Gas turbine engine compressor case mounting arrangement
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.
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.
2. The compressor case support arrangement of claim 1 , including an intermediate case for supporting said rear compressor case portion.
3. The compressor case support arrangement of claim 2 , wherein said intermediate case supports said rear compressor case portion adjacent a bleed ring.
4. The compressor case support arrangement of claim 1 , wherein said inlet case is removable from said gas turbofan engine separately from said compressor case.
5. The compressor case support arrangement of claim 1 , including a seal adjacent a front portion of said compressor case, said seal for restricting fluid movement between said compressor case and said inlet case.
6. The compressor case support arrangement of claim 5 , wherein said seal permits relative movement between said compressor case and said inlet case.
7. The compressor case support arrangement of claim 6 , wherein said seal is a “W” seal.
8. The compressor case support arrangement of claim 1 , wherein said compressor case houses a low pressure compressor.
9. The compressor case support arrangement of claim 1 , including a plumbing access area positioned between said fan section and said support member.
10. The compressor case support arrangement of claim 1 , wherein said support member comprises a guide vane.
11. 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; 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
wherein said plumbing access area includes at least one of an air connection and an oil connection,
wherein said inlet case includes said plumbing access area.
12. The compressor support arrangement of claim 11 , including a cover for covering at least a portion of said plumbing access area.
13. The compressor case support arrangement of claim 11 , wherein said support member comprises a guide vane.