Abstract: A conveyor system for conveying at least one product comprises a spiral first conveyor having a vertically extending central axis. The first conveyor comprises a number of conveying elements extending substantially parallel to each other. Each conveying element comprises at least one supply end for receiving the product and at least one discharge end for discharging the product. The discharge ends of the individual conveying elements are positioned at different vertical levels.

Abstract: An aircraft propulsion system including a bypass turbojet engine surrounded by a nacelle together with a mechanism attaching the engine to a pylon of an aircraft. The nacelle includes an inner structure forming a body of revolution including a rigid framework formed by an upstream annular frame fastened to an intermediate casing of the engine, a downstream annular frame supporting the exhaust casing of the engine, and longitudinal arms connecting the frames together, the annular downstream frame being fastened to the pylon by a flexible or hinged suspension mechanism.

Abstract: An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing.

Abstract: A device including a pair of counter rotating propellers with variable pitch which may be modified by an actuator located in a central cavity of the shafts. A system for transporting energy to the actuator includes a conduit passing into a static case in proximity to an epicycloidal gear train, and then control conduits leading to the actuator and crossing the planet carrier of an epicycloidal gear train. The junction is affected by a dynamic joint with a collector. This transport path avoids a high temperature turbine.

Abstract: An aircraft propulsion system (110) comprising a bypass turbojet engine surrounded by a nacelle defining a flow passage for the secondary stream flows, and connection means for connecting the engine to a wing (132) of an aircraft and comprising a pylon (134) substantially parallel to the longitudinal axis (135) of the engine together with suspension means suspending the engine from the pylon, the pylon being angularly offset from a vertical plane (150) containing the longitudinal axis of the engine and from the top of the nacelle, and being situated outside the flow path for the secondary stream.

Abstract: A conveyor for conveying products comprises at least a drivable helically-shaped inner track conveyor member and a drivable helically-shaped outer track conveyor member. The outer track conveyor member surrounds the inner track conveyor member. The pitches of the inner track conveyor member and the outer track conveyor member are different.

Abstract: A conveyor for conveying products comprises at least a drivable helically-shaped inner track conveyor member and a drivable helically-shaped outer track conveyor member. The outer track conveyor member surrounds the inner track conveyor member. The pitches of the inner track conveyor member and the outer track conveyor member are different.

Abstract: A method for buffering products, such as bottles, cans and pots, wherein the products are carried upwards on a moving, inclined first conveying surface at a first flow rate. The products on the first conveying surface can accumulate against a guide member at the upper end of the first conveying surface, after which the products are guided from the guide member onto a second conveying surface, on which they are conveyed onwards at a second flow rate. The first conveying surface is disposed at such an angle and is provided with such a surface condition that the dragging force exerted on the products from the first conveying surface is just a little greater than the force of gravity being exerted on the products in the direction along the conveying surface. As a result, the products can be buffered in a simple manner, while the products exert only little pressure on each other.

Abstract: A conveyor system for conveying a product comprises a first conveyor adjacent to a second conveyor via a junction, the conveying direction of the first conveyor near the junction is different from the conveying direction of the second conveyor near the junction. The first conveyor has a first conveying surface and the second conveyor has a second conveying surface for supporting the product thereon. The first conveyor describes at least a spiral path near the junction wherein a central axis extends at least substantially in vertical direction. A moving assembly is configured to move the product from the first conveyor to the second conveyor. The moving assembly comprises a push-out guide which makes a stroke for each product that passes, or comprises a guide configured such that products are guided automatically along the guide only upon the movement of the conveying surface of the first conveyor.

Abstract: A system, including: a linear actuator axially arranged in a first propeller and rotatably secured thereto, a first linking mechanism connecting a rod of the linear actuator to a second propeller to change a setting of blades thereof, and including an intermediate bearing between the propellers, which is capable of transmitting translation of the rod of the linear actuator and disconnecting a rotatable link to the first propeller to make it possible to change the setting of the blades of the second propeller rotated in an opposite direction to the first propeller, and a second linking mechanism combined with blades of the first propeller to change a setting thereof.

Abstract: A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.

Abstract: A turbojet is suspended by attachments including hinged links. An attachment includes a support including three branches with passages through which a pin passes, the pin being oriented generally parallel to a direction that is tangential to a casing and being hinged to a central branch of the support by a ball joint.

Abstract: An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.

Abstract: A conveyor system for conveying at least one product comprises a spiral first conveyor having a vertically extending central axis. The first conveyor comprises a number of conveying elements extending substantially parallel to each other. Each conveying element comprises at least one supply end for receiving the product and at least one discharge end for discharging the product. The discharge ends of the individual conveying elements are positioned at different vertical levels.

Abstract: A device for protecting a computer of an aircraft turbine engine, the device comprising a box containing the computer and a cover covering the box, the box being supported by tabs forming integral portions of the box and maintaining a flow of air between the bottom of the box and a portion of the casing of the engine on which they are to come into secure contact via resilient studs, the box being made of a composite material.

Abstract: An assembly is designed to attach hangers from which an aircraft propulsion unit is suspended. The propulsion unit is intended to be suspended from a structural element of the aircraft. The propulsion unit includes a turbojet engine having a longitudinal axis and the attachment assembly having a clevis mount for attaching the hangers to a casing of the propulsion unit. The clevis mount is fixed to the casing by means designed to form a connection between the clevis mount and the casing at the external periphery of the casing.

Abstract: The present invention relates to an annular case (20) of a multi-flow turbojet engine comprising a first element (22) forming a hub, a second element (24) forming a cylindrical casing, radially on the outside of and concentric with the first element, radial arms (23) connecting the first element (22) to the second element (24), at least part of said arms being structural and having an aerodynamic flow straightener vane profile, characterized in that it comprises a first ring sector (20C) of the case and a second ring sector (20T), the first ring sector being made of composite material and the second ring sector of metal, said radial arms (23T) of the second ring sector (20T) being structural.

Abstract: A gas turbine engine including: a casing in which is mounted at least one shaft for driving a fan solidly connected to a driving drum including blades to compress an airflow moving from upstream to downstream in the engine; and an axial retention mechanism, on standby, solidly connected to the casing and arranged to come into contact with the driving drum such as to prevent axial movement of the drum in event of breakage of the driving shaft.

Abstract: An air inlet duct and method for producing such for a turbojet nacelle, the air inlet duct including an upstream annular lip and a downstream outer annular structure. The upstream annular lip and the downstream outer annular structure are formed as a one-piece part made from composite material and the upstream lip is covered with a metal layer formed by electro-deposition or plastic forming. A turbofan engine can include such an air inlet duct.

Abstract: A fitting including at least one composite material bracket with two flat segments forming an angle less than 180° on an inside of the bracket and an angle greater than 180° on an outside of the bracket, together with a stiffener extending on the inside of the bracket between the two flat segments is disclosed. The bracket presents a slot crossing a straight line between the two flat segments, the slot extending into the two flat segments. The stiffener is folded in register with the slot and includes tabs fastened to each of the two flat segments.