Gas turbine engine afterburner
US10634352B2 · kind B2 · utility
0Cited by
58References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 28, 2017 |
| Grant date | Apr 28, 2020 |
| Priority date | — |
| Expiry date | Jul 3, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00015
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages are arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.