Gas turbine engine compressor case mounting arrangement
AssigneeUnited Technologies Corporation
InventorsBrian D. Merry, Gabriel L. Suciu, Christopher M. Dye
Life of this patent
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Abstract
A compressor case support arrangement for a gas turbine engine includes a fan section having a central axis and a compressor case for housing a compressor. An inlet case guides air to the compressor. The compressor case is positioned axially further from the fan section than the inlet case. A support member extends between the fan section and the compressor case. The support member restricts movement of the compressor case relative to the inlet case. The support member is positioned axially further from the fan section than the plumbing access area.
Claims16
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.
A compressor case support arrangement for a gas turbine engine comprising:
- a fan section having a central axis;
- a plumbing access area;
- 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, said support member positioned axially further from said fan section than said plumbing access area.
Dependencies are inferred from the claim text.