Abstract: An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the means for supplying air has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

Abstract: An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Abstract: An aircraft turboprop engine (310) including at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body. At least one of the bodies includes a compressor. The low-pressure body drives a first gearbox (16) The turboprop engine also includes at least one load compressor (60) for supplying air to an air-conditioning circuit of an aircraft cabin. A rotor (61) of the load compressor is coupled to the low-pressure body. The load compressor (60) includes an air inlet (62) connected to a conduit (72) to bleed air from the compressor of the turboprop engine when all of the aforementioned bodies include only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies include at least two compressors.

Abstract: 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.

Abstract: A method for managing an electrical power supply system (1) of an aircraft, the power supply system (1) comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS1, MPS2), a plurality of contactors (C1-C18) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G1, G2) and/or the main power unit (MPS1, MPS2); and a management module which is capable of controlling the contactors (C1-C18), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS1, MPS2) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G1, G2).

Abstract: A method of fabricating a ceramic turbine blade, the method includes selective melting on a powder bed in order to obtain a blade mold cavity in a mold, a ceramic-based suspension is provided, the suspension is introduced into the blade mold cavity, the suspension is subjected to a gelation step in the mold cavity in order to obtain a blade suitable for being extracted from the mold cavity, and the blade is extracted from the mold cavity.

Abstract: A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.

Abstract: An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

Abstract: An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a first gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein said supply means has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

Abstract: The invention relates to an aircraft turboprop engine (310) comprising at least a low-pressure body (12) and a high-pressure body (14), possibly also an intermediate-pressure body, at least one of said bodies comprising a compressor, the low-pressure body driving a propeller by means of a first gearbox (16), the turboprop engine also comprising means for supplying air to an air-conditioning circuit of an aircraft cabin, characterised in that said supply means comprise at least one compressor (60) of which the rotor (61) is coupled to the low-pressure body, said load compressor (60) including an air inlet (62) connected to means (72) for bleeding air from the compressor of the turboprop engine when all of the aforementioned bodies comprise only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies comprise at least two compressors.

Abstract: The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Abstract: The invention concerns a structure (3) for providing emergency electric power to an aircraft (1) comprising a pressurized cabin (10), at least one main engine and an auxiliary power unit (APU), the structure being designed to provide electric power to the aircraft in the event of failure of the main engine and the emergency auxiliary unit, the structure comprising a circuit (30) for recovering air from the cabin (10), and an electricity-generating system (32, 24, 34) which generates electricity by depressurizing the air recovered from the cabin (10).

Abstract: The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the auxiliary power unit; a unit (4) for controlling the airflow fed to the auxiliary power unit; and a valve (31) for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (30), the opening of the valve being driven by the control unit (4). The structure is characterized in that it further comprises a circuit (32) for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Abstract: A method and a system for supplying electrical energy to an aircraft that is equipped with a plurality of loads to be powered, said power supply system comprising a plurality of power sources and an on-board energy management module, the energy management module being electrically connected to said power sources and to said loads to be powered. The energy management module is arranged so as to control a supply of power to at least one of said loads using at least two different power sources in parallel in the event of increased energy requirements, said load being initially powered by a single power source.

Abstract: A method for managing an electrical power supply system (1) of an aircraft, the power supply system (1) comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS1, MPS2), a plurality of contactors (C1-C18) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G1, G2) and/or the main power unit (MPS1, MPS2); and a management module which is capable of controlling the contactors (C1-C18), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS1, MPS2) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G1, G2).

Abstract: A propulsion system including: a booster; a turbojet engine; the booster including a chamber which is fixed to a rear casing of the turbojet engine by being arranged along the longitudinal axis thereof, which chamber includes at a rear a jet pipe and includes at least one charge and a mechanism initiating the charge; and gas bleed tubes connected to the booster and which are configured either for igniting the combustion chamber of the turbojet engine on for starting the turbine of the turbojet.

Abstract: Method for supplying non-propulsive power for an aircraft, comprising the driving of a shaft (13) of an environmental control system (1) of the aircraft by a combination of energy sources selected from: an auxiliary power unit (4), a starter/generator (18), and auxiliary-air supply means (63).

Abstract: 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.