Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.

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 fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

Reduction of operation efficiency of a GTCS at a time of changing an operation using bypass stack to an operation using HRSG is suppressed. An HRSG of the GTCS is provided with an air supply piping and a ventilation piping connected to a fuel line of a duct burner at a position upstream of a main shut-off valve and downstream of a fuel shut-off valve, an air supply shut-off valve that opens/closes the air supply piping, and a ventilation shut-off valve that opens/closes the ventilation piping, and is configured such that during an operation using a bypass stack, an inlet of the HRSG is closed to open a bypass stack, a main shut-off valve and the fuel shut-off valve are closed, and the air supply shut-off valve and the ventilation shut-off valve are always opened, and at a time of changing to an operation using HRSG, the inlet of the HRSG is opened to close the bypass stack without shutting down a GT, the main shut-off valve and the fuel shut-off valve are opened, and the air supply shut-off valve and the ventilation shut-off valve are closed.

A valve member cooling arrangement for a valve having at least one housing with sets of working fluid inlet/outlet ports and coolant supply/return ports. A valve member movably disposed within a valve chamber has a valve head configured to control flow between the working fluid ports. The valve member has valve member inlet/outlet openings and defines an internal valve member cooling passage uniting the valve openings. At least one coolant sleeve is disposed about the valve member. The coolant sleeve(s) have inflow and outflow ports separated inflow from outflow by at least one seal. During static and dynamic positioning of the valve member, the valve member inlet(s) are in communication with inflow port(s) of the coolant sleeve, and the valve member outlet(s) are in communication with outflow port(s) of the coolant sleeve(s).

A gas turbine with a burner, which gas turbine has at least one fuel feed line and at least one fuel outflow line, wherein a flushing water line is connected fluidically to the fuel feed line, and wherein a leakage oil tank is connected fluidically via a drainage line to the fuel outflow line and the connection of the fuel outflow line and the drainage line is provided at a point downstream of at least one closure valve in the fuel outflow line, wherein a bypass line is connected fluidically to the fuel outflow line upstream of the closure valve, which bypass line connects the fuel outflow line fluidically to the leakage oil tank.

A fuel injector assembly for a combustor including an axially staged fuel injector includes an injector body having an inner wall and a boss that is rigidly connected to the injector body the boss includes an inner wall. The inner wall of the boss and the inner wall of the injector body together define a flow passage of the fuel injector assembly. The injector body defines an inlet to the flow passage and the boss defines an outlet of the flow passage.

A mobile heating device, comprising a heater assembly including a fuel chamber, and a fuel supply line for supplying liquid fuel to the heater assembly, where the heater assembly further includes an evaporator receiving arrangement for evaporating liquid fuel, said arrangement comprising an evaporator receiving body for receiving an evaporator element for distributing and evaporating liquid fuel, where the fuel supply line comprises a supply pipe with an inlet for inputting fuel and an outlet for outputting fuel to the combustion chamber, where the fuel supply line further includes an emptying device for partly or completely emptying the fuel supply line through the outlet.

Embodiments of the present disclosure are directed toward a system and method to drain a fuel manifold wherein a fuel drainage and purge system includes a fuel manifold and a drainage line extending from the fuel manifold. The drainage line is configured to flow a liquid-gas mixture from the fuel manifold. The fuel drainage and purge system also includes a drain valve disposed along the drainage line, a vent line extending from the drainage line upstream of the drain valve, a vent valve disposed along the vent line, and a drainage trap arranged along the drainage line downstream of the drain valve. The drainage trap is configured to separate the liquid-gas mixture into a liquid stream and a gaseous stream.

Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.