Abstract: A system for measuring a bending deformation of a surface of a material which cooperates with a bending test machine to deform a test piece. The system includes a first portion with lateral teeth which bear against an upper surface of the test piece. A first load support connected to the lateral teeth applies a constant force towards the test piece. A second portion with a central tooth bears against the upper surface. A second load support connected to the central tooth applies a constant force oriented towards the test piece. A measuring device includes a deformation sensor having a first arm connected to the first portion, and a second arm connected to the second portion. The first arm and the second arm are separated from each other by a variable distance (?B) measured by the measuring device.

Abstract: A system for measuring a bending deformation of a surface of a material which cooperates with a bending test machine to deform a test piece. The system includes a first portion with lateral teeth which bear against an upper surface of the test piece. A first load support connected to the lateral teeth applies a constant force towards the test piece. A second portion with a central tooth bears against the upper surface. A second load support connected to the central tooth applies a constant force oriented towards the test piece. A measuring device includes a deformation sensor having a first arm connected to the first portion, and a second arm connected to the second portion. The first arm and the second arm are separated from each other by a variable distance (AB) measured by the measuring device.

Abstract: A coupon suitable for peeling tests, derived from a vane and including: (i) a portion of blade that comprises an intrados surface, an extrados surface and a leading edge and/or trailing edge and (ii) a vane reinforcement that covers and is glued to at least a part of the intrados surface, a part of the extrados surface and which extends beyond the leading and/or trailing edge. The reinforcement is split over the entire length of the leading edge and/or trailing edge such that the reinforcement is separated into two plates separate from one another and facing each other on either side of the slit beyond the leading and/or trailing edge. Furthermore, at least one of the plates furthermore comprises, beyond the leading and/or trailing edge, notches configured to provide a hold to this same plate.

Abstract: A device to test the peeling resistance of coupons, each formed of a support and an adhesive, includes: (i) a frame including rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a traction device including a vertical jack linked to an attachment element including a loop configured in order to cause detachment of the adhesive from the surface of the support, (iii) a device for measuring the force exerted by the jack in order to pull the loop during peeling, and (iv) a coupon, complex in shape, such as one derived from a reinforced vane. At least one roller is translationally adjustable in relation to other rollers and the coupon is specially prepared in order to facilitate carrying out the tests.

Abstract: A device and a method for peeling tests, in order to test the peeling resistance of coupons each formed of a support and an adhesive. The device comprises: (i) a frame comprising rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a traction device comprising a vertical jack linked to an attachment element comprising a loop configured in order to cause detachment of the adhesive from the surface of the support, (iii) a device for measuring the force exerted by the jack in order to pull the loop during peeling, and (iv) a coupon, complex in shape, such as one derived from a reinforced vane. At least one roller is translationally adjustable in relation to other rollers and the coupon is specially prepared in order to facilitate carrying out the tests.

Abstract: A coupon suitable for peeling tests, derived from a vane and comprising: (i) a portion of blade that comprises a frontside surface, a backside surface and a leading edge and/or trailing edge and (ii) a vane reinforcement that covers and is glued to at least a part of the frontside surface, a part of the backside surface and which extends beyond the leading and/or trailing edge. The reinforcement is split over the entire length of the leading edge and/or trailing edge such that the reinforcement is separated into two plates separate from one another and facing each other on either side of the slit beyond the leading and/or trailing edge. Furthermore, at least one of the plates furthermore comprises, beyond the leading and/or trailing edge, fastening means providing a hold to this same plate.

Abstract: A bypass gas turbine engine having an intermediate structural casing positioned between a primary flow path and a bypass flow path, and configured between a low pressure compressor and a high pressure compressor. The engine further having a bleed device arranged to deflect a portion of a gas flow from the low pressure compressor toward the bypass flow path. The bleed device includes an annular cavity defining a manifold situated upstream the intermediate casing and opening along the outer wall of the primary flow path, a plurality of conduits positioned along the intermediate casing, a plurality of tubes configured around the high pressure compressor and connecting the conduits to the bypass flow path, and at least one flow regulating valve disposed along the interior of each of the plurality of tubes.

Abstract: A bypass gas turbine engine having an intermediate structural casing positioned between a primary flow path and a bypass flow path, and configured between a low pressure compressor and a high pressure compressor. The engine further having a bleed device arranged to deflect a portion of a gas flow from the low pressure compressor toward the bypass flow path. The bleed device includes an annular cavity defining a manifold situated upstream the intermediate casing and opening along the outer wall of the primary flow path, a plurality of conduits positioned along the intermediate casing, a plurality of tubes configured around the high pressure compressor and connecting the conduits to the bypass flow path, and at least one flow regulating valve disposed along the interior of each of the plurality of tubes.

Abstract: A system for cooling the lubricant of the speed reducer of an aircraft turboshaft-engine during high-speed flight and during low-speed taxying. The cooling system includes a radiator through which the lubricant flows. An air supply duct delivers cooling air over the radiator. An air discharge duct discharges the air into the exhaust nozzle of the engine. The air supply duct is fed by an arcuate air take-off slot disposed in the air intake of the engine. The air discharge duct is provided with a flap for slowing air flow through the cooling system, and with an ejector-mixer, which is fed by compressed air, taken from the engine compressor, for creating a Venturi effect to increase air flow through the cooling system when required.

Abstract: A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a fan cowling forming an outer boundary of an airflow duct and a jet engine structure including a jet engine cowling. The thrust reverser has a casing affixed to the jet engine structure, the casing having a plurality of attaching yokes. A first thrust reverser flap is pivotally connected to a corresponding one of the attaching yokes and is located rearwardly of an exit of the airflow duct, each first thrust reverser flap having a distal end and being movable between a forward thrust position, and a reverse thrust position. A second thrust reverser flap is pivotally connected to the distal end of a corresponding one of the first thrust reverser flaps and is also movable between a forward thrust position, and a reverse thrust position, wherein the second thrust reverser flaps also redirect air flow emanating from the air flow duct.

Abstract: A cooling device for an aircraft turboshaft engine includes a boundary layer suction device formed by a perforated external wall portion of the aircraft, a collector on the inside of the wall portion for receiving the air flowing in through the perforations, and a discharge device discharging the air from the collector. The cooling device is completed by a heat exchanger which is disposed in the path of the air flow through the collector, a pump for pumping fluid to be cooled through the heat exchanger from a circuit of the engine, and a regulator regulating the fluid flow through the exchanger to control the temperature of the fluid. The fluid which is cooled may be from the lubrication circuit, the fuel circuit, or an air circuit of the engine, and the boundary layer suction device is preferably disposed in the pod of the engine.

Abstract: A device for suspending a turboprop engine from a structural element of an aircraft comprises a suspension pylon parallel to the longitudinal axis of the engine and fixed to the structural element, resilient connections between the engine and the pylon and an arch fixed to the pylon, and a torsion bar carried by the arch so that the bar can pivot freely about its own axis, the opposite ends of the torsion bar being connected to opposite sides of the engine by respective lever and link rod assemblies so that the torsion bar takes up the reaction torque about the longitudinal axis of the engine.