Safran Aircraft Engines

Snecma

Labinal Power Systems

Safran Electrical & Power

Marc Missout

Nicolas Claude Parmentier

Alain Pierre Garassino

Julien Alexis Louis Ricordeau

Mathieu Jean Pierre Trohel

Olivier Robert Michel Delepierre-Massue

Jean-Jacques Charrier

Moez Bensaied

Francis Pottier

Stephane Ribeiro

Romain Tabart

Moëz Bensaied

Stéphane Ribeiro

An aerodynamic arm for an aircraft turbine engine casing includes a tubular outer shell having a generally elongate shape extending substantially along an axis. The shell has axial ends configured to be connected to a turbine engine casing. An electrically conductive core extends inside the shell and has ends configured to electrically connect to the ends of the shell. An insulating material occupies a space between the core and the shell.

Aerodynamic arm for an aircraft turbine engine casing

An aircraft turboprop engine has at least one low-pressure body and one high-pressure body. The low-pressure body drives a thrust propeller using a gearbox. The turboprop engine further includes a means for supplying air to an air-conditioning circuit of an aircraft cabin. The supply means includes a load compressor and a rotor that is coupled to the low-pressure body by the gearbox. The supply means further includes a means for controlling the rotation speed of the rotor of the compressor, which means comprise an electric motor, and a mechanical differential for coupling a first output shaft of said electric motor to a second output shaft of said gearbox and to said compressor rotor, such that the rotation speed of said rotor depends on the respective rotation speeds of said first and second output shafts.

Supply of air to an air-conditioning circuit of an aircraft cabin

A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.

Cooling of an oil circuit of a turbomachine

A front-fan turbojet engine including at least one fluid circuit and an air/fluid heat exchanger by which the fluid is cooled by air external to the turbojet engine and a splitter for splitting a flow downstream of the fan between a primary flow and a secondary flow. The heat exchanger is associated with a thermoelectric generator including a first and a second thermal exchange surface, of which the first surface is in thermal contact with the airflow and the second surface is in thermal contact with the fluid to be cooled in the exchanger.

Turbine engine incorporating thermoelectric generators

Growing community of inventors

Montigny le Bretonneux, France

Marc Missout