Abstract: A device for spraying a liquid for use in dye penetration inspection into an inner cavity of a workpiece for making a turbine engine part, the device including a workpiece support, a manifold for spraying the inspection liquid into the inner cavity, a manifold for sucking up and discharging the sprayed inspection liquid, and a mechanism for tilting at least a portion of the support from a substantially horizontal position to an inclined position in which the workpiece is inclined so that the inspection liquid sprayed into the cavity flows under gravity to a zone from which it is sucked up.

Abstract: A method for improving the heat resistance of a resistive element embedded in an alumina deposit covering a surface of a substrate, in which the alumina deposit includes a surface portion and a deep portion which is sandwiched between the surface portion and the surface of the substrate and in which the resistive element is located, is provided. The method includes a densification of the surface portion of the alumina deposit.

Abstract: A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Abstract: A device heating a fluid and usable in a rocket launcher to pressurize a liquefied propellant. The device includes a first burner performing first combustion between a limiting propellant and an excess propellant; a first heat exchanger in which first burnt gas from the first combustion transfers heat to the fluid; at least one second burner into which both the first burnt gas and some limiting propellant are injected to perform second combustion between the limiting propellant and at least a portion of unburnt excess propellant present in the first burnt gas. The second burnt gas from the second combustion flows through a second heat exchanger to transfer heat to the fluid. Burnt gas from each combustion flows in respective burnt gas tubes within a common overall heat exchanger including the heat exchange units, the gas transferring heat to the fluid, the fluid flowing between the burnt gas tubes.

Abstract: A sensor is placed on a plate lowered into the hollow of the shaft and guided by taut wires between a lower attachment device and an upper motorized winder. The deformations, responsible for measurement errors and caused either by static deformations, produced by the weight or poor construction of the apparatus, or by vibrations, are to a large extent eliminated.

Abstract: A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.

Abstract: The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.

Abstract: A turbojet engine including an intermediate casing including radial arms and a driveshaft for a gearbox for auxiliary machines of the turbojet engine, the driveshaft mounted in a radial arm, the radial arm including an intermediate bearing supporting the driveshaft, the intermediate bearing including plural rolling bearings supporting the driveshaft, the driveshaft including a first shaft element connected at one end to a mechanism providing mechanical transmission to an engine shaft of the turbojet engine, and a second shaft element connected at one end to a mechanism providing mechanical transmission to the box. The first shaft element and the second shaft element are linked by a connection including plural splines. A single plane transversely passes through the plural splines and the plural rolling bearings.

Abstract: A method of estimation on a curve of a relevant point for detecting an anomaly of a motor. The method includes selecting a profile including a binary code, each component of which codes a direction of variation between two consecutive characteristic points of at least one learning curve, a model making it possible to estimate a relevant point based on a set of characteristic points of a curve and a filter. The method also includes applying the filter of the profile selected to the curve, determining a set of characteristic points of the filtered curve and of a binary code, comparing the determined code and the code of the profile selected, and estimating, as a function of the comparison, the relevant point on the curve based on the characteristic points of the filtered curve and the model of the profile selected.

Abstract: Device for depressurizing at least one chamber (E1, E2) of a turbomachine (1) intended to accommodate at least one bearing (7, 8) of a rotor of said turbomachine, which bearing is supplied with lubricating oil under pressure by a feed pump (15) and by an oil feed duct (16), said device comprising at least one breather tube (10) connected to said chamber in order to extract an oil mist therefrom, an oil separator (30) able to separate the oil from the air in said mist and a jet pump (11) pneumatically connected to said chamber by said breather tube and said oil separator, said pump comprising a pump tube (17) into which there open a primary circuit (21) supplied with fluid under pressure via a fluid feed duct and a secondary circuit (22) connected to said oil separator in order to place the chamber under a reduced pressure, characterized in that the primary circuit (21) comprises at least two pressurized-fluid injectors (13, 24) positioned in said tube and fed independently of one another.

Abstract: The main purpose of the invention is a propeller (32) for a turbomachine (1) comprising a plurality of blades (48) and a blade support ring (47) fitted with housings (50) each of which holding a pivot (52) supporting the root (58) of one of said blades (48), characterized in that at least one of the pivots (52) is associated with at least one dynamic scoop (100), capable of moving between distinct positions, an open position in which a cooling airflow (F) can be captured, and a closed position as a function of the orientation of the corresponding blade.

Abstract: A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element.

Abstract: An aircraft turbine engine including at least one spool rotating at speed N1 and a monitoring system including: a regulating module including at least one regulation measurement channel to obtain a measurement of the speed N1 and a mechanism to compare the obtained speed measurement with a thrust setpoint to provide a thrust status; and a module for engaging a protection function of UHT or ATTCS type of the turbine engine. The turbine engine further includes a system for protection against overspeed to prevent ejection of high-energy debris outside the turbine engine, the protection system including at least one overspeed measurement channel to obtain an overspeed of the rotating spool of the turbine engine. The engagement module compares at least one overspeed obtained with at least one reference speed defined according to the protection function to be engaged, to engage the protection function according to results of the comparison.

Abstract: A mechanical system for a turbomachine includes a turbomachine part to be attached and a plurality of threaded attachment elements mounted on the turbomachine part in sequence along a line. The attachment elements fix the turbomachine part to the turbomachine. At least some of the attachment elements are arranged to be prevented from rotating by mutual cooperation about their corresponding thread axes, by a rotation prevention system provided on each of these attachment elements called self-locking elements. The self-locked elements cooperate in pairs, each pair including two directly consecutive self-locked elements along the line. At least one of the pairs has a distance between the thread axes of its two self-locked elements less than the distance between one of these two thread axes and the axis of either of the two attachment elements arranged along the line on each side of the at least one of the pairs.

Abstract: A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a spark plug guide and including an inner collar and an outer collar that are axially spaced apart from each other by a cylindrical portion. Each collar extends radially outwards. The bushing is floatingly mounted inside the chimney with its collars axially positioned between the collar of the chimney and the washer. The inner collar comes in operation to bear against the collar of the chimney. The outer collar presents an outside diameter (d1) greater than the inside diameter (d2) of the washer.

Abstract: Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.

Abstract: A rotating assembly for a turbomachine, including a disc having an external periphery with alternating recesses and teeth, blades extending radially from the disc and the feet of which are axially engaged and radially retained in the recesses of the disc, platforms extending on the circumference from the blades and being arranged end to end on the circumference, with respect to each other, axial sealing device upstream and/or downstream of an annular zone extending radially from the platforms up to the disc. The sealing device radially includes an internal annular portion and an external annular portion structurally distinct from each other, and the external annular portion of which is elastically constrained radially inwards by the internal annular portion.

Abstract: A method of fabricating a composite material casing for a gas turbine engine, the method including making an outer shroud including a platform and a flange, making an inner shroud of smaller diameter than the outer shroud and including a platform and a flange, making a plurality of casing arms, each including a blade that is terminated at each radial end by a respective platform, arranging a plurality of openings in the respective platforms of the shrouds, each opening serving to receive a platform of a casing arm, and assembling the casing arms with the outer shroud and with the inner shroud by inserting the platforms of the casing arms in the openings of the shrouds. A composite material casing is obtained by such a method.

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Abstract: The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.