Abstract: A device for ventilating turbine components in a gas turbine engine which includes first and second turbine rotors mechanically independent of each other, the first turbine rotor includes an HP turbine disk and the second turbine rotor includes an LP turbine disk and with a first circuit for ventilating the LP turbine is disclosed. The device includes an air compression wheel arranged downstream of the HP turbine disk between the HP turbine disk and LP turbine disk in order to assist the circulation of the air in the first circuit.

Abstract: A device for the detection of the passage of objects, people or animals bearing a radio frequency identification (RFID) tag, including at least one mobile support which, when at rest, forms a barrier to the passage of the objects, people or animals and which, when in contact with the latter, is capable of moving towards a withdrawn position, this mobile support bearing an antenna connected electrically to an RFID tag reader.

Abstract: A turbomachine such as an aircraft turbojet including an electrical generator/starter that can be mounted and dismounted by axial translation in an upstream enclosure of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables which extend inside the structural arms of the intermediate casing of the turbomachine.

Abstract: Turbomachine such as an aircraft turbojet comprising an electrical generator/starter (26) that can be mounted and dismounted by axial translation in an upstream enclosure (18) of the turbomachine between the low-pressure compressor and the high-pressure compressor, and couple to electrical cables (34) which extend inside the structural arms (12) of the intermediate casing (10) of the turbomachine.

Abstract: Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine case elements, the nozzle being caused to pivot by an actuator 46 mounted on the engine case and connected by a link 50 to a pivot 22 of the nozzle.

Abstract: An assembly arrangement between an inner race of a bearing and a journal supported in rotation in this bearing includes a journal annular groove and a race annular groove which interact to form an annular channel when they are placed opposite one another. The assembly further includes a retaining ring placed in the annular channel, which prevents a relative movement in translation between the journal and the inner race. The assembly also includes at least one recess of the journal and at least one tooth of the inner race, which interact to prevent a relative movement in rotation between the journal and the inner race.

Abstract: According to one aspect of the present invention there is provided an acoustic laminate suitable for use in wall, floor and ceiling assemblies and other dividing structure assemblies, the laminate including: a viscoelastic acoustic barrier being in the form of discrete, spaced apart sections or a continuous layer; and a construction panel, the barrier affixed to one or more panel faces of the construction panel.

Abstract: A composition for producing sheet material with sound dampening properties wherein the composition includes water, gelatine, glycerine and a filler material.

Abstract: A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Abstract: A compressor with a centripetal air takeoff system that includes pipes installed between an outer collar and an inner collar. Each pipe is fitted in a hole in the outer collar and in a hole in the inner collar. The system further includes a locking mechanism between the pipe and the inner collar.

Abstract: According to one aspect of the present invention there is provided an acoustic laminate including: a first layer of viscoelastic acoustic barrier material; a sound absorbing/decoupling batt affixed to the first layer of viscoelastic acoustic barrier material, the batt at rest defining a batt plane; the batt including a plurality of batt fibres; the batt further including retaining fibres, wherein the batt fibres and/or retaining fibres are disposed perpendicular to the batt plane and having end portions thereof disposed at a batt surface, the end portions affixed to the viscoelastic barrier material so that either the first layer of viscoelastic acoustic barrier material or the sound absorbing/decoupling batt itself may be retained in spaced relation from a mounting surface when the laminate is so mounted, the retention being achieved in any orientation by bearing a mass load of the batt or first layer of viscoelastic material along the axis of the affixed batt fibres and/or retaining fibres.

Abstract: The apparatus of this invention comprises a casing (10) having an upstream chamber (12) which feeds with cold air an auxiliary duct (40) that supplies at least one first duct (52, 54), which feeds a rear zone (ZAr) of the cabin; a first mixing chamber (20) which supplies processed air to second ducts (30, 32, 34) that feed a front zone (ZAv) of the cabin; and a heating chamber (16) which supplies heated air to the mixing chamber (20) and the first duct or ducts. The device further comprises a second mixing chamber (50) and a single distribution shutter valve (56), having a first control member (60) which is arranged to distribute part of the heated air coming from the heating chamber (16) selectively, either to the first mixing chamber (20) or to the second mixing chamber (50); and a second control member (62) arranged to control distribution of the mixed air from the second mixing chamber through the first duct or ducts (52, 54). Applicable to motor vehicles.

