Assembly of a gas turbine with combustion chamber air bypass
AssigneeMAN Energy Solutions SE
InventorsBernhard Cosic, Franklin Genin
Life of this patent
Estimating the term…
Abstract
An assembly for a gas turbine having a combustion chamber, a swirler, a combustion zone in the combustion chamber, and an air feed. In a transition region from the air feed to the swirler that is flowed through by the air, a plenum is formed and the assembly adjoining the plenum has the swirler, the combustion chamber, and a cover closing the combustion chamber. The assembly has an air conduction channel designed to conduct part of the air flow flowing into the assembly into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.
Claims14
An assembly for a gas turbine comprising:
- a combustion chamber;
- a swirler;
- a cover;
- a combustion zone arranged in an interior space of the combustion chamber;
- an air feed, via which an air flow is fed to the combustion chamber;
- a plenum is formed in a transition region that can be flowed through by air from the air feed to the swirler and an assembly adjoining the plenum comprises the swirler and the combustion chamber and the cover closing off the combustion chamber;
- and
- an air conduction channel configured as a combustion chamber air bypass, which conducts a part of the air flow flowing into the assembly through the air feed from the plenum through the cover and through the swirler past the combustion zone into the combustion chamber, so that air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.
An assembly for a gas turbine comprising:
- a combustion chamber;
- a swirler;
- a cover;
- a combustion zone arranged in an interior space of the combustion chamber;
- an air feed, via which an air flow is fed to the combustion chamber;
- a plenum is formed in a transition region that can be flowed through by air from the air feed to the swirler and an assembly adjoining the plenum comprises the swirler and the combustion chamber and the cover closing off the combustion chamber;
- and
- an air conduction channel configured as a combustion chamber air bypass, which conducts a part of the air flow flowing into the assembly through the air feed from the plenum through the cover and through the swirler past the combustion zone into the combustion chamber, so that air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone,
- wherein the air conduction channel leads from the plenum through the cover into an outer region,
- the air conduction channel diverts a bypass flow in the outer region on a side of the cover facing away from the combustion chamber, and
- the air conduction channel leads from the outer region through the cover into the swirler and from the swirler into a section of the combustion chamber, which in a flow direction of the air flow is arranged after and/or offset to the combustion zone.
A gas turbine comprising:
- a combustion chamber;
- a swirler;
- a cover;
- a combustion zone arranged in an interior space of the combustion chamber;
- an air feed, via which an air flow is fed to the combustion chamber;
- a plenum is formed in a transition region that can be flowed through by air from the air feed to the swirler and an assembly adjoining the plenum comprises the swirler and the combustion chamber and the cover closing off the combustion chamber;
- and
- an air conduction channel configured as a combustion chamber air bypass, which conducts a part of the air flow flowing into the assembly through the air feed from the plenum through the cover and through the swirler past the combustion zone into the combustion chamber, so that the air flow leading through the air feed is divided into a main flow leading through the swirler into the combustion zone and a bypass flow leading past the combustion zone.
Dependencies are inferred from the claim text.