Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.

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 bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.

Abstract: A high-efficiency, stall-proof airfoil is an aircraft wing configuration whereby a motive force directly induces gaseous fluid flow across a lifting surface of the airfoil without requiring a movement of the wing through an air space. The airfoil is provided with means to control a pitch, a roll and a yaw motion and to control a position and stability of the aircraft. When not undergoing horizontal displacement, it provides highly efficient use of fuel resources, precluding the formation of drag and its incumbent power consumption. Air pressure at a bottom of the wing remains essentially ambient. Therefore, differential pressure between a lower surface of the wing and an upper surface of the wing maintains its maximum possible quantity. Virtually, all of the power consumed is utilized in a production of lift. Additionally, because lift is generated without regard to an angle-of-attack, forward speed, nor a configuration of a leading edge of the wing, the configuration is essentially stall proof.

Abstract: A vaned ring for a turbomachine stator includes an outer shell (42), a vane (46) having a vane head (52), and two platforms (60) arranged circumferentially on either side of the vane head, and fixed on a radially inner face (61) of the outer shell by means of detachable fasteners. The vane head has first conical seatings (70) bearing on respective second conical seatings (72) of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring comprises a frangible pin (73) including a base (73A) mounted on the outer shell and a head (73B) projecting radially inwards with respect to the outer shell and having a head surface (73C) forming, vis-a-vis a top surface (74) of the vane head, a stop opposing a displacement of the vane radially outwards.

Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.

Abstract: A hybrid architecture for avionics data transmission and a corresponding system are disclosed. In one aspect, the architecture includes a plurality of subscriber stations connected by a data transmission capability. The stations are connected on the one hand by a first capability for transmitting data to their neighbors to form at least a first data transmission network in a closed ring between the stations and on the other hand by a second capability for transmitting data to a capability forming a central communication plan switch to form at least one second data transmission network in a star between the stations and the capability forming the central plan switch.

Abstract: This application relates to dye-therapeutic moiety conjugates for imaging, targeting, and treating cancerous cells and/or tumors.

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.

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 guide vane for a dual flow aircraft turbine engine includes an aerodynamic part. The aerodynamic part includes 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. The aerodynamic part is embodied as a single piece, and includes heat transfer fins arranged in the duct expanding substantially parallel to a direction of the duct. The fins are spaced from each other depending on the direction of the duct and a transversal direction of the vane, so that at least some of the fins are arranged substantially staggered.

Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.

Abstract: This disclosure is directed to compositions comprised of retinaldehyde, one or more skin conditioning agents, and, optionally, one or more additional retinoids. This disclosure is directed. Embodiments are also directed to compositions comprised of retinaldehyde, one or more peptides, one or more skin conditioning agents, one or more calcium containing agents, and, optionally, one or more additional retinoids. Embodiments are also directed to compositions comprised of retinaldehyde, one or more peptides, one or more skin conditioning agents, one or more calcium containing agents, and, optionally, one or more additional retinoids. Additional embodiments disclose methods for treating the skin wherein a characteristic of the skin is improved, the characteristics include firmness, elasticity, fine lines and wrinkles, skin texture, dullness, dyschromia, skin tone, reduction or elimination of acne, and any combination thereof.

Abstract: A method is provided that includes: weaving one first portion including warp and weft threads intertwined according to the fundamental weave of each portion of woven wall corresponding to this first portion, stopping introduction of weft threads after insertion of a weft thread associated with the positioning of one elongated element having a main axis, the weft thread being intertwined with the warp threads of each portion of woven wall, introducing each elongated element between the warp threads defining with the associated weft thread, the insertion position of this elongated element, and maintaining in position each elongated element and introducing one new weft thread intertwining warp threads of the structure according to the fundamental weave of each wall portion or according to at least one new weave, to resume production of the structure, with each elongated element not being taken in the structure.

Abstract: This digital data exchange architecture includes at least one communication network having at least one communication plane, a plurality of pieces of subscriber electronic equipment, and several switches. Each switch includes means forming a time referencing server able to: generate a local current time reference; transmit this local current time reference generated on the corresponding communication plane via a frame; receive via one or several frames the current time references generated by at least some of the switches of the corresponding communication plane; analyze the received current time references, in order to generate a local following time reference according to a predetermined generation law; and associate the local following time reference with the local current time reference.

Abstract: The present invention relates to a method that may be used in a digital data communication system comprising a communication network constituted of a plurality of nodes, and a plurality of subscriber equipment units each connected to a node, includes: a transmission phase (P1) including the steps of limiting of the size of each frame to be transmitted, adding identification-authentication credentials, and transmitting the frames with a predetermined transmission interval; and a transmission phase (P2) including the steps of monitoring-checking for compliance with the input conditions; removal of each frame that is non-compliant, replicating each frame that is compliant, monitoring-checking for compliance with the output conditions, removing each frame that is non-compliant, transmitting each frame that is compliant, and recording and storing of the identification-authentication credential for each frame transmitted.

Abstract: A high-efficiency, stall-proof airfoil is an aircraft wing configuration whereby a motive force directly induces gaseous fluid flow across a lifting surface of the airfoil without requiring a movement of the wing through an air space. The airfoil is provided with means to control a pitch, a roll and a yaw motion and to control a position and stability of the aircraft. When not undergoing horizontal displacement, it provides highly efficient use of fuel resources, precluding the formation of drag and its incumbent power consumption. Air pressure at a bottom of the wing remains essentially ambient. Therefore, differential pressure between a lower surface of the wing and an upper surface of the wing maintains its maximum possible quantity. Virtually, all of the power consumed is utilized in a production of lift. Additionally, because lift is generated without regard to an angle-of-attack, forward speed, nor a configuration of a leading edge of the wing, the configuration is essentially stall proof.

Abstract: A data security system for securing the critical data of an on-board airplane avionics system comprising access control means for controlling access to the said data on the basis of the security related information of a user, wherein the security related information is selected from the group consisting of: a list of authorised users; a maximum number of allowed accesses, as well as the types of allowed accesses; a time window allowed for access; a series/concatenation allowed for access, by various different users; and a hierarchical prioritisation of the zones associated with the data storage means.

Abstract: Disclosed is a module for transporting a fluid, including a woven structure forming a tubular pipe and at least one end connector placed at one end of the woven structure, the end connector including a main body delimiting an internal channel for the passage of the fluid. According to the invention, the internal wall of the body delimiting the channel, or the external wall of the body delimiting the external lateral surface of that body, being annular and having at least one shoulder defining an internal, respectively external, bearing face for the reception of at least one ring, the free end of the woven structure is anchored in the connector only by friction of the faces of the free end with the surfaces of the ring or rings and the internal, respectively external, wall of the main body.

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).