System and method for diverting boundary layer air
US5779189A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 19, 1996 |
| Grant date | Jul 14, 1998 |
| Priority date | — |
| Expiry date | Mar 19, 2016 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A diverterless engine inlet system that integrates a "bump" surface with a forward swept, aft-closing cowl to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression surface raised outwardly from the body of the aircraft to form a portion of the inner surface of the inlet. The cowl couples to the body of the aircraft to form the remaining surfaces of the inlet and closes against the body of the aircraft at the aft-most points of the inlet opening. The bump and the cowl work together to divert low energy boundary layer air from the inlet during aircraft operation, thus eliminating the requirement for a boundary layer diverter. The diverterless inlet provides a lower cost, reduced complexity air induction system that can be used on a supersonic aircraft engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.