Gas turbine combustion chamber
US5465577A · kind A · utility
3Cited by
8References
6Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Nov 10, 1994 |
| Grant date | Nov 14, 1995 |
| Priority date | — |
| Expiry date | Nov 10, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/42
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine combustion chamber, which consists of an inlet zone (1) with injection, an ignition delay zone (2), a reaction zone (3), a burn-out zone (4) and a transition zone (5) to the turbine, the reaction zone (3) has a cross-section which increases in such a way that the gas dynamics of the combustion process can take place at constant pressure or constant Mach number. By this means, the total pressure loss and the combustion chamber length necessary for the combustion are reduced and this is reflected in an improvement to the efficiency and the output.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.