Safran Helicopter Engines

Safran Landing Systems

Antoine Pascal Moutaux

Thomas Klonowski

Romain Jean Gilbert Thiriet

Benjamin Fulleringer

Jean-Julien Camille Vonfelt

Olivier Bedrine

Florent Nierlich

Olivier Lafargue

Bertrand Nogarede

David Bernard Martin Lemay

Jean-Michel Presse

Alexis Thomas Valentin Longin

Pierre Anthony Sicaire

Olivier Audrey David Lafargue

Rafaël Samson

Philippe Jean Rene Marie Benezech

Olivier Robert

A propulsive assembly including a first and a second gas turbine each having a gas generator and a free power turbine, a main rotor coupled to the free power turbine of a first and a second main coupling, a first and a second reversible electric machine each coupled to the gas generator, by way of a first deactivatable coupling, and each coupled to the main rotor by way of a second deactivatable coupling, the first deactivatable coupling being activated when the electric machines are rotating in a first direction of rotation, and the second deactivatable coupling being activated when the electric machines are rotating in a second direction of rotation opposite to the first direction of rotation.

Propulsive assembly for a multi-engine hybrid aircraft

A system for pumping and metering a fluid for a turbine engine, which system includes at least one pump for the fluid and an electronic computer configured to determine the flow rate of the fluid to be delivered to the turbine engine, the pumping and metering system being wherein it further includes a first electric motor and a second electric motor, which are each configured to drive the at least one pump, and in that the electronic computer includes a first control loop for controlling at least the first electric motor and a second control loop for controlling at least the second electric motor.

System for pumping and metering a fluid for a turbine engine and method for controlling such a system

A device for a hybrid aircraft including a turboshaft engine having a gas generator, a free turbine, and a main rotor. The device includes a first reversible electric machine coupled to a shaft of the free turbine by way of a first free wheel, and to the main rotor. The device further includes a second reversible electric machine coupled to a shaft of the gas generator by way of a second free wheel, and coupled to the main rotor by way of a third free wheel. The second free wheel activates when the second electric machine rotates in a first direction of rotation, and the third free wheel activates when the second electric machine rotates in a second direction of rotation opposite to the first direction of rotation.

Transmission device for hybrid aircraft

A propulsion system () for a helicopter, comprising a turboshaft engine () with a linked turbine and an electric machine () capable of operating as an electric motor, the turboshaft engine () and the electric machine () being capable of driving in rotation at least one main rotor () intended to be coupled to a rotating wing () characterised in that it comprises means of coupling and decoupling () in rotation between a rotor () of the electric machine () and a rotor () of the turboshaft engine (), the means of coupling and decoupling () being capable of allowing the rotor () of the turboshaft engine () to be driven in rotation with the aid of the electric machine (), in a first state of the propulsion system (), and capable of allowing the rotor () of the turboshaft engine () and the rotor () of the electric machine () to be decoupled in rotation, in a second state of the propulsion system ().

Propulsion system for a helicopter

The invention relates to an aircraft propulsion system, comprising a main transmission unit () and at least two turbojet engines connected to the main transmission unit (), respectively a first turbojet engine () and a second turbojet engine (), each turbojet engine comprising a free turbine (), characterized in that the first turbojet engine () comprises a heat exchanger () configured to recover some of the thermal energy from the exhaust gas at the outlet of the free turbine, and in that the propulsion system comprises at least one computer () configured to control the two turbojet engines and to limit the acceleration and the deceleration of the first turbojet engine () when neither of the turbojet engines is broken down, in order to limit the reactor power transients at the heat exchanger ().

Asymmetric propulsion system with heat recovery

The invention relates to a temperature measurement device comprising at least three probes, a computer, the computer being configured to estimate a temperature on the basis of voltage measurements at the output of the probes, characterised in that the probes are connected together in a plurality of meshes mounted in series, with at least one mesh comprising at least two probes mounted in parallel and at least one other mesh comprising a probe or a plurality of probes mounted in parallel.

Thermometric measurement by meshing of probes, particularly in turbine engines

The electrical machine according to the invention is a dual machine, and comprises a first machine which can be reversed and a second machine functioning through induction between two windings. The second machine can be used for de-icing a propeller, the induction-receiving winding being mounted on the propeller shaft. The first electrical machine can function as an electrical engine to 'taxi' the aircraft. In certain embodiments, the winding mounted on the stator is common to the two machines and different magnetic flows are utilised to control them. A separate functioning of the two machines and a very good integration into the aircraft engine, with space-saving and low mass, are possible.

Aircraft turboprop engine provided with an electric machine

An electric actuator for inlet guide vanes of a gas turbine engine, the electric actuator including a fixed portion secured to a stationary portion of the engine and a movable portion that is mechanically connected to the inlet guide vanes, stationary electromagnets distributed at regular intervals around the periphery of the movable portion and fastened to the fixed portion, and movable electromagnets arranged between the stationary electromagnets, each movable electromagnet being secured on either side to first and second piezoelectric elements, the movable electromagnets and the first and second piezoelectric elements having a degree of freedom of movement relative to the movable portion and having inside faces forming a common line of contact that is tangential to the movable portion.

Device for controlling inlet guide vanes by means of a multilayer piezoelectric actuator

A device for controlling a propeller, having variable-pitch blades, of a turboprop engine, has a first hydromechanical device for controlling the pitch of the blades of the propeller and a second hydromechanical device for controlling the speed of rotation of the propeller. The device includes a single electromechanical actuator with a movable actuator member mechanically connected both to the first hydromechanical device for controlling the pitch, in order to manage the pitch setpoint, and to the second hydromechanical device for controlling the speed, in order to manage the speed setpoint.

Device for controlling a propeller, having variable-pitch blades, of a turboprop engine

An actuating system for an aircraft having an electromechanical actuator () comprising a non-volatile memory () wherein stored data () including configuration data () specific to the electromechanical actuator is stored. The system also includes a control unit () using the configuration data to implement a servo-control loop, the output signal of which is a digital signal controlling the electric motor of the electromechanical actuator and at least one digital transmission channel () connecting the control unit and the electromechanical actuator.

Growing community of inventors

Moissy-Cramayel, France

Antoine Pascal Moutaux