Gas turbine engine compressor case mounting arrangement
US8075261B2 · kind B2 · utility
65Cited by
11References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 21, 2007 |
| Grant date | Dec 13, 2011 |
| Priority date | — |
| Expiry date | Oct 12, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.