Gas turbine engine front architecture modularity
US7955046B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 25, 2007 |
| Grant date | Jun 7, 2011 |
| Priority date | — |
| Expiry date | Feb 8, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is disclosed that includes a spool having a compressor section. An inlet case is arranged axially upstream from the compressor section. A gearbox is secured to the inlet case. The gearbox couples the spool and a fan. A sealing assembly is arranged between the inlet case and the gearbox to provide a sealed bearing compartment. The inlet case, gearbox and seal assembly provide a module. A fastening element removably secures the module to the spool. The gas turbine engine can be serviced by disconnecting the fastening element from the engine core. The gearbox and inlet case can be removed as a module from the engine core without disassembling the gearbox.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.