Turbine combustor with tangential fuel injection and bender jets
US4891936A · kind A · utility
48Cited by
17References
9Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 28, 1987 |
| Grant date | Jan 9, 1990 |
| Priority date | — |
| Expiry date | Dec 28, 2007 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2250/322
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The cost of fuel injection nozzles 50 and their tendency to clog in a gas turbine having an annular combustor 26 can be reduced by alternating the fuel injection nozzles 50 with bender jets 56 configured to introduce a combustion supporting gas into an annular combustion zone 40 at locations between the fuel injectors 50 to achieve uniform turbine inlet temperature distribution while requiring fewer of the nozzles 50 and allowing those nozzles 50 that are utilized to have larger fluid flow paths that are less prone to clogging.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.