Combustor for a gas turbine engine
US12072100B1 · kind B1 · utility
1Cited by
29References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 7, 2023 |
| Grant date | Aug 27, 2024 |
| Priority date | — |
| Expiry date | Nov 7, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/16
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for an aircraft gas turbine engine includes a dome structure, a swirler assembly connected to the dome structure, and a cowl connected to the dome structure and defining a plenum between the dome structure and the cowl, and surrounding the swirler assembly. The cowl includes an airflow opening through an upstream wall portion of the cowl for providing a flow of compressed air into the plenum. In addition, the cowl includes a cowl steam channel therewithin and a plurality of steam injection nozzles that provide a flow of steam from the cowl steam channel into the plenum.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.