Abstract: The device (10) of the invention comprises a shaped box having a bottom wall (12) connected to a peripheral wall (14) in order to delimit a housing (20) for receiving the enclosure (22) of an electric motor (24) driving a turbine (32), the latter being received in a volute (26). The bottom wall (12) has in it at least two holes (48) at a distance from the rotation axis (XX) defined by the motor shaft so as to allow the passage of a flow of cooling air (F) which passes through the enclosure (22) of the motor and rejoins the volute (36). Application in particular to automobile heating, ventilation and/or air-conditioning apparatus.

Abstract: An eletronic package comprising a printed circuit board on which are mounted a plurality of decoupling capacitors is disclosed. A carrier component electrically connects an integrated circuit to the printed circuit board through a plurality of solder balls. The plurality of solder balls comprises at least one solder ball for the integrated circuit ground voltage connection and at least one solder ball for the integrated circuit power voltage connection. The plurality of decoupling capacitors is organized as a set of ‘n’ capacitors ranged from a lower capacitor value Clow to a higher capacitor value Chigh such that the range Clow to Chigh of the ‘n’ capacitor values is a function of the frequency range Flow to Fhigh on which the integrated circuit operates.

Abstract: The invention concerns a device comprising a dressing provided with a layer (8) for absorbing the wound exudates and electric supply means (9) to circulate a current in said wound, through the dressing. The invention is characterized in that said layer (8) consists of a dry hydrophile substantially non-conductive layer at the time it is applied on the wound, the subsequent migration of the exudates into the thickness of said layer (8) controlling the activation of said electric supply means (9), concomitantly with the continuation of the process of exudate absorption by said layer (8).

Abstract: An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulation of the nozzle cross section and direction. Converging flaps (7) are guided on an upstream side by the spherical wall (5) and are supported at a downstream side by a control lever (13) which hinges on the control ring (12) and rests upstream on an external surface (16) of the spherical wall (5). Diverging flaps (10) hinge on the converging flaps (7) to form an inner ring of hot flaps. The diverging flaps (10) are situated downstream in an extension of the converging flaps (7) and further hinge on an outer ring of cold flaps (11), which in turn hinge on the control ring (12).

Abstract: An axially symmetric turbojet engine exhaust-nozzle includes a system for masking the exhaust jet, such system including inner hot flaps (7), hinging on a conical shell (4) and driven by a first control ring (10) powered by linear actuators (11), and outer cold flaps (20) hinging on an annular assembly (12) and driven by a second control ring (22) powered by linear actuators (23) to vary the angle of the cold flaps. The annular assembly (12) is axially displaceable by a third set of linear actuators (30). Each cold flap (20) comprises an inner skin (40) fitted with orifices (43) and hinging on the annular assembly(12) and an outer skin (41) spaced radially away of the inner skin (40) to define an air flow channel between the skins.

Abstract: A gas-flow exhaust assembly for a jet propulsion system of an aircraft in which a converging exhaust nozzle (4) is fitted with translating cold flaps (21, 22). The primary exhaust nozzle (4) comprises two hot-flaps (5, 6) situated beyond a primary duct (1) enclosed by an aircraft fairing (2). The fairing (2) is extended by a secondary exhaust nozzle (20) which is supported by the primary duct (1) and which is translatable by a control mechanism (27a, 27b). The secondary exhaust nozzle (20) comprises cold flaps (21, 22) which are driven by another control mechanism (29a, 29b) independently of the angular positions of the hot flaps (5, 6). Preferably, there are two eyelid-shaped cold-flaps (21, 22) hinging and supported on horizontal transverse shafts (23a, 23b). The shafts (23a, 23b) are preferably affixed on two lateral slides (24a, 24b) which slide on the primary duct (1) and are displaceable by the control mechanism (27a, 27b) which translates the secondary exhaust nozzle (20).

Abstract: A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to the rear portion of the turbojet engine, and an inner flap ring having a plurality of inner forward driven flaps and a plurality of inner forward interlock flaps, each having a forward portion pivotally attached to the rear portion of the turbojet engine, the inner flap ring also having a plurality of inner rear driven flaps and a plurality of inner rear interlock flaps, each inner rear flap having a front edge portion pivotally connected to a rear edge portion of a corresponding inner forward flap.