Abstract: The invention relates to a guide vane for a twin-spool aircraft turbomachine, of which the aerodynamic part (32) comprises an internal lubricant cooling passage (50a) extending along a principal lubricant flow direction (52a). According to the invention, the aerodynamic part is made in a single piece and also comprises heat transfer fins (80a, 80b) arranged in the passage (50a) connecting the intrados and extrados walls (70, 72) and extending approximately parallel to the direction (52a), these fins being distributed in successive rows along the principal direction (52a) and made such that for two rows (R1, R2) of staggered directly consecutive fins, the row (R1) comprises fins (80a) forming a positive acute angle A1 with a dummy reference plane (Pf), while the row (R2) comprises fins (80b) forming a negative acute angle A2 with this plane (Pf).

Abstract: The invention relates to a guide vane intended to be mounted in a turbine engine between an inner shroud (17) and an outer shroud (16), comprising a longitudinal straightening body (41) for an air flow extending between a first end (42) intended to be positioned at the inner shroud (17) and a second end (44) intended to be positioned at the outer shroud (16), the longitudinal straightening body having an aerodynamic profile defined by a leading edge (41a) and a trailing edge (41b) in the flow direction of the air flow, and by a camber line (41c) extending from the leading edge (41a) to the trailing edge (41b).

Abstract: A support structure suitable for interposing between the engine and the nacelle of an aeroengine and suitable for being fastened on an intermediate casing is provided. The structure includes a shroud having a plurality of sectors, a plurality of radial arms each installed between two adjacent shroud sectors, and a plurality of fasteners for fastening the plurality of shroud sectors to the plurality of radial arms. The shroud sectors and radial arms form a skeleton for transmitting structural forces within the intermediate casing. The structure includes non-structural fairings mounted on the skeleton and suitable for reconstituting the airflow passage. Each of the shroud sectors and radial arms is formed by a metal frame without mechanical discontinuity, each shroud sector metal frame defining at least one opening that is closed by a cover and each radial arm metal frame defining at least one orifice for receiving a closure plate.

Abstract: This multi-user processor system for processing information, of the type including a data exchange engine (3) associated with multiple users (1) of shared resources (2), is characterized in that it includes means (4) for controlling data exchange in the processor, associated with each user, the exchange engine and the shared resources, in order to authorize transactions or not and in that the engine includes means (5) for breaking down authorized transactions into elementary sub-transactions, means (6) for interlacing the sub-transactions obtained from the breaking down of the authorized transactions of several users and the means (6) for distributing these interlaced sub-transactions among the different resources.

Abstract: Embodiments herein are directed to moisturizing compositions comprising interpenetrating polymer networks, methods of making moisturizing compositions and methods of using moisturizing compositions.

Abstract: Variable displacement systems, utilizing a phase relationship controller to determine and control the volumetric displacement of liquid and gas compression systems, including applications of said systems to continuously variable, constant speed power transmissions and to variable compression-ratio internal combustion engines.

Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).

Abstract: The compositions of the various embodiments include benzoyl peroxide and Hest G-18-0. The methods of this invention include treating acne, increasing the solubility of benzoyl peroxide, and treating the skin. Embodiments are also directed to a dual chamber package comprising a chamber for benzoyl peroxide and a chamber for Hest G-18-0.

Abstract: A data collection device (100) is described which monitors the environmental conditions and the operations of a medical device (10). The data collection device may be arranged to communicate wirelessly via a cloud computing environment with a central computer (210). The central computer compares the reported use data with a preventive maintenance model to predict when or how the medical device will fail. In addition, the central computer may integrate reports from many data collection devices operating in various environments for the purpose of analyzing and improving the predictive maintenance model.

Abstract: A closer for an attachment orifice of an OGV in a turbine engine, the vane having a blade fixed to a root provided with attachment orifices, the closer including a cup adapted to be fixed in the attachment orifice of an OGV; a cylindrical shaped plug engaging in the cup, the plug including an upper face inclined relative to the ground plane of the plug; a guide adapted to position the plug on the cup by rotation into a working position, in which the upper face of the plug coincides with the surface level of the vane root; a blocking system to block the plug in the working position.

