Provided is a gas turbine combustor that can achieve improvement of the combustion stability. A gas turbine combustor includes a pilot burner of the diffusion combustion type, a pilot flow control valve that regulates a flow rate of fuel to be supplied to the pilot burner, a main burner of the premix combustion type arranged on an outer circumference side of the pilot burner, main flow control valves that regulate flow rates of fuel to be individually supplied to burner sectors into which the main burner is sectioned in a circumferential direction, and a controller configured to control the pilot flow control valve and the main flow control valves. The controller controls the main flow control valves such that, when fuel is to be supplied to all the burner sectors, a difference in fuel flow rate occurs between at least one burner sector and the other burner sectors among the burner sectors.

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 a combustor by supplying fuel to a first fuel manifolds and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and using a pump to drive gas into the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

Method of adjusting the pressure balance or a control device, in particular of a servo valve, the requisite adjusting movement being applied by a disc translator.

Method of adjusting the pressure balance or a control device, in particular of a servo valve, the requisite adjusting movement being applied by a disc translator.

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA) is disclosed. An example fuel supply system includes a fuel supply line to supply fuel to a combustion engine, a fuel metering valve coupled to the fuel supply line, the fuel metering valve to control a flow of fuel through the fuel supply line to the combustion engine, a throttle valve coupled to the fuel supply line downstream of the fuel metering valve, the throttle valve to bleed off fuel supplied to the combustion engine based on a pressure difference across the fuel metering valve, and a controllable servo coupled to the throttle valve, the controllable servo to control the throttle valve based on a sensor output indicative of the pressure difference.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member A control method is further included.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.

Disclosed is a system including a turbine having a plurality of blades being spaced circumferentially around a shaft. A plurality of dispensers is included. Each dispenser of the plurality of dispensers is positioned facing the open surface of the plurality of blades and directs discharged fluid toward the open surface of the plurality of blades to drive the turbine. A housing encloses the plurality of blades and a portion of each dispenser. A plurality of exhaust pipes is coupled to the housing and extends away from the shaft directing the discharged fluid out of the housing. Each exhaust pipe corresponds to a respective dispenser of the plurality of dispensers. A controller is in communication with the plurality of dispensers and is configured to control the plurality of dispensers.

A gear pump includes gears received within a housing defining an inlet, an outlet and end plates. The gears have shaft portions on each of two sides of each of the two gears. The shaft portions are mounted in journal bearings. The journal bearings each have a gear side face adjacent one of the two gears. A remote face is on a remote side of the journal bearing remote from each of the two gears. There is a plurality of heat pipes in at least one of the journal bearings. The heat pipes move heat from the gear face of the at least one of the journal bearings to the remote face. The plurality of heat pipes is enclosed by the housing, and extend generally in an axial direction from an end adjacent the gear face to an end adjacent the remote face. A fuel supply system is also disclosed.