Safran Helicopter Engines

Safran Aircraft Engines

Turbomeca

Romain Thiriet

Camel Serghine

Patrick Marconi

Vincent Poumarede

Fabien Mercier-Calvairac

Caroline Seve

Pierre Darfeuil

Francois Danguy

Olivier Bedrine

Pierre Yvart

Hugues Filiputti

Stephen Langford

Jean-Michel Bazet

Laurent Fabbri

Jean-Luc Charles Gilbert Frealle

Bertrand Moine

Alphonse Puerto

Laurent Soulie

Antoine Marie Georges Caratge

Frederic Moulon

Fabien Mercier-calvairac

Antoine Drachsler

François Danguy

Philippe Barrat

Franck Garde

Christian Sarrat

François Porel

Guillaume Demezon

Eric Pierre Seinturier

Jérôme Irigoyen

Jean Michel Bazet

Jean-Michel Sannino

Pascal Guillemet

Nicolas Marucheau De Chanaud

Frédéric Moulon

Jean-Louis Besse

Jerome Irigoyen

Antoine Marie Caratge

Francois Porel

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (), characterised in that it comprises a pneumatic turbine () mechanically connected to said turbine engine () so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage () connected to said pneumatic turbine () by means of a pneumatic circuit () for supplying pressurised gas to said pneumatic turbine (); a controlled fast-opening pneumatic valve () arranged on the pneumatic circuit () between said storage () and said pneumatic turbine () and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (), or in a closed position in which said pneumatic turbine () is no longer supplied with pressurised gas.

Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter

The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step () of measuring the rotation speed of the helicopter rotor, a step () of calculating the drift of the measured rotation speed, a step () of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step () of activating the emergency device if the verified conditions are validated.

Method and system for controlling an emergency device

The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.

Helicopter equipped with a device for emergency lift assistance

The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine () being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.

Removable pack for reactivating a turboshaft engine, architecture for a multi-engine system for propelling a helicopter, provided with such a pack, and corresponding helicopter

A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.

Turbomachine designed to operate in turning gear mode

The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step () of receiving data () that are representative of the flight of the helicopter; a step () of selecting the turboshaft engine for which a change of mode would be most relevant; a step () of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step () of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.

Method for automatically controlling the operating speed of a helicopter turboshaft engine, corresponding control device and helicopter provided with such a device

Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurized liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurized liquid.

Hydraulic device for emergency starting a turbine engine, propulsion system of a multi-engine helicopter provided with one such device, and corresponding helicopter

The invention relates to a turboshaft engine comprising a gas generator () that is capable of being rotated, and a free turbine () that is rotated by the gases of said gas generator, characterized in that it comprises a device () for controlled mechanical coupling of said gas generator () and said free turbine () that is capable of connecting said gas generator () and said free turbine () mechanically and on demand as soon as the rotational speed of said gas generator () reaches a predetermined threshold speed.

Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter

The invention relates to a turboshaft engine comprising a gas generator () that is capable of being rotated, and a free turbine () that is rotated by the gases of said gas generator (), characterized in that it comprises a device () for spontaneously mechanically coupling said gas generator () and said free turbine () that is capable of mechanically and spontaneously connecting said gas generator () and said free turbine () as soon as the ratio of the rotational speed (NGG) of said gas generator to the rotational speed (NTL) of said free turbine reaches a predetermined threshold value.

Turboshaft engine, twin-engine helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a twin-engine helicopter

The invention relates to a method and to a device for optimized global management of a power network of an aircraft comprising a plurality of items of power equipment, characterized in that it comprises a modulefor selecting at least one optimization objective () from a plurality of predetermined objectives, a module () for receiving equipment data, a module () for receiving aircraft data, and a module () for determining operating setpoints () of the power equipment from equipment data () and aircraft data () which is suitable for achieving at least one selected optimization objective ().

Method of optimized global management of an energy network of an aircraft and corresponding device

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

Device and method for testing the integrity of a helicopter turbine engine rapid restart system

An emergency starter that allows responsiveness within a few seconds, without having disadvantages associated with mass and size of a back-up hydraulic or pneumatic starter. An instantaneous gas thrust of pyrotechnic type is coupled with a positive displacement transmission generator in conjunction with automatic coupling to/uncoupling from a set that is to be started. An emergency start-up system includes at least one pyrotechnic gas generator connected to an electrical initiator itself connected to a computer, a positive displacement motor housing straight-cut gears, the pyrotechnic gas generator being coupled to the motor by an inlet in the casing. The motor includes a mechanism of connection capable of moving at one end of the drive shaft configured to couple the transmission shaft to a driven shaft of the set that is to be started via a centrifugal clutch.

Method and system for the emergency start-up of an energy generator set

An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.

System and method for emergency starting of an aircraft turbomachine

Growing community of inventors

Jurancon, France

Romain Thiriet