Abstract: A device for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbo machine, in particular of an aircraft, the device including a rotating main body extending about a longitudinal axis, the main body including an internal flow duct for a first flow of fuel, extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second flow of fuel, and including at least one orifice for the second flow of fuel to pass through, and an external annular groove in fluidic communication with the at least one orifice in the first portion.

Abstract: A fuel supply circuit including a supply duct in which a first flow (Fl) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (Fl), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.

Abstract: A fuel supply circuit including a supply duct in which a first flow (F1) is able to circulate, at least one supply pump for circulating the fuel from a tank to a metering unit, and a recirculation duct for a second flow upstream of the pump, wherein the ducts (20, 60) discharge in different directions upstream of the pump; the circuit includes a dispensing device including an internal flow duct for the first flow (F1), an external flow channel for the second flow and at least one passage orifice for the second flow, which communicates fluidically with the channel; and the at least one orifice (810) and the duct are coaxial and respectively discharge upstream of the pump.

Abstract: A device for distributing at least one fuel flow for a circuit for supplying fuel to a combustion chamber of a turbo machine, in particular of an aircraft, the device including a rotating main body extending about a longitudinal axis, the main body including an internal flow duct for a first flow of fuel, extending through the main body along the axis, a first annular portion configured to form an outlet passage for a second flow of fuel, and including at least one orifice for the second flow of fuel to pass through, and an external annular groove in fluidic communication with the at least one orifice in the first portion.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.

Abstract: A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system including first and second positive displacement pumps, a hydraulic actuator, and a fuel metering unit. As a function of a position of a slide of the actuator, a feed orifice of the actuator may be connected to a high-pressure delivery orifice connected to an outlet of the second pump, or to a low-pressure delivery orifice connected to a low-pressure feed line. The fuel metering unit includes through sections, one of these through sections being connected to an outlet of the high-pressure pumping system and the other through section being connected to an outlet of the high-pressure pumping system and leading to a high-pressure pilot chamber of the hydraulic actuator.

Abstract: The invention relates to a piston having a first face, a second face opposite to the first face, a third face connecting said first and second faces together and presenting a groove, and a sealing gasket housed in said groove. The piston includes a duct constituted by a first segment situated inside the piston and connecting said first face to said groove, by a second segment situated inside the piston and connecting said second face to said groove, and by an intermediate segment connecting together said first and second segments and crossing said groove, the walls of said intermediate segment being formed by the walls of said groove and by said sealing gasket in such a manner that said intermediate segment forms a leaktight tube that opens out solely via the first segment and via the second segment, said intermediate segment presenting at least one obstacle suitable for impeding the flow of fluid that flows along said intermediate segment.

Abstract: A fuel-injection device in a turbomachine, comprising a high-pressure pump (10) supplying a flow control valve (16), whose outlet is connected via a pressurization and cut-off valve (20) to a fuel-injector (18) feed pipe (22), the valve (20) being connected to the inlet and to the outlet of the pump (10) in order to define two fuel pressurization thresholds, one being used to start-up and restart the turbomachine, and the other being used for operating the turbomachine as from an idle speed and for commanding an equipment with variable geometry (24).