A multi-point fuel injection device for an aircraft engine, including an inlet line, at least two injection lines, and a purge line, a fuel distributor member connected to each line and including a moveable element which includes an injection passage, in which the moveable element additionally includes a purge passage, and is configured to adopt a first range of positions in which the injection passage interconnects the inlet line and the injection lines, and a second range of positions in which the injection passage interconnects the inlet line and at least a first injection line while the purge passage interconnects the purge line and at least a second injection line, the device additionally includes an actuator adapted to move the moveable element into a safety position when a failure of the distribution member is detected, the injection passage interconnecting, in this safety position of the moveable element, the inlet line and the first injection line while the purge passage does not interconnect the purge line to any of the injection lines.

A combustion staging system includes a splitting unit which receives a metered fuel flow and controllably splits the received fuel flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel from the splitting unit to the pilot and mains stages. The splitting unit selects and deselects pilot-only operation. Both pilot and mains manifolds are selectable for pilot and mains operation. A cooling flow recirculation line has a delivery section arranged to provide a cooling flow of fuel to the mains manifold when it is deselected during pilot-only operation. Cooling flow enters the delivery section from a high pressure fuel zone of the engine and exits the return section to a low pressure fuel zone of the engine. A controller adjusts the splitting unit during pilot-only operation to partially select the mains manifold thereby increasing the pressure in the mains manifold to meet a target fuel pressure therein.

A combustion staging system includes a splitting unit which receives a metered fuel flow and controllably splits the received fuel flow into pilot and mains flows. Pilot and mains fuel manifolds distribute fuel from the splitting unit to the pilot and mains stages. The splitting unit selects and deselects pilot-only operation. Both pilot and mains manifolds are selectable for pilot and mains operation. A cooling flow recirculation line has a delivery section arranged to provide a cooling flow of fuel to the mains manifold when it is deselected during pilot-only operation. Cooling flow enters the delivery section from a high pressure fuel zone of the engine and exits the return section to a low pressure fuel zone of the engine. A controller adjusts the splitting unit during pilot-only operation to partially select the mains manifold thereby increasing the pressure in the mains manifold to meet a target fuel pressure therein.

A combustion staging system has a splitting unit receiving and splitting metered fuel flow into out-going pilot and mains flows; pilot and mains fuel manifolds receiving the pilot and mains flows; and parallel mains flow scheduling valves distributing the mains flow. The mains flow scheduling valves pass the pilot fuel flow to injector pilot discharge orifices. Each mains flow scheduling valve has a chamber containing a piston, the chamber to a piston pilot side communicating with the pilot fuel manifold and the chamber to a mains side of the piston communicating with the mains fuel manifold. The piston is biased towards a closed pilot-only position preventing flow out of the chamber mains side to the injector mains discharge orifice. The piston is movable under increased pressure in the mains fuel manifold to an open pilot-and-mains position allowing flow out of the chamber mains side to the injector mains discharge orifice.

A combustion staging system has a splitting unit receiving and splitting metered fuel flow into out-going pilot and mains flows; pilot and mains fuel manifolds receiving the pilot and mains flows; and parallel mains flow scheduling valves distributing the mains flow. The mains flow scheduling valves pass the pilot fuel flow to injector pilot discharge orifices. Each mains flow scheduling valve has a chamber containing a piston, the chamber to a piston pilot side communicating with the pilot fuel manifold and the chamber to a mains side of the piston communicating with the mains fuel manifold. The piston is biased towards a closed pilot-only position preventing flow out of the chamber mains side to the injector mains discharge orifice. The piston is movable under increased pressure in the mains fuel manifold to an open pilot-and-mains position allowing flow out of the chamber mains side to the injector mains discharge orifice.

A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance.

A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance.

Various embodiments include gas turbomachine (GT) fuel systems, related control systems and GTs. In some cases, the GT fuel system includes: a plurality of combustion chambers circumferentially disposed around a gas turbine; a set of fuel nozzles directly mounted to each of the plurality of combustion chambers; a set of conduits coupled with each of the set of fuel nozzles at a first end of each of the conduits; and a set of liquid fuel check valves coupled with a second end of each of the set of conduits, the set of liquid fuel check valves being positioned radially offset and axially offset from the set of fuel nozzles.

The present invention relates to dual fuel delivery system for a gas turbine. A dual fuel delivery system for a gas turbine includes: a main fuel line having a main fuel oil conduit and a main fuel gas conduit, wherein the main fuel gas conduit encloses, at least partially, the main fuel oil conduit; and a fuel ring connected to the main fuel line, the fuel ring having a fuel gas ring connected to the main fuel gas conduit and a fuel oil ring connected to the main fuel oil conduit, wherein the fuel gas ring encloses, at least partially, the fuel oil ring.

A combustion staging system is provided for fuel injectors of a multi-stage combustor of a gas turbine engine. The system has a splitting unit which receives a metered total fuel flow and controllably splits the metered total fuel flow into out-going pilot and mains fuel flows to perform pilot-only and pilot-and-mains staging control of the combustor. The system further has pilot and mains fuel manifolds which respectively receive the pilot and mains fuel flows. The system further has a plurality of mains flow scheduling valves which distribute the mains fuel flow from the mains fuel manifold to mains discharge orifices of respective injectors of the combustor. The system further has servo line which extends to the mains flow scheduling valves, the servo line being controllably fillable with pressurised fuel to change the pressure in the servo line relative to the pressure in the mains fuel manifold. Each mains flow scheduling valve has a chamber containing a movable piston, the chamber to a mains side of the piston being fed by the mains fuel manifold, and the chamber to a servo side of the piston being fed by the servo line. The piston has an open pilot-and-mains position which allows flow out of the mains side of the chamber to the mains discharge orifice of the respective injector. The piston is biased towards a closed pilot-only position which prevents flow out of the mains side of the chamber to the mains discharge orifice of the respective injector. The piston is movable to the closed position under an increase in pressure in the servo line relative to the mains fuel manifold.