Separate boundary layer engine inlet
US6527224B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Mar 23, 2001 |
| Grant date | Mar 4, 2003 |
| Priority date | — |
| Expiry date | Mar 23, 2021 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A dual boundary layer engine inlet for a turbofan propulsion engine of an aircraft having a first air inlet positioned generally within the boundary layer flowing around the exterior surface of the aircraft. A first passageway fluidly interconnects the first air inlet and the turbofan propulsion engine to provide air from the boundary layer to the bypass to reduce aerodynamic drag. A second air inlet is positioned generally outside of the boundary layer. This second passageway fluidly interconnecting the second air inlet and the turbofan propulsion engine to provide air outside of the boundary layer to the core and compressor of the turbofan engine to maintain engine efficiency.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.