Combined stage single shaft turbofan engine
US7055306B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 30, 2003 |
| Grant date | Jun 6, 2006 |
| Priority date | — |
| Expiry date | May 19, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF04D25/16
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbofan engine includes a combined stage rotor mounted for common rotation with a shaft, a compressor stage, and a turbine stage. Each of the plurality of fan blades of the combined stage rotor are contiguous with a respective compressor blade. The combined stage rotor is located at a junction between a fan bypass duct and a core duct. The fan bypass stage portion includes a plurality of the fan blades which communicate incoming airflow into fan bypass airflow through the fan bypass duct. The compressor stage portion includes a plurality of the compressor blades which communicated airflow into core airflow through the core duct. The plurality of fan blades extend substantially perpendicular to the plurality of compressor blades such that the plurality of compressor blade portions extend at least partially into the core duct and preferably will include splitters for enhanced efficiency.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.