Abstract: The present invention relates to novel 2-primary amino-4-secondary amino-quinoline derivatives, their manufacture, pharmaceutical compositions comprising them and their use as medicaments. The active compounds of the present invention are useful for the treatment and prevention of proliferative neoplastic and non-neoplastic diseases.

Abstract: The present invention relates to novel 2-primary amino-4-secondary amino-quinoline derivatives, their manufacture, pharmaceutical compositions comprising them and their use as medicaments. The active compounds of the present invention are useful for the treatment and prevention of proliferative neoplastic and non-neoplastic diseases.

Abstract: The invention relates to an assembly on an engine, which comprises a first and a second piece mounted so as to rotate relative to one another. A connecting device is provided between such pieces. It comprises a first annular part defining a flange fixed to the first piece a second annular part extending substantially parallel with the axis of rotation of the engine and studs connecting the first and second annular parts together. An interface for the rotational sliding about said axis is positioned between the second annular part and the second piece. The second annular part is sectorized.

Abstract: The invention provides quinoline derivatives, their manufacture, pharmaceutical compositions containing them, and their use as medicaments. The active compounds of the present invention are useful for the treatment of proliferative neoplastic and non-neoplastic diseases.

Abstract: A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet.

Abstract: A method for improving the operational life of production parts, such as steel sucker rods, couplings, pump parts, and tubes, for use in underground recovery or production of oil and gas, includes coating the steel production parts with a layer of corrosion resistant alloy (CRA) to reduce a loss rate of the steel by improving corrosion resistance and mitigate pitting. In one embodiment, the corrosion resistant alloy is a nickel-based alloy. In other embodiments, the steel production parts can either be coated with an epoxy/phenolic layer, or coupled with a sacrificial anode. The coating process can implemented by any one of the following processes: cold spray coating; electroless corrosion resistant coating; flow forming; and electrochemical machining.

Abstract: The invention relates to an insert for a turbine engine test vane including the insert and a vane body. The insert includes at least two external surfaces. The insert is configured to fit into the vane body, such that the external surfaces are vane aerodynamic surfaces each forming part of a vane aerodynamic profile.

Abstract: The invention relates to an assembly on an engine, which comprises a first and a second piece mounted so as to rotate relative to one another. A connecting device is provided between such pieces. It comprises a first annular part defining a flange fixed to the first piece a second annular part extending substantially parallel with the axis of rotation of the engine and studs connecting the first and second annular parts together. An interface for the rotational sliding about said axis is positioned between the second annular part and the second piece. The second annular part is sectorized.

Abstract: The invention provides quinoline derivatives, their manufacture, pharmaceutical compositions containing them, and their use as medicaments. The active compounds of the present invention are useful for the treatment of proliferative neoplastic and non-neoplastic diseases.

Abstract: A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X.

Abstract: A method for improving the operational life of production parts, such as steel sucker rods, couplings, pump parts, and tubes, for use in underground recovery or production of oil and gas, includes coating the steel production parts with a layer of corrosion resistant alloy (CRA) to reduce a loss rate of the steel by improving corrosion resistance and mitigate pitting. In one embodiment, the corrosion resistant alloy is a nickel-based alloy. In other embodiments, the steel production parts can either be coated with an epoxy/phenolic layer, or coupled with a sacrificial anode. The coating process can implemented by any one of the following processes: cold spray coating; electroless corrosion resistant coating; flow forming; and electrochemical machining.

Abstract: A part to modify the profile of an aerodynamic jet, including: a first face configured to be secured on the aerodynamic jet, and a second face defining a modified aerodynamic jet profile, configured to modify an initial profile of the aerodynamic jet.

Abstract: A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.

Abstract: The invention relates to an insert for a turbine engine test vane including the insert and a vane body. The insert includes at least two external surfaces. The insert is configured to fit into the vane body, such that the external surfaces are vane aerodynamic surfaces each forming part of a vane aerodynamic profile.

Abstract: A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

Abstract: A retaining ring assembly for at least one blade of a rotor disk of a turbine engine and a supporting flange for the ring. The flange and the ring are rotating parts having an axis X, the flange including an attachment edge configured to be connected to the rotor disk and a free edge configured to bear against the retaining ring; and the flange bears against the ring such that the bearing force of the flange on the ring has an axial component and a radial component relative to the axis of revolution X.

Abstract: A low-pressure turbine for a turbomachine including turbine disks with festooned annular flanges for fastening to a festooned annular flange of a drive cone connecting the turbine disks to a turbine shaft, solid portions of the festooned annular flanges of the turbine disks and of the drive cone being connected to peripheries of the turbine disks and of the drive cone, respectively, via concave filets that are asymmetrical.

Abstract: A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.