Abstract: A turbomachine air starter, including a first compartment wherein non-overrunning elements of the air starter are situated, corresponding to elements which are only run in the turbomachine starting phase, and a second compartment wherein overrunning elements of the air starter are situated, corresponding to the elements which are run throughout an operating time of the turbomachine, including the starting phase. The first compartment includes an oil receptacle for oil splash lubrication of the non-overrunning elements, and the second compartment includes an AWC type oil cavity for lubrication of the overrunning elements supplied by the lubrication oil return of the overrunning elements, in turn supplied with pressurized lubrication oil supplied by the turbomachine, the receptacle and the cavity being internal to the air starter.

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: A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor.

Abstract: A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet.

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 system and a method for ventilating a plant including an auxiliary power unit (APU) in an aircraft compartment are disclosed. The compartment is ventilated in an independent manner with individualized air feeds to each item of equipment concerned. According to one embodiment, a system for feeding and ventilating an aircraft auxiliary power source plant includes an APU and items of equipment mounted in connection with the APU. The APU is fitted with an exhaust nozzle which leads into a gas discharger mounted outside the compartment. Separate and independent ducts channel air between air inlets made through the compartment, and the APU and items of equipment. At least one ventilation duct that is separate and independent from the other ducts is coupled to an air inlet of the compartment in order to ventilate the APU and the items of equipment of the plant.

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: A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit; on a monitoring channel: a speed sensor of a turbomachine gas generator shaft, a speed measurement circuit, and a turbomachine stop control circuit. Each channel uses dissimilar characteristics eliminating common mode errors. Each speed sensor delivers a pseudo-sine frequency signal. On each channel, speed monitoring circuits compare the frequency signal with a minimum threshold, delivering an error signal when the measured frequency is lower than the minimum threshold. A common speed cross checking circuit detects exceeding a determined deviation between both frequencies, the monitored deviation being higher or lower than a maximum deviation corresponding to loss of a frequency period on either sensor.

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 concealment that covers all or a main part of naval vessels and their surroundings and crew, by making provision for coupling a flow of air with an injection of fluid to cause formation of a cloud and to orient the cloud to optimize coverage of the vessel and the surroundings to be protected. A concealment apparatus includes a gas turbine coupled to a conduit discharging a flow of smoke composed of a combustion gas loaded with droplets of fluid in suspension. The conduit includes two branches that emerge on each lateral half-hull of the hull of the vessel. The branches are symmetrical with respect to a vertical symmetry plane of the ship and, through their curvature, have roughly a direction oriented towards the rear of the ship. In this way, the flow of smoke is also oriented towards the rear of the ship.

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

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: An auxiliary power supply architecture includes one APU and a fuel supply basic circuit with a common fuel storage tank, a primary circulation conduct and secondary conducts for injecting such fuel into the combustion chambers of the APU unit through appropriate injectors. Such architecture also includes another independent fuel supply circuit to supply the APU unit with an emergency tank, a specific primary conduct for emergency fuel circulation and secondary conducts for injecting emergency fuel into the combustion chambers through appropriate injectors.

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: A shaft for a turbine engine, the shaft having a cavity subdivided axially into first and second chambers. The shaft also includes a distributor member having an axial duct, a first radial orifice, and a second radial orifice. The axial duct has an open first end and a second end closed in the axial direction. The first radial orifice connects the second end of the axial duct to the first chamber in order to feed a first bearing with lubricating fluid, and the second radial orifice connects the second end of the axial duct to the second chamber to feed a second bearing with lubricating fluid. The first radial orifice and the second radial orifice of the distributor member are at substantially equal axial distances from the lubricating fluid inlet.

Abstract: An air starter for turbomachine, including a forward casing, an aft casing, an annular exhaust flow path opening up between an aft end of the forward casing and a forward end of the aft casing, and a cylindrical outlet mesh of the exhaust flow path is disclosed. The forward and aft ends of the outlet mesh include devices for axially retaining the forward casing and the aft casing respectively to the mesh. At least one of the devices for axially retaining one of the casings to the mesh enables a relative rotation of the mesh and this casing.

Abstract: A system and a method for ventilating a plant including an auxiliary power unit (APU) in an aircraft compartment are disclosed. The compartment is ventilated in an independent manner with individualized air feeds to each item of equipment concerned. According to one embodiment, a system for feeding and ventilating an aircraft auxiliary power source plant includes an APU and items of equipment mounted in connection with the APU. The APU is fitted with an exhaust nozzle which leads into a gas discharger mounted outside the compartment. Separate and independent ducts channel air between air inlets made through the compartment, and the APU and items of equipment. At least one ventilation duct that is separate and independent from the other ducts is coupled to an air inlet of the compartment in order to ventilate the APU and the items of equipment of the plant.

Abstract: Air starter for turbomachine, comprising a forward casing (12), an aft casing (14), an annular exhaust flow path (32) opening up between an aft end of the forward casing and a forward end of the aft casing, and a cylindrical outlet mesh (44) of the exhaust flow path (32) the forward and aft ends of which comprise means (48, 52) of axially retaining the forward casing (12) and the aft casing (14) respectively to the mesh (44), wherein at least said means (52) of axially retaining one (14) of the casings to the mesh (44) enable a relative rotation of the mesh (44) and this casing (14).

Abstract: The invention relates to a decoupling sleeve having driving and driven shafts connected by dog clutches. The driving shaft transmits torque to the driven shaft in one direction during a forward direction of rotation where a rod-shaped connecting member is connected to two shafts so that the connecting member is detached from one of the shafts if subject to a reverse torque beyond a specific threshold. The two shafts become free in rotation relative to one another upon this detachment.

Abstract: The invention relates to a decoupling sleeve comprising a coaxial driving shaft and a coaxial driven shaft, connected by dog clutches by means of which the driving shaft transmits engine torque to the driven shaft in one direction during forward operation, a connecting member being connected to the first of the two shafts on the one hand and to the second shaft on the other hand, such that the connecting member is detached from the first shaft in the event of reverse torque occurring beyond a specific threshold, the two shafts being then free in rotation relative to one another. The sleeve is characterized in that the connecting member is connected by screwing to a nut which is mobile in translation relative to the first shaft against a return spring and mobile in rotation over a limited angle, the connecting member being detached from the first shaft by unscrewing the nut. The connecting member is, in particular, in the shape of a rod.