Societe De Construction Des Avions Hurel-dubois

Society De Construction Des Avions

John F Kennedy

Alain M Fournier

The aircraft propulsive unit having on the one hand, a fixed central structure in the axis of which is housed a gas generator whose nozzle delivers a hot jet and, on the other hand, an upstream fan or blower concentric with the gas generator and rotating inside an annular channel defined by the fixed structure and by a peripheral cowling or fairing with double wall carried by the fixed structure, the blower providing the forced circulation of a cold flow in the channel for improving the performance of the power unit, the fairing being formed of two parts, the upstream one of which is fixed and surrounds the blower, whereas the downstream one is mobile and slides parallel to the axis x--x' of the generator, the propulsive power unit further having a system for reversing the thrust of the cold flow which is formed of pivoting doors having respectively external and internal walls which, in the retracted position of the doors, are aligned respectively with the external and internal walls of the fairing. The doors are housed in openings of the sliding part of the fairing, defined by annular parts joined together by beams, the doors pivoting about pivots housed in the beams and each door being coupled by at least one link to the fixed central structure so that the backward movement of the sliding part of the fairing causes rotation of the doors, which frees openings and closes the annular channel, the doors projecting radially outwardly of the fairing.

Aircraft power unit of the type with faired blower equipped with a

The invention provides a thrust inverser for a jet engine comprising doors 5-6 pivotably mounted at 14 on two beams diametrically opposite with respect to the gas discharge channel 2. The mechanism for operating the doors is entirely contained in the closed caisson formed by one of the beams 3, this mechanism comprising an actuating cylinder 15 driving a transmission piece 21 suspended from the beam 3, the transmission piece being coupled to two links 28 pivotably secured to the doors 5 and 6.

Door thrust reverser for a jet engine

The invention relates to thrust reversal devices for jet aircraft turboreactors and particularly for a turbo-fan type engine. The casing E surrounding the engine structure D comprises an intermediate section S3 formed by doors P4 pivoting about an axis 17-17' extending along a chord of passage CA so that the rear part of the door is short, which provides considerable clearance for the doors which may open up to 90.degree., as well as an action of flux F1 flowing in the passage promoting opening of the doors. A jack 21 coupled to each of the doors acts between the fixed structure of the casing and the internal part of the door.

Thrust reversal device for air-craft turbojets

The engine is of the type having a central body surrounded by a casing defining therebetween a duct for the passage of the flux. The casing comprises a fixed upstream section extended downstream by means in which are housed jacks; a downstream section movable axially to which are fixed the rods of the jacks; and an intermediate section formed of swinging doors mounted between the beams and hinged thereto by lateral pivots, each door being coupled to the mobile downstream section by means of a hinged link so that the movement of the downstream section causes the doors to swing. This type of reverser is designed more especially for turbo-fan engines having a lateral nacelle configuration in which the whole of the flux flows in the annular duct between the central body and the casing.

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Boulogne, France

John F Kennedy