Gas turbine engine fuel injector
US5737921A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Apr 20, 1995 |
| Grant date | Apr 14, 1998 |
| Priority date | — |
| Expiry date | Apr 20, 2015 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A multi-stream fuel injector for a gas turbine engine comprises a plurality of concentric member which define a plurality of flow passages carrying HP compressor air or fuel/air mixture. One of the members is formed with a wide-angle, frusto-conical flared lip to propagate a wide-angle fuel/air mixture cone in the combustion region. The lip is of such a cross-sectional configuration that air flowing over the lip surface remains attached to the surface and flows in a non-turbulent manner, initially in a radially inward direction, and subsequently in a radially outward direction. The lip ensures that undesirable regions of recirculation are avoided around the fuel injector.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.