The invention relates to a guide vane intended to be arranged in all or part of an air flow of an aircraft bypass turbomachine fan, the vane comprising an aerodynamic part equipped with at least one interior lubricant cooling passage delimited in part by an intrados wall and an extrados wall of the vane, there being flow-disturbing lugs, made as one piece with one of the intrados and extrados walls, passing across the passage. According to the invention, in any plane of section passing orthogonally through the lugs, the space defined between these lugs has a geometry defined exclusively by a set of annulus shapes of the same dimensions, partially overlapping one another and each in part delimiting at least two of these lugs.

The invention relates to a device (1) for drilling holes in the axial and radial direction of a blade root of a wind turbine, wherein the device comprises: a first base (2), which is to be stationary positioned on the ground; a second base (3), which is moveably mounted to the first base (2) and movable along a first direction; first drive means for positioning the second base (3) along the first direction; a rotary arm (4), which is pivotally mounted to the second base (3) around a main axis (5); second drive means for rotating the rotary arm (4) around the main axis (5); wherein the rotary arm (4) comprises a guide track (7) which extends from a first outer end to a second outer end of the rotary arm (4) thereby passing the main axis (5); first drilling means (8) moveably arranged on the guide track (7), comprising a first drilling tool (8-1) for drilling holes in a second direction (8-2), which second direction (8-2) is perpendicular to the main axis (5) andthird drive means for positioning the first drilling means (8) along the guide track (7); second drilling means (9) mounted on the rotary arm (4), comprising a second drilling tool for drilling holes in a third direction (9-2), which third direction (9-2) is parallel to the main axis (5).

The invention relates to a method and an arrangement for introducing boreholes into a surface of a workpiece (W) mounted in a stationary manner using a boring tool which is attached to the end face of an articulated-arm robot (KR) and which can be spatially positioned by said robot. The method has the following method steps: positioning the articulated-arm robot-guided boring tool at a spatial position which lies opposite a specified machining location on the workpiece surface at a specified distance therefrom, producing a rigid mechanical connection which supports the end face of the articulated-arm robot (KR) on the workpiece and which can be released from the workpiece surface, and machining the surface by moving the boring tool towards the machining location and subsequently engaging the boring tool with the workpiece (W) at the machining location on the workpiece surface while the end face of the articulated-arm robot (KR) is connected to the workpiece. The invention is characterized by the combination of the following method steps: the boring tool is moved towards the workpiece (W) by means of an NC advancing unit attached to the end face of the articulated-arm robot (KR), the boring process is monitored on the basis of information obtained using a sensor system which detects the position of the boring tool relative to the workpiece surface and which is attached to the end face of the articulated-arm robot (KR), and the boring process is terminated upon reaching a specified boring depth.

A miniaturized turbogenerator (200) to directly provide electrical propulsion (307 308, 309) to small land, air, and maritime vehicles without an intervening electricity storage battery (315). The invention comprises of a process of miniaturization (500) of a turbine engine core (100), in particular its compressors and turbines (400), by means of hyper-feed machining by linear force alone, i.e. without rotation of either the workpiece or the cutting tool (505), and a resulting apparatus of a miniaturized turbogenerator (200) that has sufficient power density to provide high-performance electrical propulsion (310) for commercially feasible automobiles, urban air mobility vehicles, and other small vehicles and vessels with greater performance than battery-electric vehicles (300).

The invention relates to a device (1) for drilling holes in the axial and radial direction of a blade root of a wind turbine, wherein the device comprises:a first base (2), which is to be stationary positioned on the ground;a second base (3), which is moveably mounted to the first base (2) and movable along a first direction;first drive means for positioning the second base (3) along the first direction;a rotary arm (4), which is pivotally mounted to the second base (3) around a main axis (5);second drive means for rotating the rotary arm (4) around the main axis (5);wherein the rotary arm (4) comprises a guide track (7) which extends from a first outer end to a second outer end of the rotary arm (4) thereby passing the main axis (5);first drilling means (8) moveably arranged on the guide track (7), comprising a first drilling tool (8-1) for drilling holes in a second direction (8-2), which second direction (8-2) is perpendicular to the main axis (5) andthird drive means for positioning the first drilling means (8) along the guide track (7);second drilling means (9) mounted on the rotary arm (4), comprising a second drilling tool for drilling holes in a third direction (9-2), which third direction (9-2) is parallel to the main axis (5).

Disclosed techniques include creating a pressure differential within an interior of a dual-wall component relative to pressure at an exterior of the dual-wall component, fabricating a hole in a first wall of the dual-wall component, while fabricating the hole in the first wall of the dual-wall component, acoustically monitoring the hole fabrication, while acoustically monitoring the hole fabrication, detecting breakthrough of the first wall of the dual-wall component based on an acoustic signal due to gas passing through the fabricated hole, and based on the acoustic signal, ceasing the fabrication of the hole.

A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.

A method for processing a CMC airfoil includes nesting an airfoil fiber preform in a cavity of a fixture that has first and second tool segments, closing the fixture by rotating a first tool segment about a hinge, the closing causing the tool segments to clamp on a tail portion of the fiber preform and thereby conform the tail portion to the fixture. While in the fixture, the fiber preform is then partially densified with an interface coating material to form a partially densified fiber preform. While still in the fixture, one or more cooling holes are drilled into the trailing edge of the partially densified fiber preform. After the drilling, the partially densified fiber preform is removed from the fixture and further densified with a ceramic matrix material to form a fully densified CMC airfoil.

A method for producing one or more cooling holes in an airfoil for a gas turbine engine is disclosed. The method includes casting one or more hole starter bosses on a suction side, a pressure side, or both of the airfoil, drilling the one or more cooling holes into the airfoil by way of the one or more hole starter bosses, and removing the one or more hole starter bosses after drilling the one or more cooling holes into the airfoil.