Assembly of a gas turbine with combustion chamber air bypass

Patent metadata

Field	Value
Publication number	US-11435083-B2
Application number	US-202117351903-A
Country	US
Kind code	B2
Filing date	Jun 18, 2021
Priority date	Jun 19, 2020
Publication date	Sep 6, 2022
Grant date	Sep 6, 2022

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.

First claim

The invention claimed is:

1. 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.

2. The assembly according to claim 1 ,
wherein a temperature curve of a temperature of the air conduction channel and/or of a temperature adjoining the air conduction channel varies from an inflow side, on which the air flows into the air conduction channel, to an outflow side, on which the air flows out of the air conduction channel, by maximally 10%.

3. The assembly according to claim 1 ,
wherein the air conduction channel is formed by a tubing, at least in sections.

4. The assembly according to claim 1 ,
wherein the air conduction channel is formed by the cover, at least in sections.

5. The assembly according to claim 1 ,
wherein the air conduction channel is formed by the swirler, at least in sections.

6. 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.

7. The assembly according to claim 1 , further comprising:
a valve arranged in the air conduction channel, configured to adjust a flow rate of the bypass flow.

8. The assembly according to claim 1 ,
wherein the cover and the swirler are formed integrally with one another.

9. The assembly according to claim 6 ,
wherein the air conduction channel conducts the bypass flow into an annular space formed in the combustion chamber, which annular space surrounds the combustion zone.

10. The assembly according to claim 9 ,
wherein at least one flow body is provided on the annular space, by way of which the bypass flow is conducted into a section of the combustion chamber located outside the annular space.

11. The assembly according to claim 10 ,
wherein the at least one flow body introduces the bypass flow into a section of the combustion chamber located outside the annular space such that the bypass flow in the combustion chamber does not pass through the combustion zone and thus a combustion of a mixture of a fuel and air of the main flow occurring in the combustion zone is not influenced.

12. The assembly according to claim 1 ,
wherein the combustion chamber is a tubular combustion chamber.

13. The assembly according to claim 1 , further comprising:
a pressure housing surrounding the combustion chamber,
wherein the air feed is formed by an air space between a combustion chamber wall delimiting the combustion chamber and the pressure housing annularly surrounding the combustion chamber wall.

14. 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.

Assignees

• Man Energy Solutions Se

Inventors

• Cosic Bernhard
• Genin Franklin

Classifications

• F23R3/16

  with devices inside the flame tube or the combustion chamber to influence the air or gas flow · CPC title

• F23R3/12 Primary

  inducing a vortex · CPC title

• F23R3/26 Primary

  Controlling the air flow · CPC title

• F23R3/14

  by using swirl vanes · CPC title

• F05D2220/32

  in gas turbines · CPC title