A fuel system (10) for a gas turbine engine that improves efficiency by supplying fuel to a primary stage (14) and secondary stage (16) via a common fuel source (18) is disclosed. The fuel system (10) may be formed from first and second primary injector assembly stages (20, 22) and a first premix injector assembly stage (24) positioned upstream from a combustor chamber (26), whereby the first premix injector assembly stage (24) is a secondary injector system. The second primary stage (22) and the first premix stage (24) may be in fluid communication with the same fuel source (18) to eliminate duplicative components found within systems where fuel is supplied individually to the second primary stage and the first premix stage. In at least one embodiment, the second primary injector assembly stage (22) and the first premix injector assembly stage (24) may each be in communication with a fuel manifold (28) configured to supply more fuel to the second primary stage (22) than the first premix stage (24).

A system includes a metering module that receives fluid through a fluid inlet. The metering module includes a rotating component driven by the fluid, an electric machine, and a controller. The fluid is received from the fluid inlet at an inlet flow rate, and the rotating component provides the fluid to an outlet of the rotating component at an outlet pressure. The electric machine is configured to generate electrical power in response to rotation of the rotating component. The controller is powered by the electrical power generated by the electric machine, and controls a rotational speed of the rotating component to control the outlet pressure.

A system includes a metering module that receives fluid through a fluid inlet. The metering module includes a rotating component driven by the fluid, an electric machine, and a controller. The fluid is received from the fluid inlet at an inlet flow rate, and the rotating component provides the fluid to an outlet of the rotating component at an outlet pressure. The electric machine is configured to generate electrical power in response to rotation of the rotating component. The controller is powered by the electrical power generated by the electric machine, and controls a rotational speed of the rotating component to control the outlet pressure.

The invention relates to a turbine engine fuel injection architecture including: two fuel injection manifolds (30A, 30B), each manifold being suitable for dispensing a fuel flow to at least one associated injector; a main fuel-proportioning device (32) suitable for proportioning a total fuel flow (Q) to be supplied to at least both injection manifolds (30A, 30B); and a distribution proportioning device (31), located between the main fuel-proportioning device (32) and the injection manifolds (30A, 30B) and suitable for distributing at least part of the total fuel flow between both manifolds. The architecture is characterized in that it also includes a bypass valve (35) suitable for discharging a flow from a first manifold (30A, 30B) to a second manifold (30B, 30A), in the event of excess fuel pressure in the first manifold. The invention also relates to a turbine engine combustion assembly including said architecture.

The invention relates to a turbine engine fuel injection architecture including: two fuel injection manifolds (30A, 30B), each manifold being suitable for dispensing a fuel flow to at least one associated injector; a main fuel-proportioning device (32) suitable for proportioning a total fuel flow (Q) to be supplied to at least both injection manifolds (30A, 30B); and a distribution proportioning device (31), located between the main fuel-proportioning device (32) and the injection manifolds (30A, 30B) and suitable for distributing at least part of the total fuel flow between both manifolds. The architecture is characterized in that it also includes a bypass valve (35) suitable for discharging a flow from a first manifold (30A, 30B) to a second manifold (30B, 30A), in the event of excess fuel pressure in the first manifold. The invention also relates to a turbine engine combustion assembly including said architecture.

A split control unit in a distributed flow unit includes a flow inlet configured to receive a fuel flow, a first manifold having flow lines to supply fuel to one or more primary nozzles, and a second manifold having flow lines to supply fuel to one or more secondary nozzles. In an embodiment, the second manifold is in fluid communication with the flow inlet. A metering valve has a first port in fluid communication with the flow inlet and with the second manifold. The metering valve is configured to supply a metered fuel flow to the first manifold. A flow passage is in fluid communication with, and runs between, a flow line of the first manifold and a flow line of the second manifold to allow for a continuous cooling flow in the second manifold when all of the one or more secondary nozzles are closed.

A split control unit in a distributed flow unit includes a flow inlet configured to receive a fuel flow, a first manifold having flow lines to supply fuel to one or more primary nozzles, and a second manifold having flow lines to supply fuel to one or more secondary nozzles. In an embodiment, the second manifold is in fluid communication with the flow inlet. A metering valve has a first port in fluid communication with the flow inlet and with the second manifold. The metering valve is configured to supply a metered fuel flow to the first manifold. A flow passage is in fluid communication with, and runs between, a flow line of the first manifold and a flow line of the second manifold to allow for a continuous cooling flow in the second manifold when all of the one or more secondary nozzles are closed.

The invention relates to a fuel system (1) for a turbine engine, adapted for injecting fuel in a combustion chamber (5) of the turbine engine, comprising: a pilot circuit (10), adapted for injecting fuel in the combustion chamber (5) by means of a pilot pipe (14), a main circuit (20), adapted for injecting fuel in the combustion chamber (5) by means of a main pipe (24),
the fuel system (1) being characterized in that it also comprises a thermal conductor (30) confined between the pilot pipe (14) and the main pipe (24) and configured to direct the thermal flow from the main pipe (24) to the pilot pipe (14).

To provide an axial piston motor, comprising at least one main burner, which has at least one main combustion space and at least one main nozzle space, and comprising at least one pre-burner, which has at least one pre-combustion space and at least one pre-nozzle space, wherein the pre-combustion space is connected to the main nozzle space by way of at least one hot gas feed, that has improved operating and control characteristics even under non-steady-state operating conditions, the pre-nozzle space of the pre-burner has at least one auxiliary hot gas feed.

To provide an axial piston motor, comprising at least one main burner, which has at least one main combustion space and at least one main nozzle space, and comprising at least one pre-burner, which has at least one pre-combustion space and at least one pre-nozzle space, wherein the pre-combustion space is connected to the main nozzle space by way of at least one hot gas feed, that has improved operating and control characteristics even under non-steady-state operating conditions, the pre-nozzle space of the pre-burner has at least one auxiliary hot gas feed.