Abstract: A turbofan jet engine includes an outer casing supported by arms, an inner casing facing the outer casing, ancillaries, and an ancillaries distribution support. The ancillaries distribution support is formed along the axis of an arm on the inner casing. The ancillaries distribution support includes a first sole plate for reception of ancillaries on the outer side of the inner casing and a second sole plate for reception of ancillaries on the inner side of the inner casing. Such a turbofan jet engine reduces the longitudinal dimension necessary for the ancillaries to pass through.

Abstract: A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.

Abstract: The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.

Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.

Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.

Abstract: The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.

Abstract: This invention concerns a turbofan jet engine comprising an outer casing supported by arms, an inner casing facing the casing and ancillaries. An ancillaries distribution support is formed along the axis of an arm, on the inner casing, comprising a first sole plate for reception of ancillaries on the outer side of the inner casing. The invention reduces the longitudinal dimension necessary for the ancillaries to pass through.

Abstract: A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.