Gas turbine engine compressor arrangement
US8807477B2 · kind B2 · utility
10Cited by
50References
21Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 30, 2011 |
| Grant date | Aug 19, 2014 |
| Priority date | — |
| Expiry date | Dec 22, 2032 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D27/406
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.