Abstract: A leading-edge shield for a turbomachine blade includes a pressure-side wing and a suction-side wing. Both the pressure-side wing and suction-side wing extend heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge. They are connected together via the leading edge. The rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).

Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).

Abstract: A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, the method comprising the following steps: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the value ap of the parameter a of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of said part and obtaining the value ap/ref of the parameter a of the CIELAB colorimetric space; c) calculating ?ap=ap?ap/ref; and d) establishing a risk of heating said determined zone to be tested if ?ap is higher than a threshold value A1.

Abstract: A method for the non-destructive testing of the heating of a part made from polymer material, the method comprising the following steps: a) carrying out a measurement by infrared spectroscopy on a part to be tested and extracting therefrom at least one of absorbance values and transmittance values according to a spatial frequency; and b) from the measurement of at least one of absorbance and transmittance, determining the period of time during which said region of the part to be tested has been subjected to a given heating temperature and determining said heating temperature, using a reference database comprising at least one of absorbance measurements and transmittance measurements, the measurements established over a plurality of reference samples made from polymer material that have been subjected to a given temperature during a given period of time.

Abstract: A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.

Abstract: A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, comprising: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the values ap, bp and Lp of the parameters a, b and L of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of the part and obtaining the values ap/ref, bp/ref and Lp/ref of the parameters a, b and L of the CIELAB colorimetric space; c) calculating the colour difference ?Ep between the colorimetric measurements obtained in steps a) and b); and d) from the value ?Ep, determining the time period during which said zone to be tested of the part has been subjected to a determined heating temperature, by using a reference database.

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) having a pressure-side wing (34) and a suction-side wing (36), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing (34) presenting a greater length than the suction-side wing (36) over a first segment (S1) of the leading-edge shield (32), and an equal or smaller length than the suction-side wing (36) over a second segment (S2) of the leading-edge shield (32).

Abstract: A leading-edge shield (32) for a turbomachine blade (16) includes a pressure-side wing (34) and a suction-side wing (36). Each of the wings (34, 36) extends along a height (H) from a bottom edge (50) to a top edge (51) and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing (36) and the pressure-side wing (34) presents a segment (S1), adjacent to the top edge (51) and extending over at least 10% of the height (H), wherein the rear edge (42) slopes towards the top edge (51).

Abstract: The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield (32) for a turbomachine blade (16), said leading-edge shield (32) including a pressure-side wing (34) and a suction-side wing (36). Each pressure-side wing (34) and suction-side wing (36) extends heightwise from a bottom edge (50) to a top edge (51) and lengthwise from the leading edge (18) to a rear edge (40, 42), and they are connected together via the leading edge (18), and wherein the rear edge (42) of the suction-side wing (36) presents at least one shaped segment (S1, S2) that is shaped in such a manner that the length of the suction-side wing (36) within this segment is shorter than the length (l2, l3, l21, l22, l31, l32) of the suction-side wing (36) at each end of this segment (S1, S2).

Abstract: A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, the method comprising the following steps: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the value ap of the parameter a of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of said part and obtaining the value ap/ref of the parameter a of the CIELAB colorimetric space; c) calculating ?ap=ap?ap/ref; and d) establishing a risk of heating said determined zone to be tested if ?ap is higher than a threshold value A1.

Abstract: A method for non-destructively testing the heating of a determined zone of a part made of a polymer material, comprising: a) taking at least one colorimetric measurement on said determined zone to be tested and obtaining the values ap, bp and Lp of the parameters a, b and L of the CIELAB colorimetric space; b) taking at least one colorimetric measurement on said reference zone of the part and obtaining the values ap/ref, bp/ref and Lp/ref of the parameters a, b and L of the CIELAB colorimetric space; c) calculating the colour difference ?Ep between the colorimetric measurements obtained in steps a) and b); and d) from the value ?Ep, determining the time period during which said zone to be tested of the part has been subjected to a determined heating temperature, by using a reference database.

Abstract: A method for the non-destructive testing of the heating of a part made from polymer material, the method comprising the following steps: a) carrying out a measurement by infrared spectroscopy on a part to be tested and extracting therefrom at least one of absorbance values and transmittance values according to a spatial frequency; and b) from the measurement of at least one of absorbance and transmittance, determining the period of time during which said region of the part to be tested has been subjected to a given heating temperature and determining said heating temperature, using a reference database comprising at least one of absorbance measurements and transmittance measurements, the measurements established over a plurality of reference samples made from polymer material that have been subjected to a given temperature during a given period of time.

Abstract: A turbine engine blade comprising an aerodynamic surface that extends in a first direction between a leading edge and a trailing edge, and in a second direction substantially perpendicular to the first direction between a root and a tip of the blade, and a leading-edge reinforcement comprising a fin partly covering the aerodynamic surface of the blade, characterised in that the fin has a radially outer edge arranged in the vicinity of the tip of the blade and extending between the leading edge and the trailing edge, this radially outer edge comprising an upstream point fitting flush with the tip of the blade at the leading edge and a so-called downstream point separated from the tip of the blade.

Abstract: Fabricating a blade by 3D weaving a preform that is to be impregnated with resin. The visibility of the cut ends of certain yarns of the preform, e.g. the warp yarns, is accentuated in order to cause curved lines to appear, and the configuration of these curved lines is compared with a reference configuration in order to shape the preform properly.

Abstract: Fabricating a test blade including defects for calibrating a tomography installation for verifying similar blades. A three-dimensional blank is made by weaving fibers of synthetic material and elements of resin in the solid state are inserted into predetermined locations in said blank prior to coating it in resin.

Abstract: Fabricating a blade by 3D weaving a preform that is to be impregnated with resin. According to the invention, the visibility of the cut ends of certain yarns of the preform (16), e.g. the warp yarns, is accentuated in order to cause curved lines (20) to appear, and the configuration of these curved lines is compared with a reference configuration in order to shape the preform properly.

Abstract: A test blade and a method for fabricating the test blade are presented for use in calibrating a tomography system configured to inspect turbomachine blades for defects. The test blade may include a three-dimensional fiber blank and a polymerized resin. The blank may be created by weaving synthetic material fibers. The resin may be configured to be injected into a mold as a liquid where the resin may polymerize around the fiber blank. The test blade may be configured to be modified to include particular defects such as cut fibers and/or cavity defects which are perceived by the tomography system. The dimensions of the cavity defects may be substantially created by pulling two or more fibers apart at a specific distance with a spreading tool.

Abstract: Fabricating a test blade including defects for calibrating a tomography installation for verifying similar blades. A three-dimensional blank is made by weaving fibers of synthetic material and elements of resin in the solid state are inserted into predetermined locations in said blank prior to coating it in resin.

Abstract: Fabricating a test blade including defects for calibrating a tomography installation for verifying similar blades. A three-dimensional blank is made by weaving synthetic material fibers, and cavities are created at predetermined locations in the blank before coating it in resin.