upstream compressor case portion and a downstream compressor case portion, the downstream compressor case portion being axially further from the inlet case than the upstream compressor case portion, wherein the support member extends between the fan section and the upstream compressor case portion, and the inlet case is removable from the gas turbofan engine separately from the compressor case; the compressor case includes a low pressure compressor section and a high pressure compressor section.