Abstract: A device that measures turbomachine aerodynamic flow parameters is presented. The device includes the information collection elements relating to the flow parameters, and a body that includes the information collection elements. The body features a portion that is elongated in the longitudinal direction and configured to form the leading edge of a turbomachine vane, and a first side portion that laterally extends portion in an axial direction, wherein the information collection elements protrude from the leading edge of the portion and the portion includes internal channels that route the information and individually communicate with at least one information collection elements, wherein the first side portion features a first surface configured to fit, at least partially, onto a second surface of an intrados or extrados wall of a turbomachine vane.

Abstract: A method for generating a three-dimensional (3D) computer model of an assembly that includes wiring routing, which includes creating a part data structure that defines a part in a virtual product management system. The part data structure includes a plurality of nodes that define at least 3D part design data, 3D wiring routing design data and wiring routing annotation data of the part. The method includes importing at least the 3D part design data, the 3D wiring routing design data and the wiring routing annotation data to the part data structure from a computer-aided design (CAD) model system and generating a 3D computer model of the assembly. The method also includes transmitting the 3D computer model of the assembly to an electronic end user device.

Abstract: A device that measures turbomachine aerodynamic flow parameters is presented. The device includes the information collection elements relating to the flow parameters, and a body that includes the information collection elements. The body features a portion that is elongated in the longitudinal direction and configured to form the leading edge of a turbomachine vane, and a first side portion that laterally extends portion in an axial direction, wherein the information collection elements protrude from the leading edge of the portion and the portion includes internal channels that route the information and individually communicate with at least one information collection elements, wherein the first side portion features a first surface configured to fit, at least partially, onto a second surface of an intrados or extrados wall of a turbomachine vane.

Abstract: The invention relates to an instrumented airfoil for mounting in a flow passage through a turbine, compressor, or module of a turbine engine. An instrumentation member is attached to an airfoil and includes information-obtaining means received in a cutout formed in the airfoil and projecting relative to the leading edge or the trailing edge. According to the invention, the instrumentation member also comprises a holder portion that is united with the information-obtaining means and that is attached to the cutout in such a manner that its surface is in alignment respectively with the suction side wall, the pressure side wall, and the leading edge or the trailing edge of the airfoil, the transitions between these respective surfaces not presenting any setbacks.

Abstract: A method for generating a three-dimensional (3D) computer model of an assembly that includes wiring routing, which includes creating a part data structure that defines a part in a virtual product management system. The part data structure includes a plurality of nodes that define at least 3D part design data, 3D wiring routing design data and wiring routing annotation data of the part. The method includes importing at least the 3D part design data, the 3D wiring routing design data and the wiring routing annotation data to the part data structure from a computer-aided design (CAD) model system and generating a 3D computer model of the assembly. The method also includes transmitting the 3D computer model of the assembly to an electronic end user device.

Abstract: A vane intended to be mounted in a supply fluid pattern, includes a blade delimited in a lateral direction by an outer surface, the blade housing a data routing channel and having a groove leading to the outer surface and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending there through. The data collecting means include one of an inserted tube and a cable, and the groove is formed in one of the outer surface opposite that whereto the inserted tube and the cable leads, and the blade that includes an orifice passing therethrough the outer surface.

Abstract: A vane intended to be mounted in a supply fluid pattern, the vane comprising: a blade delimited in a lateral direction by an outer surface having an upper surface and an lower surface which are joined at ends, so as to form there a leading edge and a trailing edge respectively, the blade housing a channel for routing data and having a groove leading to at least one of the upper surface and lower surface walls and which communicates with the data routing channel, and data collecting means for collecting data on one of the outer surface of the blade and the close vicinity thereof, the data collecting means being connected, through the groove, to the data routing channel, or extending therethrough, wherein the data collecting means comprises one of an inserted tube and a cable, and the groove is formed in one of the upper surface and lower surface wall opposite that whereto said one of the tube and the cable leads, and the blade is gone through by an orifice provided between the upper surface and the lower su

Abstract: The invention relates to an instrumented airfoil for mounting in a flow passage through a turbine, compressor, or module of a turbine engine. An instrumentation member is attached to an airfoil and includes information-obtaining means received in a cutout formed in the airfoil and projecting relative to the leading edge or the trailing edge. According to the invention, the instrumentation member also comprises a holder portion that is united with the information-obtaining means and that is attached to the cutout in such a manner that its surface is in alignment respectively with the suction side wall, the pressure side wall, and the leading edge or the trailing edge of the airfoil, the transitions between these respective surfaces not presenting any setbacks.