Aircraft engine apparatus with reduced inlet vortex
US6129309A · kind A · utility
30Cited by
15References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 24, 1998 |
| Grant date | Oct 10, 2000 |
| Priority date | — |
| Expiry date | Jul 24, 2018 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/0273
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft engine apparatus with a reduced inlet vortex is provided which utilizes a vortex disruption system that periodically discharges pulses of engine bleed fluid through at least one outlet port opening through the inlet of the engine nacelle to disrupt the engine inlet vortex. The vortex disruption system thereby prevents ingestion of foreign matter into the engine inlet without sacrificing engine power, efficiency, or aircraft cruise performance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.