Gas turbine engine comprising fuel-oil heat exchangers fluidly connected to fuel spray nozzles
US12378920B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 24, 2024 |
| Grant date | Aug 5, 2025 |
| Priority date | — |
| Expiry date | Jan 24, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/22
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
There is provided a method of operating a gas turbine engine including a combustor. The combustor includes a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the chamber. The nozzles include a first and second subset of fuel spray nozzles. The combustor is operable in a condition wherein the first subset is supplied with more fuel than the second. A ratio of the number of nozzles in the first subset to the second is 1:2 to 1:5. The method includes operating the engine so a reduction of 20-80% in an average of particles/kg of nvPM in the exhaust when the engine is operating at 85% available thrust for given operating conditions and when the engine is operating at 30% is obtained when fuel provided to the nozzles is a sustainable aviation fuel instead of a fossil-based hydrocarbon fuel. Also provided is a gas turbine engine for an aircraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.