Gas fuel turbine engine for reduced oscillations

A gas turbine engine operating on gaseous 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 first main fuel manifold circumferentially disposed about the turbine engine and supplied with the gaseous fuel from a common fuel supply, the first main fuel manifold being fluidly coupled to a first set of fuel injectors of the plurality of fuel injectors to direct the main fuel supply to the first set of fuel injectors;
• a second main fuel manifold circumferentially disposed about the turbine engine and supplied with the gaseous fuel from the common fuel supply, the second main fuel manifold being fluidly coupled to a second set of fuel injectors of the plurality of fuel injectors to direct the main fuel supply to the second set of fuel injectors;
• and
• a restriction device fluidly coupled to the second main fuel manifold to reduce the flow of gaseous fuel from the common supply into the second main fuel manifold.

A gas turbine engine operating on gaseous 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 gaseous fuel from a common fuel supply to the main fuel supply of each fuel injector of the plurality of fuel injectors;
• and
• a restriction device 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 gaseous fuel delivery system for a gas turbine engine, comprising:

• a main gaseous fuel delivery system configured to deliver main fuel to fuel injectors of the gas turbine engine, the main gaseous fuel delivery system including,
• a first main fuel manifold arranged circumferentially about the gas turbine engine,
• a second main fuel manifold arranged circumferentially about the gas turbine, the first main fuel manifold and the second main fuel manifold being supplied with gaseous fuel from a common fuel supply pipe, and
• a restriction device fluidly coupling the second main fuel manifold and the common fuel supply pipe, the restriction device being configured to restrict the flow of fuel into the second main fuel manifold compared to the flow of fuel into the first main fuel manifold;
• and
• a pilot gaseous fuel delivery system configured to deliver pilot fuel to the fuel injectors, the pilot gaseous fuel delivery system including a pilot fuel manifold arranged circumferentially about the gas turbine engine.