Gas turbine combustor having secondary fuel nozzles with plural passages for injecting a diluent and a fuel
US11846426B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 9, 2021 |
| Grant date | Dec 19, 2023 |
| Priority date | — |
| Expiry date | Aug 9, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00002
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine including a compressor section, a combustor for combusting a fuel, and a turbine. Compressed air flows through a combustion liner of the combustor in a bulk airflow direction. The combustor includes a primary fuel nozzle and a secondary fuel nozzle. The secondary fuel nozzle is downstream of the primary fuel nozzle in the bulk airflow direction. The primary fuel nozzle is configured to inject a primary portion of the fuel into a primary combustion zone, and the secondary fuel nozzle is configured to inject a secondary portion of the fuel into a secondary combustion zone. The secondary combustion zone is located downstream of the primary combustion zone in the bulk airflow direction. The fuel may be one of diatomic hydrogen fuel and a hydrogen enriched fuel.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.