Combustion chamber of a gas turbine
US5081844A · kind A · utility
27Cited by
5References
5Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 2, 1990 |
| Grant date | Jan 21, 1992 |
| Priority date | — |
| Expiry date | Mar 2, 2010 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E20/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In an annular combustion chamber (A), a row of premixed burners (B, C) are located in the peripheral direction at the inlet end. The large premixed burners (B), which are the main burners of the annular combustion chamber (A), and the small premixed burners (C), which are the pilot burners of the annular combustion chamber, are located alternately relative to one another and at a uniform distance apart. Both the main burners (B) and the pilot burners (C) enter into a single annular front wall (10).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.