Abstract: A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is hydroformed against a circular blank made from titanium or titanium alloy.

Abstract: A method for increasing the coefficient of adhesion between two parts that rotate as one with a rotor, for example a turbomachine rotor, those parts pressing against one another via pressing faces. The method includes milling at least one of the pressing faces so as to modify its surface finish and increase its roughness, then covering the or each machined face with a thin layer of a material that is hard and has a high coefficient of friction.

Abstract: A method for repairing a compressor blade of a turbine engine, the blade including a cat's tongue at the radial end thereof, the radial extension of which is less than a predefined nominal radial extension. The method includes elongating the cat's tongue via a cold-compacting operation applied to the walls of said tongue, such that the radial elongation thereof becomes greater than the nominal extension. The compacting operation is a rollerburnishing operation carried out by moving the end of the blade between two rollers having rectilinear generatrices and spaced apart by a distance smaller than the thickness of the cat's tongue, along the chord connecting the leading edge with the trailing edge thereof.

Abstract: A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream.

Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.

Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.

Abstract: A wall-cooling device for cooling a wall subjected to a heat source and to an outer fluid. The device includes a cooling part with a fastening portion and a cooling portion. The cooling part is made of a thermally-conductive shape-memory alloy having a transition temperature T. The fastener portion is for fastening the device rigidly on a face of the wall. The cooling portion is shaped so that it takes up a first position that is substantially parallel to the wall when the temperature of the wall is lower than the temperature T and so that it takes up a second position in which a plane of the second portion defines, relative to a plane tangential to the wall, a dihedral angle lying in the range 45° to 90° .

Abstract: An actuating device for opening and closing at least one shutter in a gas turbine engine, such as a turbojet engine, includes at least one actuator made of a two-way shape memory alloy having a first stable state at a first temperature in which state it actuates either the opening or the closing of the shutter, and a second stable state at a second temperature, in which state it actuates either the closing or the opening of the shutter, respectively.

Abstract: The de-icing system comprises a flexible bladder (5) filled with de-icing fluid, pressed by the centrifugal forces produced when the rotor tip (1) is rotating against the inner wall thereof to apply a pressure favoring the progressive and calibrated discharge of the fluid, in the absence of a pump and any other active means. For this, the bladder comprises a concavity (11) at the rear which is automatically enlarged under the effect of centrifugal forces during operation and discharges the fluid continuously from the bladder.

Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.

Abstract: A method for repairing a compressor blade of a turbine engine, the blade including a cat's tongue at the radial end thereof, the radial extension of which is less than a predefined nominal radial extension. The method includes elongating the cat's tongue via a cold-compacting operation applied to the walls of said tongue, such that the radial elongation thereof becomes greater than the nominal extension. The compacting operation is a roller-burnishing operation carried out by moving the end of the blade between two rollers having rectilinear generatrices and spaced apart by a distance smaller than the thickness of the cat's tongue, along the chord connecting the leading edge with the trailing edge thereof.

Abstract: A device for centering a tube inside a hollow shaft is disclosed. The device includes a deformable device interposed between the tube and the hollow shaft and including bearing members for bearing against the inside surface of the shaft and suitable for being spaced away from the inside surface of the shaft in order to enable them to be moved inside the shaft. The deformable device is made of a shape-memory material suitable for deforming to press the bearing members against the inside surface of the shaft or to space them away therefrom on being subjected to a predetermined temperature.

Abstract: A thermal protection coating, in particular for a turbine-engine part (12), the coating being deposited by thermal spraying onto the surface of the part (12) and including at least 80% by volume of hollow ceramic microbeads distributed in a metal alloy based on nickel or cobalt, it being possible for the coating to be deposited on a bonding layer (22) of metal alloy and for it to be covered in a layer (26) providing protection against erosion or against friction wear, or in a reflective layer that reflects thermal radiation.

Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor driving a shaft capable of rotating with respect to a stator in the event of said shaft breaking is disclosed. The device includes a first braking member provided with at least one abrasive element and a second braking member including a ring-shaped element (120A) made of a material capable of being eroded by the abrasive element. One of the two braking members being secured to the rotor and the other of the two braking members being secured to the stator. The braking members come into contact with one another through axial displacement of the rotor once the shaft has broken. The abrasive element of the first braking member eroding the ring-shaped element of the second braking member.

Abstract: A support for a bearing that guides a shaft in a turbomachine is disclosed. The support includes an annular part made of a shape memory material which retains an initial shape when the load applied to it remains below a threshold value and which deforms, absorbing energy when the applied load becomes at least equal to the threshold value. The annular part is capable of reverting at least approximately to its initial shape when the applied load drops back below the threshold value.

Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.

Abstract: A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A ring made of steel, steel alloy, or superalloy which is incombustible in the presence of a titanium fire is ring roll-bonded with a ring made from titanium or titanium alloy.

Abstract: A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream.

Abstract: A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). An explosion cladding of a circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is accomplished on a circular blank made from titanium or titanium alloy.

Abstract: A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is hydroformed against a circular blank made from titanium or titanium alloy.