Abstract: A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.

Abstract: A vaned wheel device traversed by a radial drive shaft includes radial arms, one of which contains the shaft, and stationary vanes manufactured separately from the casing and a ferrule and assembled thereto. A sleeve encompassing the shaft traverses the casing and serves to support a bearing for supporting the shaft with positional accuracy, and maintaining tightness by forming a single cavity with the radial arm cavities traversing the shaft.

Abstract: A method comprises controlling an operating pressure of a fluid from a borehole. The fluid comprises solids and entrained gas. The method further comprises removing at least a portion of the entrained gas from the fluid at an upstream location. The method further comprises removing residual entrained gas from the fluid at a downstream location. The method further comprises separating at least a portion of the solids from the fluid. The method further comprises circulating the separated fluid back to the borehole. Separating of solids occurs after the removing of entrained gases from the fluid at the downstream location.

Abstract: A transmission system for avionics application data is disclosed. In one aspect, the system is for transmitting avionics application data between data producing means and data consuming means, the application data being transmitted in the form of data transmission units, each including: at least one portion of an application message, and an additional message containing identification and control information. The additional message includes: an identification sequence including a static part making it possible to identify the application message and its source and a variable part making it possible to distinguish the message in a unique manner, and a control sequence designed to check the integrity of the application message and based on a sequence representing a cyclic redundancy control code of the concatenation of at least one portion of the application message corresponding to said unit, with the identification sequence.

Abstract: The invention relates to a guide vane (24) for a dual flow aircraft turbine engine, the aerodynamic part (32) of the vane comprising an inner duct (50a) for lubricant cooling extending in a main direction (52a) and being partly bounded by a pressure side wall (70) and a suction side wall (72) of the vane. According to the invention, the aerodynamic part (32) of the vane is embodied from as a single piece, including also the heat transfer fins (80), arranged in the duct (50a) expanding substantially parallel to the direction (52a), the fins (80) being spaced from each other depending on the direction (52a) as well as a transversal direction (60) of the vane, so that at least some of the fins (80) are arranged substantially staggered.

Abstract: This system for transmitting avionic information of the type including means for transmitting data frames through at least one transmission network based on avionic switches, intended for corresponding receiving means. The system further includes means for determining the crossing time by at least some of the data frames of at least some of the switches and means on the network for transmitting a corresponding crossing time information frame associated with this data frame, intended for corresponding receiving means.

Abstract: A critical data transmission architecture in avionics systems is disclosed. The system includes a module of production, a module of consumption, and at least one physical pathway linking the module of production to the module of consumption. The module of production is configured to transmit each critical datum by at least two data, one of a first independent type and one of a second independent type that cannot interfere with one another. Each datum of the first type or the second type is transmitted in the form of a data transmission unit including a portion of an application message and a message. The additional message of each transmission unit includes a verification sequence and each datum of the first type and the second type is transmitted by the same physical pathway and is generated by different module of generation.

Abstract: This switched data transmission system, particularly for use in avionics applications, of the type comprising a plurality of electronic devices and equipment units adapted for transmitting discrete messages over a transmission network, and in which each of the devices and equipment units is connected to a network switch, the switches being connected to each other by means of data transmission links so as to form a physical topology of a loop network, each message being associated with information regarding data flow priority in the network comprising of functional priority information, is characterized in that each message is also associated with information regarding temporal priority of data flow in the network.

Abstract: This switched data transmission system, that may be used in particular in avionics applications, of the type comprising a plurality of electronic devices and equipment units adapted for transmitting discrete messages over a transmission network, and in which each of the equipment units is connected to a network switch, the switches being connected to each other by means of data transmission links so as to form a physical topology of a loop network, each message being associated with information regarding data flow priority in the network comprising of functional priority information, is characterized in that each message is also associated with information regarding topological priority of data flow in the network.

Abstract: A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.