Combustion chamber of a gas turbine working on liquid fuel
US6378310B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 28, 1999 |
| Grant date | Apr 30, 2002 |
| Priority date | — |
| Expiry date | Jan 28, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/58
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion chamber of a gas turbine working on liquid fuel includes a tubular enclosure (2) having at least one pressurized air inlet, a liquid fuel injection means (6) positioned on or in proximity to the longitudinal axis (XX′) of the tubular enclosure, and an outlet to the turbine. The fuel injection means (6) includes a series of orifices (62) arranged so as to create separate fuel jets, the jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30° and 60° at the vertex thereof. The chamber includes at least two types of pressurized air inlets placed close to each other, the first one (7) taking in the air helically around the longitudinal axis of the combustion chamber, the second air inlet (8) being tangential to enclosure (2) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel. The assembly preferably works at a pressure ranging between 2 and 30 bars and with a fuel/air ratio ranging between 0.4 and 0.8.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.