Counterrotatable booster compressor assembly for a gas turbine engine
US6666017B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 24, 2002 |
| Grant date | Dec 23, 2003 |
| Priority date | — |
| Expiry date | May 29, 2022 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D25/04
- 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 includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan shaft extension at a first location so as to form a portion of an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan shaft extension at a second location so as to form a portion of an outer flowpath for the counterrotatable booster compressor, where each compressor blade of the second compressor blade row is positioned between the first and second plat…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.