Counterrotatable booster compressor assembly for a gas turbine engine
US6739120B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 29, 2002 |
| Grant date | May 25, 2004 |
| Priority date | — |
| Expiry date | Sep 6, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C3/067
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft, the counterrotatable booster compressor assembly including a first compressor blade row connected to the first drive shaft and a second compressor blade row interdigitated with the first compressor blade row and connected to the second drive shaft. A portion of each fan blade of the second fan blade row extends through a flowpath of the counterrotatable booster compressor so as to function as a compressor blade in the second compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan blade of the second fan blade row at a first location so as to form an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan blade of the second fan blade row at a second location so as to form an outer flowpath for the counterrotatable booster compressor.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.