Combustion chamber for a gas turbine
AssigneeSiemens Aktiengesellschaft
InventorsPeter Kaufmann, Werner Krebs
Life of this patent
Estimating the term…
Abstract
A combustion chamber for a gas turbine is provided. The combustion chamber comprises at least one first and one second jet carrier, of which at least one is provided for injecting an operating gas in the combustion chamber such that waste gas fanned in the flame zone thereof is circulated to a mixing zone of the first jet carrier. In order to achieve a compact combustion chamber, the jet carriers are positioned in relation to each other such that waste gas from the flame zone of the first jet carrier flows directly to the mixing zone of the second jet carrier.
Claims21
-13. (canceled)
A combustion chamber for a gas turbine, comprising:
- a first jet carrier;
- a second jet carrier;
- and
- a combustion space,
- wherein at least one of the first jet carrier or the second jet carrier injects an operating gas in such a way into the combustion space that a waste gas is formed in a flame zone of the respective jet carrier located in the combustion space,
- wherein the waste gas is recirculated into a first mixing zone of the first jet carrier,
- wherein the first jet carrier and the second jet carrier are positioned such that the waste gas from a first flame zone of the first jet carrier will flow directly into a second mixing zone of the second jet carrier, and
- wherein flame-stabilizing is achieved in the second mixing zone using the hot waste gas with no recirculating of the waste gas.
A system, comprising:
- a combustion chamber of a gas turbine, comprising:
- a first jet carrier,
- a second jet carrier, and
- a combustion space,
- wherein at least one of the first jet carrier and the second jet carrier injects an operating gas in such a way into the combustion space that a waste gas is formed in a flame zone of the respective jet carrier located in the combustion space,
- wherein the waste gas is recirculated into a first mixing zone of the first jet carrier,
- wherein the first jet carrier and the second jet carrier are positioned such that the waste gas from a first flame zone of the first jet carrier will flow directly into a second mixing zone of the second jet carrier, and
- wherein flame-stabilizing is achieved in the second mixing zone using the hot waste gas with no recirculating of the waste gas;
- and
- a control unit provided to control a distribution of a combustion gas between the first jet carrier and the second jet carrier as a function of a load range of an operation of the gas turbine.
A gas turbine, comprising:
- a combustion chamber, comprising:
- a first jet carrier,
- a second jet carrier, and
- a combustion space,
- wherein at least one of the first jet carrier and the second jet carrier injects an operating gas in such a way into the combustion space that a waste gas is formed in a flame zone of the respective jet carrier located in the combustion space,
- wherein the waste gas is recirculated into a first mixing zone of the first jet carrier,
- wherein the first jet carrier and the second jet carrier are positioned such that the waste gas from a first flame zone of the first jet carrier will flow directly into a second mixing zone of the second jet carrier, and
- wherein flame-stabilizing is achieved in the second mixing zone using the hot waste gas with no recirculating of the waste gas.
Dependencies are inferred from the claim text.