Safran Helicopter Engines

Turbomeca

Safran Power Units

Safran Aircraft Engines

Microturbo

Patrick Marconi

Romain Thiriet

Camel Serghine

Olivier Bedrine

Pierre Darfeuil

Caroline Seve

Francois Danguy

Pierre Yvart

Jean-Francois Rideau

Jean-Michel Bazet

Stephen Langford

Laurent Fabbri

Hubert Hippolyte Vignau

Pierre Biscay

Alphonse Puerto

Denis Antoine Julien Real

Laurent Soulie

Pascal Dauriac

Antoine Marie Georges Caratge

Fabien Mercier-calvairac

François Danguy

Jean-François Rideau

Denis Real

Philippe Barrat

Guillaume Demezon

Jérôme Irigoyen

Jean-Louis Besse

Nicolas Marucheau De Chanaud

Fabien Mercier Calvairac

Pascal Guillemet

Jean-Michel Sannino

Antoine Marie Caratge

Jerome Irigoyen

A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.

Turbogenerator with simplified control system for aircraft

A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.

Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

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

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

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

A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines.

Method and architecture for the optimized transfer of power between an auxiliary power motor and the main engines of a helicopter

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

A method and architecture for recombining power of a turbomachine improving on problems of size, mass, or reliability. In the method energy is recovered in an exhaust nozzle and converted and recirculated using a mechanical and/or electrical power recombining mechanism. An example of an architecture of a turbomachine includes a main turbine engine and a heat exchanger positioned in the exhaust nozzle and coupled, via pipes, to an independent system that converts thermal energy into mechanical energy. This independent system is connected to a localized mechanical recombination mechanism via a power shaft to supply power to a power transmission shaft according to aircraft requirements.

Method and architecture for recombining the power of a turbomachine

A fuel cell () has a compressed air inlet fed by a compressor () and a fuel inlet, and it produces direct current electricity. A turbine () receives a flow of gas under pressure from the fuel cell and is mechanically coupled to the first compressor in order to drive it. A second compressor () of a circuit for use in flight to feed pressurized air to the aircraft cabin () is mechanically coupled to a shaft of the turbine. An electric machine () may be coupled to the same turbine shaft as drives the compressor (), the electric machine being capable of operating as a generator or as an electric motor.

Power generation system for an aircraft using a fuel cell

Growing community of inventors

Gelos, France

Patrick Marconi