Multi-fuel gas turbine engine with water injection
AssigneePratt & Whitney Canada Corp.
InventorScott Smith
Life of this patent
Estimating the term…
Abstract
A method of operation is provided during which a gaseous fuel is directed through a gas manifold to a plurality of fuel injectors during a first mode of operation. The gaseous fuel may be or otherwise include hydrogen gas. A gas turbine engine includes the gas manifold, a liquid manifold and the fuel injectors. A first liquid fluid is directed through the liquid manifold to the fuel injectors during the first mode of operation. The first liquid fluid may be or otherwise include water. A second liquid fluid is directed through the liquid manifold to the fuel injectors during a second mode of operation. The second liquid fluid may be or otherwise include liquid fuel.
Claims17
A method of operation, comprising:
- delivering a gaseous fuel to a plurality of fuel injectors through a gas manifold of a gas turbine engine during a first mode of operation, wherein the gaseous fuel consists of hydrogen gas;
- delivering a first liquid fluid to the plurality of fuel injectors through a liquid manifold of the gas turbine engine during the first mode of operation, wherein the gas turbine engine includes the gas manifold, the liquid manifold, and the plurality of fuel injectors, the liquid manifold being different and independent from the gas manifold, the liquid manifold is fluidly discrete of the gas manifold, and wherein the first liquid fluid comprises water;
- and
- delivering a second liquid fluid to the plurality of fuel injectors through the liquid manifold during a second mode of operation, wherein the second liquid fluid is different from the first liquid fluid, and wherein the second liquid fluid comprises liquid fuel
- wherein a first of the plurality of fuel injectors includes a liquid circuit and a gas circuit, the liquid circuit receives the first liquid fluid or the second liquid fluid from the liquid manifold, the gas circuit receives the gaseous fuel from the gas manifold, and the gas circuit is different and independent from the liquid circuit.
An aircraft system, comprising:
- a combustor comprising a combustion chamber;
- and
- a fluid delivery system including a hydrogen fuel source, a water source, a liquid fuel source, a gas manifold, a liquid manifold and a plurality of fuel injectors, the liquid manifold independent from and fluidly discrete of the gas manifold, the liquid fuel source fluidly couplable to the liquid manifold, the water fuel source fluidly coupled to the liquid manifold and fluidly decoupled from the gas manifold, the hydrogen fuel source fluidly couplable to the gas manifold, a first of the plurality of fuel injectors including a liquid inlet and a gas inlet, the liquid inlet in fluid communication with the liquid manifold, and the gas inlet in fluid communication with the gas manifold;
- the fluid delivery system configured to direct and deliver hydrogen gas from the hydrogen fuel source, through the gas manifold, to the plurality of fuel injectors for injection into the combustion chamber during a first mode of operation;
- the fluid delivery system configured to direct and deliver water from the water source, through the liquid manifold, to the plurality of fuel injectors for injection into the combustion chamber during the first mode of operation;
- and
- the fluid delivery system configured to direct and deliver liquid fuel from the liquid fuel source, through the liquid manifold, to the plurality of fuel injectors for injection into the combustion chamber during a second mode of operation.
Dependencies are inferred from the claim text.