Systems and methods for operating systems are provided. For example, a system comprises a coolant flowpath having a coolant flowing therethrough, a cooling system for cooling the coolant disposed along the coolant flowpath, a fuel flowpath having a fuel flowing therethrough, a heat exchanger fluidly connected to the coolant flowpath and the fuel flowpath for heat transfer between the coolant and the fuel to cool the fuel, and a fuel tank for accumulating the cooled fuel. The fuel is in thermal communication with a first thermal load to cool the load. An exemplary method comprises flowing a heat exchange fluid along a flowpath; flowing a fuel along a fuel flowpath including a fuel tank; passing both the heat exchange fluid and fuel through a heat exchanger to cool the fuel; and controlling the fuel flow from the heat exchanger to the fuel tank for accumulation of the cooled fuel.

A fuel supply system includes a low flow circuit that branches off parallel to the main flow circuit from the upstream main flow line upstream of the metering valve and has an upstream low flow line having a line connected to an orifice having an upstream side and a downstream side. The downstream side of the orifice is connected to a mass flow meter. A return low flow line is downstream of the mass flow meter and connected into the downstream main flow line at a downstream point. A controller is programmed to take in a low flow circuit mass flow measured by the mass flow meter, and calculate a main mass flow through the main flow circuit and the total mass flow delivered to the engine. A gas turbine engine and a method of operation are also disclosed.

A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit.

A fuel system for a gas turbine engine includes a secondary flow lockout valve. The secondary flow lockout valve includes a valve body having a first end that defines an inlet and a second end. The valve body includes at least one primary outlet bore and at least one secondary outlet bore. The valve body defines a channel in fluid communication with the primary outlet bore. The secondary flow lockout valve includes a cover that cooperates with the second end of the valve body to define a chamber. The chamber is in fluid communication with the channel such that the valve body is movable between at least a first position in which the primary outlet bore is open and a second position in which both the primary outlet bore and the secondary outlet bore are open based on a pressure in the chamber.

A fuel system for a gas turbine engine includes a secondary flow lockout valve. The secondary flow lockout valve includes a valve body having a first end that defines an inlet and a second end. The valve body includes at least one primary outlet bore and at least one secondary outlet bore. The valve body defines a channel in fluid communication with the primary outlet bore. The secondary flow lockout valve includes a cover that cooperates with the second end of the valve body to define a chamber. The chamber is in fluid communication with the channel such that the valve body is movable between at least a first position in which the primary outlet bore is open and a second position in which both the primary outlet bore and the secondary outlet bore are open based on a pressure in the chamber.

A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement.

A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement.

A system includes a generator using a fluid mixture obtained via a generator inlet, a compressor having a compressor inlet that is connected to a generator outlet by a first set of conduits, a second set of conduits connected to the compressor outlet and the generator inlet, and a sensor in communication with the second set of conduits, where a portion of the fluid mixture includes gas from a hydrocarbon well, and where exhaust fluid of the generator is provided to the compressor. A process includes obtaining a target fluid property and a fluid measurement using the sensor and modifying a parameter of a fluid control device to modify a first flow rate of the flow of the exhaust fluid through the second set of conduits relative to a second flow rate of the flow of the gas provided by the hydrocarbon well through the first set of conduits.

A fuel supply control device controls a fuel supply pump based on a front-rear differential pressure across a metering valve for a fuel supply amount, which is detected by a differential pressure gauge, using parallel flow passages of an orifice and a pressurizing valve as the metering valve, in which the fuel supply control device includes a first control amount generation unit generating a first control amount based on the front-rear differential pressure, a second control amount generation unit generating a second control amount based on the rotation speed of the fuel supply pump, a control amount selection unit, a subtractor, and a control calculation unit, in which the control amount selection unit selects the first control amount in a case where the rotation speed is equal to or lower than a predetermined threshold and select the second control amount in a case where the rotation speed exceeds the threshold.

A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionally different split ratios dependent on ascending or descending combustion fuel flow is provided. The system includes a passive fuel divider valve (FDV) that includes a primary piston and a secondary piston. The primary piston is moveable independently from the secondary piston during a portion of its stroke, and is hydro-locked to the secondary piston during another portion of its stroke. An ecology valve is also provided to purge the fuel from the primary and/or secondary manifolds during different modes of operation. A transfer valve is included to control the position of ecology piston of the ecology valve.