Safran Helicopter Engines

Turbomeca

Philippe Jean René Marie Benezech

Lorenzo Huacan Hernandez

Bertrand Moine

Jean-Luc Charles Gilbert Frealle

Cedric Roger Zordan

Eric Royer

Jean-Michel Pierre Claude Py

Eric Le Borgne

Matthieu Julien Gallot

Pierre Anthony Sicaire

Lionel Napias

Alexis Thomas Valentin Longin

Pascal Rizzo

Pascal Rupert

Bruno Facca

Maxime Quaireau

Ludovic Alexandre Leglise

Philippe Roger

Luc Jacques Pierre Reberga

Cédric Zordan

Gabriel Darrieumerlou

Sébastien Combebias

Sébastien Fouche

Jean Lindeman

Cédric Roger Zordan

A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.

Fuel supply system with air expulsion drain for an aircraft engine

The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members () of a turbomachine (), the members () being configured to travel over an operating area comprising a first position Pand a second position P, the method comprising the steps of: —(E) determining a first pivoting speed Vfrom the first position Pto the second position P; —(E) determining a second pivoting speed from the second position Pto the first position P; and—(E) determining an anomaly in the operation of the system for positioning the members () if the first speed Vis lower than a first determined speed threshold and/or if the second speed Vis lower than a second determined speed threshold.

Method for monitoring the operating state of a system for positioning variable-geometry members of a turbomachine

Device for draining liquids for an aircraft engine, comprising a collector designed to collect liquids drained from the engine, said device comprising means for pumping the liquids held in the collector and for discharging said liquids, and monitoring means designed to indicate when the liquids have been collected by the collector in an anomalous manner, said monitoring means being designed to be activated when the flow rate of collected liquids is greater than the delivery of the pumping means.

Device for draining liquids for an aircraft engine

A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.

Turbomachine comprising a privileged injection device and corresponding injection method

A turbine engine for an aircraft including a turbine engine shaft and a pumping module, including: a pump shaft, connected to the turbine engine shaft; a pump for supplying fuel to the turbine engine, mounted on the pump shaft, configured to deliver a flow of fuel as a function of a speed of rotation of the turbine engine shaft; and an electrical device mounted on the pump shaft and configured, according to a first mode of operation, to drive the pump shaft in rotation to actuate the supply pump and, according to a second mode of operation, to be driven in rotation by the pump shaft to supply electrical power to equipment of the turbine engine.

Turbine engine comprising an electrically activated fuel supply pump, and turbine engine fuel supply method

A fuel flowmeter for being fed by a pump including an inlet and an outlet, including: a metering valve including an inlet and an outlet, and arranged downstream from the outlet of the pump; a return circuit connecting the inlet of the metering valve to the inlet of the pump; and a pressure regulator device including: a movable valve member to close and open the return circuit, a pressure difference detection surface fastened to the valve member and axially separating a first chamber in communication with the inlet of the metering valve from a second chamber in communication with the outlet from the metering valve, a piston axially separating the second chamber from a third chamber connected to the outlet of the metering valve, and a channel putting the second chamber in communication with the third chamber.

Fuel flowmeter having an improved regulator device

Growing community of inventors

Morlaas, France

Philippe Jean René Marie Benezech