Abstract: Aspects of the invention relate to techniques for applying edge fragment correlation information to optical proximity correction. Neighbor-aware edge adjustment values for the edge fragments are computed based on edge placement error values and edge fragment correlation information. The computation comprises: selecting a group of edge fragments around a center edge fragment, calculating preliminary neighbor-aware edge adjustment values based on the edge placement error values and the edge fragment correlation information for the group of edge fragments, storing the preliminary neighbor-aware edge fragment adjustment value for the center edge fragment, and repeating the selecting, the calculating and the storing with each of the edge fragments being the center edge fragment. The computed neighbor-aware edge adjustment values are combined with conventional edge adjustment values and the edge fragments are adjusted accordingly. The process may be repeated for a number of times.

Abstract: Aspects of the invention relate to techniques for applying edge fragment correlation information to optical proximity correction. Conventional edge adjustment values for the edge fragments are first derived from edge placement error values. Neighbor-aware edge adjustment values for the edge fragments are then computed based on the edge placement error values, the conventional edge adjustment values and edge fragment correlation information. The computation comprises: calculating pseudo edge placement error values by subtracting neighboring edge movement contribution values from the edge placement error values and calculating the neighbor-aware edge adjustment values based on the pseudo edge placement error values. The computed neighbor-aware edge adjustment values are combined with conventional edge adjustment values and the edge fragments are adjusted accordingly. The process may be repeated for a number of times.

Abstract: A method for separating features in a target layout into different mask layouts for use in a photolithographic process. Features of a target layer are searched for features having a predefined shape. In one embodiment, portions of the feature having the predefined shape divided into two or more sub-features and at least one sub-feature are not considered when separating the features into two or more mask layouts. In another embodiment, features having a predefined shape are cut to form two or more sub-features and all features and sub-features are considered when separating the features of the target layout into the two or more mask layouts.

Abstract: The invention relates to a turbine wheel in a turbine engine, the wheel comprising a disk having a plurality of blades with roots that are axially engaged and radially retained in longitudinal slots in the outer periphery of the disk, the blades having platforms that extend circumferentially end to end and that are radially facing longitudinal teeth of the disk that define the slots. Protection members for protecting the flanks of the slots and made out of sheet metal are mounted on the teeth of the disk and held thereon by co-operating shapes, the protection members including means for bearing radially against the platforms of the blades in order to oppose circumferential tilting of the blades, and they also include means for at least partially closing the radial gaps between the teeth and the platforms of the blades.

Abstract: Aspects of the invention relate to techniques for determining edge fragment correlation information. With various implementations of the invention, image intensity slope information for edge fragments in a layout design is determined. The image intensity slope information comprises information describing how image intensity for each of the edge fragments changes with its position. Image amplitude sensitivity information for the edge fragments is also determined. The image amplitude sensitivity information comprises information describing how image amplitude for each of the edge fragments changes with positions of neighboring edge fragments. Based on the image intensity slope information and the image amplitude sensitivity information, edge fragment correlation information for the edge fragments is determined. Using the edge fragment correlation information, the layout design may be processed by using, for example, OPC techniques.

Abstract: A blade made of composite material including an airfoil formed of filaments or fibers, optionally woven, impregnated with a heat-curable resin, with an intrados wall and an extrados wall between the leading edge and the trailing edge; and a device for damping the vibrations incorporated in one or other of the intrados and extrados walls is disclosed. The damping device is formed of at least one layer made of viscoelastic material and a layer made of rigid material, these layers being superposed. The layer made of rigid material includes a first zone and a second zone. The layer made of viscoelastic material is interposed between the airfoil and the first zone of the rigid layer, and the second zone of the rigid layer is attached to the wall of the airfoil without interposition of viscoelastic material.

Abstract: Aspects of the invention relate to techniques for determining edge fragment correlation information. With various implementations of the invention, image intensity slope information for edge fragments in a layout design is determined. The image intensity slope information comprises information describing how image intensity for each of the edge fragments changes with its position. Image amplitude sensitivity information for the edge fragments is also determined. The image amplitude sensitivity information comprises information describing how image amplitude for each of the edge fragments changes with positions of neighboring edge fragments. Based on the image intensity slope information and the image amplitude sensitivity information, edge fragment correlation information for the edge fragments is determined. Using the edge fragment correlation information, the layout design may be processed by using, for example, OPC techniques.

Abstract: A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece.

