Liquid fuel turbine engine for reduced oscillations
AssigneeSolar Turbines Incorporated
InventorMario E. Abreu
Life of this patent
Estimating the term…
Abstract
A gas turbine engine may include a plurality of pilot fuel supply lines configured to supply liquid fuel. Each pilot fuel supply line may be coupled to a respective fuel injector. The turbine engine may include a plurality of main fuel supply lines configured to supply liquid fuel. Each main fuel supply line may be coupled to a respective fuel injector. The turbine engine may also include a flow restriction provided in a first plurality of the plurality of main fuel supply lines. A second plurality of the plurality of main fuel supply lines may be free from the flow restriction.
Claims25
A gas turbine engine, comprising:
- a plurality of pilot fuel supply lines configured to supply liquid fuel, each pilot fuel supply line coupled to a respective fuel injector;
- a plurality of main fuel supply lines configured to supply liquid fuel, each main fuel supply line coupled to a respective fuel injector;
- and
- a flow restriction provided in a first plurality of the plurality of main fuel supply lines, and a second plurality of the plurality of main fuel supply lines being free from the flow restriction.
A gas turbine engine operating on liquid fuel, comprising:
- a plurality of fuel injectors arranged around a central axis, each fuel injector having a main fuel supply and a pilot fuel supply;
- a main liquid thel line coupled to each of the plurality of thel injectors, the main liquid fuel line being configured to provide the main fuel supply;
- a pilot liquid fuel line coupled to each of the plurality of fuel injectors, the pilot liquid fuel line being configured to provide the pilot fuel supply;
- and
- flow restriction devices coupled to the main liquid fuel lines of multiple fuel injectors of the plurality of fuel injectors, the flow restriction devices being configured to reduce the flow of main fuel to the multiple fuel injectors as compared to the main fuel flow to the remaining fuel injectors.
A gas turbine engine operating on liquid fuel, comprising:
- a plurality of fuel injectors arranged around a central axis, each fuel injector having a main fuel supply and a pilot fuel supply;
- conduits configured to direct liquid fuel from a common fuel supply to the main fuel supply of each fuel injector of the plurality of fuel injectors;
- and
- one or more restriction devices configured to reduce an amount of fuel flowing through the conduits coupled to multiple fuel injectors of the plurality of fuel injectors compared to the amount of fuel flowing through the conduits coupled to remaining fuel injectors.
A liquid fuel delivery system for a gas turbine engine, comprising:
- a main liquid fuel delivery system configured to deliver main fuel to fuel injectors of the gas turbine engine, the main liquid fuel delivery system including,
- a main fuel divider block supplied with liquid fuel from a fuel supply,
- conduits fluidly coupling the main fuel divider block to each fuel injector of the gas turbine engine, and
- restriction devices coupled to selected conduits to reduce an amount of fuel directed from the main fuel divider block to selected fuel injectors as compared to other fuel injectors of the gas turbine engine;
- and
- a pilot liquid fuel delivery system configured to deliver pilot fuel to the fuel injectors, the pilot liquid fuel delivery system including a pilot fuel divider block supplied with liquid fuel from a fuel supply.
Dependencies are inferred from the claim text.