Swirler for combustor of gas turbine engine
US10591163B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 21, 2017 |
| Grant date | Mar 17, 2020 |
| Priority date | — |
| Expiry date | May 8, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/286
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes an annular combustor shell, the annular combustor shell defining a combustion chamber, and a fuel injector extending at least partially into the combustion chamber, and configured to deliver a flow of fuel and a flow of combustion air into the combustion chamber for combustion. The fuel injector includes a swirler with a swirler exit having a circumferential width along a circumferential axis greater than a radial width along a radial axis. A swirler for a gas turbine engine includes a swirler entrance and a swirler exit. The swirler exit has a circumferential width along a curvilinear circumferential axis greater than a radial width along a radial axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.