Abstract: The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising: —a step of producing a blank from at least two parts (50, 51), at least one of which is a solid part, the at least two parts being assembled by a diffusions connection technique and without melting, and—a step of machining this blank in order to produce a blade with a defined profile.

Abstract: The present invention concerns a metal reinforcement for a turbomachine blade comprising an aerodynamic surface which extends between a leading edge and a trailing edge, the reinforcement comprising a base (21) forming its leading edge (20) and being extended by two lateral fins (22, 23) so as to define an inner surface capable of receiving the leading edge of the blade, the method comprising the following steps: (a) obtaining at least two parts each forming at least one of the fins of the reinforcement, each part being integral and finished, at least one of the parts being produced by machining a metallic blank; (b) assembling the parts, previously positioned on a tool (8), by a technique of fusion welding or friction stir welding in order to obtain the reinforcement.

Abstract: The present invention concerns an outboard propulsion device for a navigational seacraft comprising a propulsion means (4), at least one engine (1) supplying torque to a drive shaft (20) extending out of the engine and driving a transmission shaft (3) intended to supply torque to the propulsion means, the drive shaft and the propulsion shaft being in a fixed relative orientation, and a transmission means (2) connected at the input to the drive shaft (20) in order to receive the engine torque and transmit it, in the form of modified torque, to the transmission shaft (3) to which it is connected at the output, and the transmission shaft (3) is a double universal joint shaft (30, 31) that extends in an inclined manner between the transmission means (2) and the propulsion means (4).

Abstract: The present invention concerns a method for sharpening a worn removable machining tip (3) and the corresponding sharpened tip. The tip having a first cutting edge (7) damaged after a first use (u1), said tip having, in the state prior to the use of same, specific dimensional and geometrical parameters within a defined tolerance range and said first undamaged cutting edge (7) having a defined sharpness, the method involves sharpening the cutting face (9) by removing material from said cutting face on said first damaged edge (7), in order to make said tip (3) match said specific dimensional and geometrical parameters within said defined tolerance range, having a second cutting edge (7?) of said defined sharpness.

Abstract: The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising:—a step of producing a blank from at least two parts (50, 51), at least one of which is a solid part, the at least two parts being assembled by a diffusion connection technique and without melting, and—a step of machining this blank in order to produce a blade with a defined profile.

Abstract: A cylinder head, an element and a base plate of a longitudinal piston engine having a cylinder head body and a base plate comprising at least one element, the base plate being interposed between a combustion chamber and the cylinder head body, comprising an upper face facing the cylinder head body and an opposing lower face arranged to face the combustion chamber and being attached to the cylinder head body, the cylinder head body being made from a material with a mass density and hardness that are less than those of the material constituting the base plate. The base plate and the body are assembled by screws for fastening the base plate to the cylinder head that are located towards the periphery of the base plate and of the body and by at least one part for fastening the cylinder head to the base plate including a threaded end designed to be engaged in a corresponding orifice of the base plate, said orifice being located closer to the center of the base plate than the fastening screws.

Abstract: The present invention relates to a set (1) of plates (2, 3; 12, 13; 21, 22; 41) or parts obtained by cutting a block (4, 4?, 4??, 35) of metal or composite material extending around a plane (5) comprising a first plate (2, 12, 21, 41) or part having an upper face (7, 33) and is second plate (3, 13, 22) or part having a lower face (8). The upper face (7, 33) of the first plate (2, 12, 21, 41) or part has a surface (7, 330) having at least two lines of inflection or changing slope with respect to said plane (5), and the lower face (8) of the second plate (3, 13, 22) or part has a surface (8) with a shape complementary to the upper face (7, 33) of the opposite first plate (2, 12, 21, 41) at a more or less constant height, corresponding to the height of the cutting line (34) in the block (4,35).

Abstract: The present invention relates to a multi-material rotary cutting tool (1) and a method for manufacturing such a tool that includes at least one continuous or substantially continuous cutting edge (8, 9) made of at least two different successive materials. The extremity or top (10) of the tool is a point off-centered in relation to the axis of rotation (5) of the tool.

Abstract: A cylinder head, an element and a base plate of a longitudinal piston engine having a cylinder head body and a base plate comprising at least one element, the base plate being interposed between a combustion chamber and the cylinder head body, comprising an upper face facing the cylinder head body and an opposing lower face arranged to face the combustion chamber and being attached to the cylinder head body, the cylinder head body being made from a material with a mass density and hardness that are less than those of the material constituting the base plate. The base plate and the body are assembled by screws for fastening the base plate to the cylinder head that are located towards the periphery of the base plate and of the body and by at least one part for fastening the cylinder head to the base plate including a threaded end designed to be engaged in a corresponding orifice of the base plate, said orifice being located closer to the center of the base plate than the fastening screws.

Abstract: The present invention relates to a method and device for manufacturing turbine blades (5; 7; 28; 33) made of a metal alloy. Starting with an aluminium and titanium alloy bar (10; 34) having a simple and/or axisymmetric shape, at least two mutually interlocking blanks (2; 3; 4; 8; 11) are produced in the bar (10; 34) by waterjet cutting (16), and then each one of said blanks (2; 3; 4; 8; 11) thus obtained is machined separately in order to obtain the blades (5; 7; 28; 33) having a final profile.