High bypass ratio counterrotating turbofan engine
US4790133A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Mar 10, 1988 |
| Grant date | Dec 13, 1988 |
| Priority date | — |
| Expiry date | Mar 10, 2008 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02K3/072
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.