Safran Aircraft Engines

Safran Electrical & Power

Safran Transmission Systems

Mathieu Jean Jacques Santin

Boris Pierre Marcel Morelli

Guillaume Julien Beck

Clément Dupays

Aldric Renaud Gabriel Marie Moreau De Lizoreux

Jean-Michel Bernard Paul Chastagnier

Thomas Turchi

Caroline Marie Frantz

Bellal Waissi

Nora El Ghannam

Gwenael Thierry Esteve

Geoffroy Marie Gérard Nicq

Benoit Gaillot-Drevon

Yvan Jean-Rene Battut

Benoît Gaillot-Drevon

Geoffroy Marie Gérard Nick

A device and a method for diagnosing an engine control unit of an aircraft, the device including an autonomous and mobile electronic diagnostic unit and connecting means for connecting the unit to an engine control unit of an aircraft, the connecting means advantageously including a single connection cable.

Diagnosis of an aircraft engine control unit

In order to fill a reservoir while avoiding laborious manual filling operations, there is added to the existing device, including a supply duct, a pump and a measuring probe, a stop valve designed to interrupt the filling as soon as the desired level has been reached, which is detected for example by an air intake which controls the closure of the valve. Two level indicators are added and make it possible to ascertain either that optimum filling has been achieved or that a malfunction is present in the system. Application to the systems for oil filling of aircraft engine reservoirs from another reservoir arranged within the aircraft, generally common to all the engines.

Device and method for filling an oil reservoir of an aircraft engine

An evaluation of the oil level of an aircraft engine tank from doses of oil delivered from another tank by a pump can be checked by comparing the evaluation of the volume provided by a sensor associated with the engine tank with an estimation of the volume extracted from the aircraft rank, either by another level sensor associated with this tank, or directly from the control of the pump. This comparison is made by a module capable of notifying staff of the need to check or maintain the device, and in particular to check if the sensor is operating correctly. Application to aeronautics, in particular to devices wherein a single aircraft tank supplies all the engine tanks.

Device for supplying an oil tank from a second tank

A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Aircraft propulsion assembly provided with a rotary transformer for supplying the blades with electrical energy

The invention concerns a propulsion device () comprising a torque generator () driving an output shaft () via a power gearbox (), the output shaft () being rotatably coupled to a thruster (), said power gearbox () being fixed on a frame () by means of suspension means (), said suspension means including hydraulic torque recovery means comprising at least a first hydraulic system () and a second hydraulic system () spaced from each other, each hydraulic system () having a pressure chamber whose volume varies according to the position of the housing () of the power gearbox () relative to the frame (), the pressure chambers of the hydraulic systems () being connected by a capillary so that a hydraulic fluid is able to flow from one pressure chamber to another via the capillary.

Propulsion device for an aircraft, such as a turboprop

In an aeroengine comprising a gas turbine engine driving a propeller via a reduction gearbox, the propeller comprising a plurality of blades, each provided with one or more electrical deicer elements and being set into rotation by a propeller-carrying shaft passing through the gearbox, the propeller-carrying shaft having a fastener flange for fastening to the propeller, provision is made, in order to deliver the electrical power needed for powering said electrical deicer elements, for the aeroengine to include a rotary three-phase transformer set into rotation by the propeller-carrying shaft and comprising firstly a rotor mounted inside the propeller-carrying shaft and angularly secured thereto, and secondly a stator secured to a stationary portion of the aeroengine, the rotary three-phase transformer being arranged behind the propeller fastener flange.

Turbine engine having a three-phase transformer for powering electrical deicer elements

Growing community of inventors

Moissy-Cramayel, France

Mathieu Jean Jacques Santin