Abstract: Air conditioning system for the pressurized cabin of an aircraft, said system (1) being characterized in that it comprises an air withdrawal module (3) configured for withdrawing ambient air from outside the aircraft, an air compression module (5) configured for compressing the withdrawn air flow (F1) and an air cooling module (10) comprising means (15) for storing at least one coolant configured for cooling the compressed air flow (F2, F3).

Abstract: A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine.

Abstract: A hydraulic torquemeter comprising a rod which is translatable in a longitudinal direction under the effect of axial thrust which is representative of the torque to be measured, and a hydraulic circuit in which a fluid flows. It also comprises a manometric capsule comprising a pressure chamber which is supplied with fluid by said hydraulic circuit, a sealed flexible membrane which is in contact with the fluid in the pressure chamber, extends in a plane which is substantially perpendicular to said rod, and is rigidly connected to one end of the rod in such a way that a longitudinal movement of the rod deforms the membrane, a drain port for the fluid in said pressure chamber, and a valve designed to adjust the pressure of the fluid in said pressure chamber according to the deformation of said membrane.

Abstract: An air conditioning system for an aircraft passenger compartment, the system including: an air supply circuit connecting at least one external air inlet to at least one air distribution outlet which opens into the compartment, an auxiliary power unit mounted in the supply circuit and configured to compress an air stream in the supply circuit, the supply circuit including a heating first branch that connects the auxiliary power unit to the air distribution outlet, and in which a heating mechanism is mounted, a cooling second branch that connects the auxiliary power unit to the air distribution outlet, and a switching mechanism configured to distribute the air stream between the heating first branch and the cooling second branch.

Abstract: Air conditioning system for the pressurised cabin of an aircraft, said system (1) being characterised in that it comprises an air withdrawal module (3) configured for withdrawing ambient air from outside the aircraft, an air compression module (5) configured for compressing the withdrawn air flow (F1) and an air cooling module (10) comprising means (15) for storing at least one coolant configured for cooling the compressed air flow (F2, F3).

Abstract: A method and architecture for recovery of energy in an aircraft, both at altitude and on the ground, and recovering thermal energy from an exhaust. An architecture for recovery of energy includes an auxiliary power unit APU including an exhaust nozzle and a gas generator including a shaft transmitting power to a load compressor. The compressor supplies compressed air via a supply duct to an ECS air conditioning system of a passenger cabin. A recovery turbocharger is connected, directly or via a transmission case, to the shaft of the APU. The turbocharger includes a recovery turbine powered by a downstream branch of a conduit mounted on a heat exchanger fitted to the nozzle. The conduit includes an upstream branch connected to channels connecting air outlets of the cabin and the compressor. A second exchanger can be mounted between the supply duct and the cabin outlet channel.

Abstract: A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine.

Abstract: A method and architecture for recovery of energy in an aircraft, both at altitude and on the ground, and recovering thermal energy from an exhaust. An architecture for recovery of energy includes an auxiliary power unit APU including an exhaust nozzle and a gas generator including a shaft transmitting power to a load compressor. The compressor supplies compressed air via a supply duct to an ECS air conditioning system of a passenger cabin. A recovery turbocharger is connected, directly or via a transmission case, to the shaft of the APU. The turbocharger includes a recovery turbine powered by a downstream branch of a conduit mounted on a heat exchanger fitted to the nozzle. The conduit includes an upstream branch connected to channels connecting air outlets of the cabin and the compressor. A second exchanger can be mounted between the supply duct and the cabin outlet channel.

Abstract: An air conditioning system for an aircraft passenger compartment, the system including: an air supply circuit connecting at least one external air inlet to at least one air distribution outlet which opens into the compartment, an auxiliary power unit mounted in the supply circuit and configured to compress an air stream in the supply circuit, the supply circuit including a heating first branch that connects the auxiliary power unit to the air distribution outlet, and in which a heating mechanism is mounted, a cooling second branch that connects the auxiliary power unit to the air distribution outlet, and a switching mechanism configured to distribute the air stream between the heating first branch and the cooling second branch.