Combustor arrangement for a gas turbine
AssigneeAnsaldo Energia Switzerland AG
InventorsAdnan Eroglu, Andrea Ciani, Douglas Anthony Pennell
Life of this patent
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Abstract
A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.
Claims20
A combustor arrangement for a gas turbine assembly, comprising:
- a first burner;
- a first combustion chamber;
- a mixer for admixing a dilution gas to hot gases leaving the first combustion chamber during operation;
- a second burner;
- a second combustion chamber arranged sequentially in a fluid flow connection, wherein the first burner, the first combustion chamber, the mixer, the second burner and the second combustion chamber are arranged in a row to form a flow path extending between the first combustion chamber and the second burner;
- a central lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer;
- wherein the central lance body includes at least one air duct for providing air for the mixer between the first burner and the second burner, wherein the air is to be injected during operation into the combustor arrangement through air supply elements;
- and
- wherein the central lance body comprises at least one fuel duct arranged within the central lance body and configured to provide fuel for the second burner, the at least one fuel duct having a curled duct on an input side, a longitudinal duct extending from the curled duct along a longitudinal axis of the central lance body to an L-shaped outlet, and wherein the L-shaped outlet is configured to provide the fuel to the second burner.
A combustor arrangement for a gas turbine assembly, comprising:
- a first burner;
- a first combustion chamber;
- a mixer for admixing a dilution gas to hot gases leaving the first combustion chamber during operation;
- a second burner;
- a second combustion chamber arranged sequentially in a fluid flow connection, wherein the first burner, the first combustion chamber, the mixer, the second burner and the second combustion chamber are arranged in a row to form a flow path extending between the first combustion chamber and the second burner;
- a central lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer;
- wherein the central lance body includes at least one air duct for providing air for the mixer between the first burner and the second burner, wherein the air is to be injected during operation into the combustor arrangement through air supply elements;
- wherein the central lance body comprises at least one fuel duct arranged within the central lance body and configured to provide fuel for the second burner, the at least one fuel duct having a curled duct on an input side, a longitudinal duct extending from the curled duct along a longitudinal axis of the central lance body to an outlet, and wherein the outlet is configured to provide the fuel to the second burner;
- and
- wherein the central lance body is removably mounted in the combustor arrangement, and wherein a cross section of the flow path increases in a counter flow direction such that the central lance body and fuel injectors extending from the central lance body are retractable in an axial direction out of the flow path.
Dependencies are inferred from the claim text.