Premixed pilot nozzle for gas turbine combustor
US11371706B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 18, 2017 |
| Grant date | Jun 28, 2022 |
| Priority date | — |
| Expiry date | Aug 24, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00004
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.