Abstract: Method for manufacturing a blade made of a composite material for a turbomachine, in particular of an aircraft, including steps of: a) arranging a preform produced by three-dimensional weaving of fibres within a mould, a polymerisable adhesive being inserted between a shield and an edge of the preform, b) closing and heating the mould, then injecting the polymerisable resin into the mould, wherein the mould is heated according to a cycle including increases in temperature from T1 to T2, then from T2 to T3, and in that the resin is injected in step b) during or just before the increase in temperature from T2 to T3, the temperature T2 being selected so that the viscosity of the adhesive is greater than the viscosity of the resin.

Abstract: A touch sensor panel includes a first set of touch electrodes configured to operate as drive lines and that are disposed in a first layer of the touch sensor panel. The touch sensor panel also includes a second set of touch electrodes configured to operate as sense lines and that are disposed in a second layer of the touch sensor panel, different than the first layer of the touch sensor panel, such that one or more mutual capacitance touch nodes are formed by the first set of touch electrodes and the second set of touch electrodes. The touch sensor panel also includes a third set of touch electrodes configured to operate as self-capacitance electrodes and that are disposed in the first layer or the second layer of the touch sensor panel.

Abstract: Techniques for sending commands to a container agent of a confidential virtual machine (VM) are disclosed. An example method includes sending a first command from a computing device to a container agent of a confidential VM running on a host computing system. The first command is sent to the container agent through a control plane of the host computing system and causes the container agent to communicate with a relying party to verify confidentiality of the confidential VM. The method also includes receiving network information for the container agent from the relying party and establishing a network connection with the container agent based on the network information received from the relying party. The method also includes sending a second command from the computing device to the container agent of the confidential VM via the network connection.

Abstract: Techniques for sending commands to a container agent of a confidential virtual machine (VM) are disclosed. An example method includes establishing a first network connection with a control plane of a host computing system and establishing a second network connection with a container agent of a confidential virtual machine (VM) running on the host computing system, wherein the second network connection bypasses the control plane of the host computing system. The method also includes receiving a command from a tenant user interface (UI) and processing the command to determine a command type. The method also includes based on the command type, sending by a processing device, the command to the control plane via the first network connection or to the container agent via the second network connection.

Abstract: A virtual machine (VM)-based container runtime executing on a computing device receives a request to run a container from a container image that is at least partially encrypted. The VM-based container runtime causes a VM to be initiated from a VM image, the VM image including an agent operable to, during execution, obtain a plurality of decryption keys operable to decrypt blocks of the container image. The agent is operable to set up a block remapper in the VM to be invoked by a file system mounted to the VM to request a particular container image block, send a request for the particular container image block to a block obtainer component executing outside of the VM, utilize a decryption key to decrypt a container image block received from the block obtainer component to generate a decrypted container image block, and pass the decrypted container image block to the file system.

Abstract: A water detection and measurement system for a resource extraction system includes a controller configured to receive first sensor signal(s) indicative of a pressure of a multiphase fluid and second sensor signal(s) indicative of a temperature of the multiphase fluid. Furthermore, the controller is configured to determine a fraction of condensed water within the multiphase fluid based on the pressure and the temperature. The controller is also configured to determine a flow rate of the condensed water based on the fraction of the condensed water within the multiphase fluid and a gas flow rate of the multiphase fluid. In addition, the controller is configured to receive third sensor signal(s) indicative of a fluid parameter of the multiphase fluid, and the controller is configured to determine a flow rate of formation water within the multiphase fluid based on the fluid parameter and the flow rate of the condensed water.

Abstract: A water detection and measurement system for a resource extraction system includes a controller configured to receive first sensor signal(s) indicative of a pressure of a multiphase fluid and second sensor signal(s) indicative of a temperature of the multiphase fluid. Furthermore, the controller is configured to determine a fraction of condensed water within the multiphase fluid based on the pressure and the temperature. The controller is also configured to determine a flow rate of the condensed water based on the fraction of the condensed water within the multiphase fluid and a gas flow rate of the multiphase fluid. In addition, the controller is configured to receive third sensor signal(s) indicative of a fluid parameter of the multiphase fluid, and the controller is configured to determine a flow rate of formation water within the multiphase fluid based on the fluid parameter and the flow rate of the condensed water.

Abstract: A water detection and measurement system for a resource extraction system includes a controller configured to receive first sensor signal(s) indicative of a pressure of a multiphase fluid and second sensor signal(s) indicative of a temperature of the multiphase fluid. Furthermore, the controller is configured to determine a fraction of condensed water within the multiphase fluid based on the pressure and the temperature. The controller is also configured to determine a flow rate of the condensed water based on the fraction of the condensed water within the multiphase fluid and a gas flow rate of the multiphase fluid. In addition, the controller is configured to receive third sensor signal(s) indicative of a fluid parameter of the multiphase fluid, and the controller is configured to determine a flow rate of formation water within the multiphase fluid based on the fluid parameter and the flow rate of the condensed water.

Abstract: The invention relates to an assembly for a turbomachine (1) extending about an axis (X) comprising: —an inner annular platform (13) and an outer annular platform (14) delimiting a flow channel (3) for a flow flowing from upstream to downstream, and —at least one fixed blade (12) extending radially between the inner annular platform (13) and the outer annular platform (14), said fixed blade (12) being profiled with a leading edge (15), characterized in that the inner annular platform (13) and/or the outer annular platform (14) comprises, upstream of the leading edge (15) of the fixed blade (12), a furrow (21) for channeling the fluid flowing in the channel (3), having a segment forming an upstream limit (22) and a segment forming a downstream limit (23), the length of the upstream limit (22) being greater than the length of the downstream limit (23).

