Snecma

Hispano Suiza

Safran Electronics & Defense

Laurent Gilbert Yves Hodinot

Nicolas Alain Bader

Nicolas Potel

Regis Michel Paul Deldalle

Frédéric Brettes

Pascal Marly

Bertrand Lacombe

Bastien Dore

Marc Raes

Celine Marie Anne Issert

Jean Charles Cappellari

Sandrine Huet

Olivier Marie Henriot

Pascal Laurent Marly

Céline Marie Anne Issert

A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.

Fuel feed circuit for an aeroengine having a high pressure pump system with two pumps

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.

Fuel feed circuit with hydraulic actuator and fuel metering unit for an aeroengine

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

Method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

A fuel-injection device in a turbomachine is disclosed. The device includes a high-pressure pump supplying a flow control valve, whose outlet is connected via a pressurization and cut-off valve to a fuel-injector feed pipe. The valve is connected to the inlet and to the outlet of the pump in order to define two fuel pressurization thresholds, one of which is used to start-up and restart the turbomachine and the other is used for operating the turbomachine from an idle speed and for commanding an equipment with variable geometry.

Fuel-injection device in a turbomachine

This invention relates to a control installation () of a turbo-machine, comprising: The installation is such that the antenna () is mounted on the unit ().

Turbo-machine control installation equipped with a passive radiofrequency identification chip unit verification system

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Cesson, France

Laurent Gilbert Yves Hodinot