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 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 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.