Abstract: A method for modeling at least part of a non-axisymmetric surface (5) of one portion (2) of a part (1). The portion (2) is bounded by first and second extremal planes (PS, PR). The method includes processing data from a device (10), by: (a) modeling at least two basic non-axisymmetric surfaces (Sk, SI, SE) making up the surface, each of the basic surfaces (Sk, SI, SE) extending between both extremal planes (PS, PR) of the portion (S); (b) constructing at least one connection curve (CR) tangential to the first and second surfaces; (c) locally modifying the first and second basic surfaces (Sk, SI, SE) to keep to the connection curve (CR) near a discontinuity; and (d) restoring, at least part of the obtained surface (5).

Abstract: A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.

Abstract: A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.

Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.

Abstract: A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade.

Abstract: The present invention relates to a method for modeling at least part of a non-axisymmetric surface (S) of one portion (2) of a part (1), the portion (2) being bounded by a first and a second extremal planes (PS, PR).

Abstract: A turbomachine rotor blade including a blade root and a blade tip spaced apart by a blade height, including at least one intermediate segment between the blade root and the blade tip that presents forward sweep over at least 50% of the blade height, and a distal segment with backward sweep between the intermediate segment and the blade tip, the distal segment also presenting a positive tangential angle of inclination.

Abstract: A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.

Abstract: A turbomachine element including an airfoil set including a plurality of airfoils that are offset from one another in a lateral direction, and upstream from at least one end of each airfoil, a group of a plurality of vortex generator devices that are mutually offset both laterally and axially.

Abstract: A one-block bladed disk includes blades, a leading edges of which has sweep and dihedral angles, both strongly variable and increasingly large upon approaching a connection to a hub to improve mechanical strength of the whole and obtain good distribution of gas flow over the height of the blade.

Abstract: A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade.

Abstract: In an embodiment of the present invention, at a Deployer level, an application software component is provided with a tree representation 510 of objects it contains. An object is a leaf node, with the attributes of the object being in nexus between the root and the leaf node. An accessor object 511 has methods to access the tree 510. In one embodiment of the present invention, at an administrator level, a handler object 611 in turn accesses accessor object 511. Handler object 611 may be part of a handler home object 619. Client applications 710 have lookup services 711 to access handler objects like 611, e.g. via a lookup home object 719, and handler home object 619.

Abstract: In an embodiment of the present invention, at a Deployer level, an application software component is provided with a tree representation 510 of objects it contains. An object is a leaf node, with the attributes of the object being in nexus between the root and the leaf node. An accessor object 511 has methods to access the tree 510. In one embodiment of the present invention, at an administrator level, a handler object 611 in turn accesses accessor object 511. Handler object 611 may be part of a handler home object 619. Client applications 710 have lookup services 711 to access handler objects like 611, e.g. via a lookup home object 719, and handler home object 619.