Abstract: 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.

Abstract: 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.

Abstract: The invention relates to a propulsion system intended to be mounted on an aircraft comprising a main body, said propulsion system comprising:—a first rotating propulsive member and a second rotating propulsive member that are intended to be mounted on either side of said main body,—a transmission housing connected to the first rotating propulsive member via a first mechanical shaft and to the second rotating propulsive member via a second mechanical shaft,—a single gas generator connected to said transmission housing and configured to rotate the first rotating propulsive member and the second rotating propulsive member, and—a single auxiliary turbomachine configured to rotate the first rotating propulsive member and the second rotating propulsive member independently of the gas generator.

Abstract: 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.

Abstract: 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.

Abstract: Aircraft turboprop engine (110), comprising at least one low-pressure body (12) and one high-pressure body (14), the low-pressure body driving a thrust propeller by means of a gearbox (16), the turboprop engine further comprising means for supplying air to an air-conditioning circuit (36) of an aircraft cabin, said supply means comprising a load compressor (60), a rotor (61) of which is coupled to said low-pressure body by means of said gearbox, characterised in that said supply means further comprise means for controlling the rotation speed of the rotor (61) of said compressor (60), which means comprise an electric motor (70), and a mechanical differential (72) for coupling a first output shaft (74) of said electric motor to a second output shaft (76) of said gearbox and to said compressor rotor (61), such that the rotation speed (V3) of said rotor depends on the respective rotation speeds (V1, V2) of said first and second output shafts.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A line replaceable unit for aircraft, the line replaceable unit including: a measuring device configured to measure useful data to define the status of the line replaceable unit, a predictive monitoring device configured to calculate indicators of potential breakdown of the line replaceable unit from useful data to define the status of the line replaceable unit, a communication interlace capable of forwarding indicators of potential breakdown to a central unit.