Abstract: A rotor disk for a fan in a turbomachine is disclosed. The disk includes in its perimeter a plurality of essentially axial grooves for the installation and retention of vane roots having hooks at their downstream ends, and deformable regions formed by cavities being situated at the downstream end of the grooves in attachment flanges for inter-vane platforms to absorb the stresses between the disk and the vane roots.

Abstract: A rotor wheel of a turbine engine includes a plurality of CMC blades each having a first portion constituting a blade airfoil and root and made as a single piece with a second portion forming an outer platform. The blades are held under twisting prestress by mutual engagement via contact zones between the outer platforms of adjacent blades, and the contact zones that are situated on opposite sides of the outer platform of a blade are defined by at least one insert that is integrated in the outer platform and that is, for example, made of a carbon-based material.

Abstract: A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Abstract: The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane.

Abstract: Techniques for initiating and, if desired, modifying location services for Secure User Plane Location (SUPL) and other location architectures are described. To initiate SUPL service, a SUPL Location Platform (SLP) transmits a SUPL initial session message applicable to any service request to a SUPL enabled terminal (SET) and receives in response the service capabilities of the SET. The SLP selects and requests service from the SET consistent with the service capabilities of the SET. The SET may initiate SUPL service by requesting the service capabilities of the SLP. The SET selects and requests service from the SLP that is consistent with the service capabilities received from the SLP. The SET and SLP communicate to determine a position estimate for the SET. The service may be modified before or while communicating between the SET and the SLP to determine a position estimate for the SET.

Abstract: The present invention relates to a blade made of composite material (100) comprising an airfoil (100A) formed of filaments or fibers, optionally woven, impregnated with a heat-curable resin, with an intrados wall and an extrados wall between the leading edge and the trailing edge. It is characterized in that a device for damping the vibrations is incorporated in one or other of the intrados and extrados walls, and is formed of at least one layer made of viscoelastic material (111) and a layer made of rigid material (110), these layers being superposed. According to one embodiment, the layer made of rigid material comprises a first zone (1101) and a second zone (1102), the layer made of viscoelastic material (111) being interposed between the airfoil and said first zone (1101) of the rigid layer (110), and said second zone (1102) of the rigid layer being attached to the wall of the airfoil (100A) without interposition of viscoelastic material.

Abstract: The present invention relates to an improvement in the clearances 12 between a casing and the moving blades 11 of a rotor 1 of a turbomachine, in particular a casing provided for this purpose, and also to a turbomachine fitted with such a casing. The invention applies in particular to aircraft turbojet engines. It relates more particularly to a turbomachine inner casing 21 comprising a plurality of annular shrouds 23 that are provided with flanges 24 for joining two adjacent shrouds 23 together. According to the invention, this inner casing 21 further includes: at least one circumferential heat shield 5 covering the flanges 24 in contact with two adjacent shrouds 23; and a cavity 6 filled with a first thermal insulation 8, said cavity being located between a concave internal surface 51a, 52a of the heat shield 5 and the flanges 24. The heat shield 5 is formed by a plurality of sectors 50 joined end to end.

Abstract: Techniques to support positioning for terminals in Secure User Plane Location (SUPL) are described. A SUPL Enabled Terminal (SET) may receive supported network information from a SUPL Location Platform (SLP), which is a location server in SUPL. The supported network information may indicate one or more radio access networks supported by the SLP, one or more types of measurement supported by the SLP, and/or information that the SET is allowed to send to the SLP. The SET may send network measurement information for a supported radio access network to the SLP. The network measurement information may include cell and/or access point (AP) information for one or more access points or base stations in the supported radio access network. The SLP may determine a location estimate for the SET based on the network measurement information from the SET.

Abstract: The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane.

Abstract: Techniques for adjusting edge segments within a layout design such that fewer iterations of an optical proximity correction process are required for covergence are provided. With various implementations, multiple iterations of an optical proximity correction process are performed on a portion of a layout design. The final displacement of various edge segments within a layout design may be employed to adjust the displacement of like edge segments within the same or alternate layout design, such that the optical proximity correction process may converge upon a suitable solution in fewer iterations.

Abstract: A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Abstract: A method for separating features in a target layout into different mask layouts for use in a photolithographic process. Features of a target layer are searched for features having a predefined shape. In one embodiment, portions of the feature having the predefined shape divided into two or more sub-features and at least one sub-feature are not considered when separating the features into two or more mask layouts. In another embodiment, features having a predefined shape are cut to form two or more sub-features and all features and sub-features are considered when separating the features of the target layout into the two or more mask layouts.