Fuel nozzle for hydrogen-based fuel operation
US12326256B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 4, 2024 |
| Grant date | Jun 10, 2025 |
| Priority date | — |
| Expiry date | Apr 4, 2044 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00002
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fuel nozzle for a gas turbine engine combustor includes a fuel nozzle assembly including an inflow tube disposed along and a nozzle axis, the inflow tube defining an inner air passage and a liquid swirler concentrically disposed about the inflow tube. The liquid swirler includes a liquid swirler inner wall, a liquid swirler outer wall having a liquid swirler outer wall end portion at a downstream-most position and angled radially inward toward the nozzle axis, and an annular liquid passage defined therebetween. The fuel nozzle assembly further includes a radial air swirler (RAS) concentrically disposed about the liquid swirler outer wall, the RAS including an RAS inner wall, an RAS outer wall having an end cap at a downstream-most position, and an annular gas passage defined therebetween. The end cap has a radiused inner surface and a contoured outer surface. The fuel nozzle assembly further includes a guide swirler disposed concentrically about the RAS outer wall, the guide swirler comprising an annular air passage angled radially inward toward the nozzle axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.