Abstract: A method for extracting at least one foreign body lodged within a blade of a high-pressure distributor of a turbojet engine, the high-pressure distributor including hollow fixed blades between two annular shrouds forming a gas flow path, each blade being coated with a thermal barrier and provided with at least one recess at least partially obstructed by a first soldered closing plate, includes the following operations: cutting off the first closing plate, extracting the foreign body from the recess, carrying out an endoscopic inspection of an internal space of the recess in order to verify that no foreign body remains, positioning a second closing plate on the recess, and soldering the second closing plate directly onto the distributor with the blades coated with the thermal barrier.

Abstract: A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.

Abstract: A method for extracting at least one foreign body lodged within a blade of a high-pressure distributor of a turbojet engine, the high-pressure distributor including hollow fixed blades between two annular shrouds forming a gas flow path, each blade being coated with a thermal barrier and provided with at least one recess at least partially obstructed by a first soldered closing plate, includes the following operations: cutting off the first closing plate, extracting the foreign body from the recess, carrying out an endoscopic inspection of an internal space of the recess in order to verify that no foreign body remains, positioning a second closing plate on the recess, and soldering the second closing plate directly onto the distributor with the blades coated with the thermal barrier.

Abstract: The invention relates to an assembly for a turbomachine (1) extending about an axis (X) comprising: —an inner annular platform (13) and an outer annular platform (14) delimiting a flow channel (3) for a flow flowing from upstream to downstream, and —at least one fixed blade (12) extending radially between the inner annular platform (13) and the outer annular platform (14), said fixed blade (12) being profiled with a leading edge (15), characterized in that the inner annular platform (13) and/or the outer annular platform (14) comprises, upstream of the leading edge (15) of the fixed blade (12), a furrow (21) for channeling the fluid flowing in the channel (3), having a segment forming an upstream limit (22) and a segment forming a downstream limit (23), the length of the upstream limit (22) being greater than the length of the downstream limit (23).

Abstract: The proposed invention is an airflow straightening assembly for a turbine engine comprising: —a cylindrical platform (15) centered on an axis (X-X), —at least one straightener blade (20) extending from the platform, —a structural unit (30) extending radially relative to the axis, and —a mechanical member (40) protruding from the platform (15), said mechanical member (40) being one of the group comprising: —a radial shaft, —an angle transmission box of a radial shaft, —an electric, hydraulic or pneumatic connection element, —an intermediate gear driving a radial shaft, the straightening assembly further comprising a fairing (50) or the protruding mechanical member, the fairing having a three-dimensional surface defined by: —at least one upstream end point (Ai, Ae) located axially upstream from the mechanical member (40) relative to the direction of air flow in the turbine engine, and —at least one downstream end point (Ci, Ce) located axially downstream from the mechanical member, the three-dimensional surface

Abstract: A turbomachine component or collection of components includes a first blade and a second blade and a platform from which the blades extend. The platform, between the pressure face of the first blade and the suction face of the second blade, has a non-axisymmetric surface defining a plurality of fins of substantially triangular section extending downstream of a leading edge of each of the blades. Each fin is associated with a leading position and a trailing position on the surface, between which positions the fin extends, such that the leading position is situated at between 5% and 35% length relative to a chord of the blade extending from a leading edge to a trailing edge of the blade. The further a fin is from the suction face of the second blade, the further the leading position of the fin is axially from the leading edge of the blades.

Abstract: The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm (30) comprises: an upstream end (31) having a guide vane profile (21) and comprising a leading edge (32) aligned with that of the vane; and a shoulder (35) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterized in that the area (Aneck) of the section of the channel at the neck is between 0.7 and 0.9 times the area (Ainlet) of the section of the channel at the leading edges.

Abstract: A portable lamp, such as a headlamp, comprising wireless bidirectional communication means for exchanging configuration instructions, parameters and/or data with at least one mobile information processing system. This mobile processing system establishes a downlink for the transmission of said configuration instructions, parameters and/or data to the lamp. The lamp can establish an uplink for the transmission of configuration instructions, parameters and/or data from the lamp to said mobile information processing system.

Abstract: The proposed invention is an air-flow straightening assembly for a turbine engine comprising:—a cylindrical platform (15) centred on an axis (X-X),—at least one straightener blade (20) extending from the platform,—a structural arm (30) extending radially relative to the axis, and—a mechanical member (40) protruding from the platform (15), said mechanical member (40) being one of the group comprising:—a radial shaft,—an angle transmission box of a radial shaft,—an electric, hydraulic or pneumatic connection element,—an intermediate gear driving a radial shaft, the straightening assembly further comprising a fairing (50) of the protruding mechanical member, the fairing having a three-dimensional surface defined by:—at least one upstream end pont (Ai, Ae) located axially upstream from the mechanical member (40) relative to the direction of air flow in the turbine engine, and—at least one downstream end point (Ci, Ce) located axially downstream from the mechanical member, the three-dimensional surface being tange

Abstract: A headlamp with a light source, an electrical power source and several states controlling power sources and light beams is presented. The first state corresponds to at least one activated state in which the electrical power source is coupled to a light source to generate a light beam. The second state corresponds to a deactivated state where the electrical power source is not coupled to a light source and no light beam is generated. The third state corresponds to a locked state in which the electrical power source is not coupled to a light source and no light beam is generated; Also included is a switching mechanism to receive a first and a second physical user input through one switching element. A processor is coupled to the switching mechanism and is used to select one among the first, second and third states in response to the physical user inputs.

Abstract: A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point ±1 degree.