Abstract: A hybrid heart valve prosthesis that can be quickly and easily implanted during a surgical procedure is provided. The hybrid heart valve includes a substantially non-expandable, non-compressible prosthetic valve member having a peripheral sealing ring and an expandable stent frame projecting from an inflow end, thereby enabling attachment to the annulus without sutures. The stent frame may be plastically-expandable and may have a thin fabric layer covering its entirety as well as secondary sealing structures around its periphery to prevent paravalvular leaking. Other sealing solutions include interactive steps at the time of valve implant to establish seals around the stent and especially between the stent and the sealing ring of the valve member.

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, 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 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: Geolocation is performed by receiving, at a plurality of non-earthbound platforms each moving in a known manner within a spatial coordinate system, a radio frequency (RF) signal transmitted from a transmitter at an unknown location on earth within the spatial coordinate system. For each of the platforms, a phase change of the received frequency carrier is measured over the same duration of time. The measured phase changes are combined to determine the transmitter location.

Abstract: An unknown location of a transmitter of interest is determined based on wireless signals transmitted by both the transmitter of interest and a reference transmitter positioned at a known location. The transmitted signals are received at a plurality of non-earthbound platforms each moving in a known manner, and phase measurements for each received signal are used to determine the unknown location.

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.