Gas turbine combustor fuel nozzle assembly and combustor liner having dilution holes in arrangements
US12215869B2 · kind B2 · utility
0Cited by
23References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Aug 21, 2023 |
| Grant date | Feb 4, 2025 |
| Priority date | — |
| Expiry date | Aug 21, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/03041
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.