Transition shoulder system and method for diverting boundary layer air
US5749542A · kind A · utility
20Cited by
5References
28Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 28, 1996 |
| Grant date | May 12, 1998 |
| Priority date | — |
| Expiry date | May 28, 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 transition shoulder into a system for diverting air from the inlet of an aircraft engine. ????? 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 transition surface works with the compression surface to divert low energy boundary layer air from the inlet during aircraft operation.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.