Aircraft fuel control to subsets of fuel spray nozzles
US12168958B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 20, 2023 |
| Grant date | Dec 17, 2024 |
| Priority date | — |
| Expiry date | Jun 20, 2043 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D37/30
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of operating a gas turbine engine having a combustor having a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber. The fuel spray nozzles have a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. The combustor is operable in a condition in which the first subset of fuel spray nozzles are supplied with more fuel than the second subset of fuel spray nozzles. A ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. The method includes providing a fuel to the plurality of fuel spray nozzles having a calorific value of at least 43.5 MJ/kg. A gas turbine engine can be for an aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.