A system includes a recirculation conduit that recirculates working fluid and a permanent magnet generator module in communication with the recirculation conduit. The working fluid from the recirculation conduit drives the permanent magnet generator module.

A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.

A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.

A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.

The present disclosure provides a fuel metering system for a gas turbine engine, the fuel metering system comprising: a fuel supply line; a fuel metering valve configured to pass an amount of fuel received from the fuel supply line to the gas turbine engine; an engine control unit configured to control the position of the fuel metering valve according to a demanded fuel flow to the gas turbine engine; a flow sensor configured to provide a measurement of a flow of fuel in the fuel metering system; wherein the engine control unit is further configured to determine a fuel flow to the gas turbine engine based upon the measurement from the flow sensor; and wherein the engine control unit is further configured to identify a loss of fuel flow control by comparing the demanded fuel flow to the determined fuel flow to the gas turbine engine.

A gas supply system includes a first tank, a first path into which a first gas generated by vaporization of a first low-temperature liquefied gas flows, a gas boosting mechanism being disposed in the first path, a second path that is a path configured to extract the first low-temperature liquefied gas from the first tank, a pump and a vaporization mechanism being disposed in the second path and a reliquefaction path that is a path configured to liquefy at least part of the first gas extracted from an upstream side of the gas boosting mechanism in the first path and to cause the liquefied first gas to flow into an upstream side of the pump in the second path, a cooling heat exchanger configured to cool the first gas by a second low-temperature liquefied gas or a second gas being disposed in the reliquefaction path.

A gas supply system includes a first tank, a first path into which a first gas generated by vaporization of a first low-temperature liquefied gas flows, a gas boosting mechanism being disposed in the first path, a second path that is a path configured to extract the first low-temperature liquefied gas from the first tank, a pump and a vaporization mechanism being disposed in the second path and a reliquefaction path that is a path configured to liquefy at least part of the first gas extracted from an upstream side of the gas boosting mechanism in the first path and to cause the liquefied first gas to flow into an upstream side of the pump in the second path, a cooling heat exchanger configured to cool the first gas by a second low-temperature liquefied gas or a second gas being disposed in the reliquefaction path.

Fuel systems of gas turbine engines of aircraft, and associated methods are provided. The fuel systems and methods can permit reverse purging of one or more fuel manifolds of a gas turbine engine to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds fluidly connectable to a combustor of the gas turbine engine. A valve is operatively disposed between the second fuel manifold and a fuel supply line for controlling fuel supply to the second fuel manifold. A reservoir includes a movable piston disposed therein and dividing the reservoir into a first chamber and a second chamber. The first chamber is fluidly connectable to the fuel supply line or to a fuel purge line via the valve. The second chamber is in fluid communication with the second fuel manifold to receive residual fuel from the second fuel manifold.

A circuit for metering fuel for a turbomachine, including a fuel metering element, a pump designed to pump a flow of fuel to the metering element, and a control valve designed to return, toward the pump, an excess flow of fuel delivered to the metering element as a function of a fuel pressure difference at the terminals of the metering element, the control valve is designed to modulate the excess flow returned toward the pump as a function of variations in the density of the fuel delivered to the metering element. A turbomachine can include such a circuit.

A circuit for metering fuel for a turbomachine, including a fuel metering element, a pump designed to pump a flow of fuel to the metering element, and a control valve designed to return, toward the pump, an excess flow of fuel delivered to the metering element as a function of a fuel pressure difference at the terminals of the metering element, the control valve is designed to modulate the excess flow returned toward the pump as a function of variations in the density of the fuel delivered to the metering element. A turbomachine can include such a circuit.