Pilot injector fuel shifting in an axial staged combustor for a gas turbine engine
US10393030B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Oct 3, 2016 |
| Grant date | Aug 27, 2019 |
| Priority date | — |
| Expiry date | May 15, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at least one injection aperture a first injection depth from the exit of the swirler and a second subcircuit having at least one second injection aperture located at a second injection depth from the exit of the swirler, wherein the first injection depth is greater than the second injection depth.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.