Abstract: A method for creating a metal reinforcement for a leading or trailing edge of a turbine engine blade including a reinforcement foot and head, the method including: creating a plurality of V-shaped tapered elements that form different parts of the metal reinforcement so that the metal reinforcement is divided into a plurality of parts distributed between the foot and the head; positioning the parts on equipment that is shaped like the leading or trailing edge of the turbine engine blade; and rigidly connecting the different parts so as to form the complete profile of the one-piece metal reinforcement the by recombining the different parts.

Abstract: Methods and systems for constraining surface consistent amplitude corrections are described. An amplitude map generated from pre-stack or post-stack seismic data can constrain, through the bin term, the surface consistent inversion. The methods and systems provide a solution to correct for wavelength and regional anomalies associated with heterogeneous near surface or buried velocity variations above the target horizon. The methods and systems can be used for 2D, 3D, 4D surveys or for a merge of different surveys.

Abstract: A forming tooling including a fixed part and a moving part set in action by a one-way press, in a first direction, the tooling varying between an open position and a closed position in which the moving part applies pressure to the fixed part; the moving part including moving dies capable of starting to deform the metal workpiece through a translational movement of the dies in a second direction simultaneous with the translational movement of the dies in the first direction during closure of the tooling, the moving dies being capable of moving away from the metal workpiece through a reverse translational movement of the moving dies, in the second direction, simultaneously with the translational movement of the moving dies in the first direction during opening of the tooling.

Abstract: A method for making a metal reinforcement for the leading edge or trailing edge of the blade of a turbine engine that includes making a metal insert defining the base of the metal reinforcement; positioning the metal insert at the end of a blank of a shaping tool, the blank repeating the shape of the turbine-engine blade; shaping a planar metal sheet on the metal insert and the blank of the shaping tool using a superplastic hot-shaping method.

Abstract: A method for creating a metal reinforcement for a leading or trailing edge of a turbine engine blade including a reinforcement foot and head, the method including: creating a plurality of V-shaped tapered elements that form different parts of the metal reinforcement so that the metal reinforcement is divided into a plurality of parts distributed between the foot and the head; positioning the parts on equipment that is shaped like the leading or trailing edge of the turbine engine blade; and rigidly connecting the different parts so as to form the complete profile of the one-piece metal reinforcement the by recombining the different parts.

Abstract: A method for making a metal reinforcement for the leading edge or trailing edge of a turbine engine blade, including: positioning a preform using an equipment positioning the preform in a position such that the preform, at one end thereof, has an area which is capable of receiving a filler metal; and, after the positioning, constructing a base for the metal reinforcement by hard-surfacing with filler metal in the area, in the form of metal beads.

Abstract: The invention relates to a method of manufacturing a composite turbomachine blade, the method comprising the following steps: a) making a preform by three-dimensionally weaving yarns including tracer yarns disposed at least at the surface of the preform; b) cutting out said preform so as to leave intact a series of tracer yarns situated along a reference face of the preform; c) pre-deforming said cut-out preform; d) compacting and stiffening said pre-deformed preform; e) providing an injection mold in which said stiffened preform is placed; f) heating said injection mold; g) injecting a binder into said injection mold, the binder comprising a thermosettable resin; and h) extracting from the mold a composite molded part presenting substantially the shape and the dimensions of said blade. The invention is applicable to a making fan blade.

Abstract: Method of manufacturing a hollow blade (1) for a turbomachine in which the blade (1) is made from a preform (14) obtained from external primary parts (28, 30). In order to reduce costs, the root part (2) of the blade is formed from spare material (34) entirely located on only one of the two external primary parts of the preform (14).