Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection
US5319935A · kind A · utility
83Cited by
7References
37Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 13, 1993 |
| Grant date | Jun 14, 1994 |
| Priority date | — |
| Expiry date | Apr 13, 2013 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/346
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Gas turbine engine combustion chamber has staged combustion to reduce nitrous oxides and includes a first radial flow swirler and a second radial flow swirler located axially of an annular mixing zone with each swirler having vanes for rotating the incoming air in substantially opposite directions relative to each other; first and second fuel injectors are provided with a first fuel injectors located in one of the passages of each of the first and second swirlers and with the second fuel injectors located upstream of the passages of the first and second swirlers.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.