Reverse-flow gas turbine combustion system
AssigneeGeneral Electric Company
InventorsGeoffrey David Myers, Thomas Edward Johnson, Stefan Maier, Stanley Kevin Widener
Life of this patent
Estimating the term…
Abstract
A gas turbine combustion system for burning air and fuel into exhaust gases. The gas turbine combustion system may include a combustor, a turbine nozzle integral with the combustor for providing the air to the combustor, and a fuel injector for providing the fuel to the combustor. The turbine nozzle and the fuel injector are positioned within the combustor such that a mixture of the air and the fuel flows in a first direction and the exhaust gases flow in a second direction.
Claims17
A gas turbine combustion system for burning air and fuel into exhaust gases, comprising:
- a combustor;
- a turbine nozzle integral with the combustor for directing the exhaust gases out of the combustor;
- an air intake for providing the air to the combustor;
- and a fuel injector for providing the fuel to the combustor;
- the air intake and the fuel injector concentrically positioned within the turbine nozzle at an exit end of the combustor, the air intake comprising a first tube concentrically positioned within the turbine nozzle and the fuel injector comprising a second tube concentrically positioned within the first tube within the turbine nozzle, such that one or both of the air and the fuel cool the turbine nozzle, a mixture of the air and the fuel flows in a first direction and the exhaust gases flow in a second direction.
A gas turbine combustion system for burning air and fuel into exhaust gases, comprising:
- a reverse flow combustor;
- a turbine nozzle positioned at a downstream end of the combustor for directing the exhaust gases out of the combustor;
- a cooling airflow channel positioned about the combustor;
- one or more air intake channels positioned to communicate air from the cooling airflow channel into the combustor;
- and a fuel injector positioned within one of the one or more air intake channels for providing the fuel to the combustor, wherein the one or more air intake channels comprise a first tube concentrically positioned within the turbine nozzle and the fuel injector comprises a second tube concentrically positioned within the first tube within the turbine nozzle.
A method for burning air and fuel into exhaust gases in a gas turbine combustion system, comprising:
- providing air to the combustion system through an air intake, the air intake comprising a first tube concentrically positioned within the turbine nozzle;
- providing fuel to the combustion system through a fuel intake, the fuel intake comprising a second tube concentrically positioned within the first tube;
- premixing substantially all of the air and the fuel to create an air-fuel mixture;
- injecting the air-fuel mixture into the combustor in a direction traveling away from the turbine nozzle;
- reacting the air-fuel mixture in a reaction zone to create the exhaust gases;
- and reversing the flow of the exhaust gases to travel toward the turbine nozzle.
Dependencies are inferred from the claim text.