Interface ring for gas turbine fuel nozzle assemblies
US9291102B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 7, 2011 |
| Grant date | Mar 22, 2016 |
| Priority date | — |
| Expiry date | Jul 22, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each include a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures defines a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.