Abstract: A rotating inlet cowl for a turbine engine includes a rotation axis. The rotating inlet cowl includes a forward cone defining a forward end of the inlet cowl. The forward end is configured to be eccentric relative to the rotation axis of the inlet cowl. Furthermore, the forward cone is truncated by a truncation surface defining the forward end of the inlet cowl.

Abstract: A rotating inlet cowl for a turbine engine includes a rotation axis. The rotating inlet cowl includes a forward cone defining a forward end of the inlet cowl. The forward end is configured to be eccentric relative to the rotation axis of the inlet cowl. Furthermore, the forward cone is truncated by a truncation surface defining the forward end of the inlet cowl.

Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.

Abstract: A method of repairing or of reworking a turbomachine disk including, on its rim, at least one external radial tab with an axial bore to accept an axial pin including a head and a shank with a threaded portion, the pin being slipped into the bore such that the head comes to press against one face of the tab through tightening of a nut on to the shank with the threaded portion against the opposite face of the tab, the pin forming a retaining mechanism to keep a tab secured to a component attached to the rim. A spot face is machined in the tab around the bore corresponding to a wearing zone, and a replacement pin including a flange pressing against the surface of the spot face, of a diameter greater than that of the head, is fitted.

Abstract: A device for axially retaining blades mounted on a turbomachine rotor disk is disclosed. The device includes a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also includes a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots. The retaining ring is housed in the groove of the disk, is held outwardly in the notches of the blade roots, and is constituted by a plurality of angular segments placed end to end.

Abstract: An oil separator rotor for a turbomachine, including a tubular hub that includes an external annular flange and an annular cover which, in cross section, is substantially L-shaped and mounted around the hub. The hub flange includes, at its external periphery, a mechanism to radially retain the free end of the cylindrical wall of the cover, so as to center this end and prevent it from deforming in the radially outwards direction under the effect of centrifugal force.

Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.

Abstract: The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices.

Abstract: The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk having a plurality of slots and a flange. The device also comprises blades, each having its root mounted in a respective slot, a retaining annulus having one end mounted against the upstream radial face of the disk, and a flange disposed around the flange of the disk and co-operating therewith to define a space forming a cooling air diffusion cavity that opens out into the bottom of each of the slots, together with air admission orifices opening out into the diffusion cavity at the upstream end thereof, the end of the retaining annulus that is mounted against the upstream radial face of the disk including a plurality of openings that open out radially into the bottom of each of the slots in the disk, at the upstream ends thereof.

Abstract: An oil separator rotor for a turbomachine, including a tubular hub that includes an external annular flange and an annular cover which, in cross section, is substantially L-shaped and mounted around the hub. The hub flange includes, at its external periphery, a mechanism to radially retain the free end of the cylindrical wall of the cover, so as to center this end and prevent it from deforming in the radially outwards direction under the effect of centrifugal force.

Abstract: The invention relates to a method of repairing or of reworking a turbomachine disk comprising, on it's rim, at least one external radial tab with an axial bore to accept an axial pin comprising a head and a shank with a threaded portion, the pin being slipped into the bore in such a way that the head comes to press against one face of the tab through the tightening of a nut on to the shank with threaded portion against the opposite face of the tab, said pin forming a retaining means to keep a tab secured to a component attached to the rim. It is characterized in that a spot face (123B; 223B; 323B) is machined in the tab around the bore (123A; 223A; 323A) corresponding to the wearing zone, and a replacement pin (100) comprising a flange (111A) pressing against the surface of said spot face, of a diameter greater than that of the head (111) is fitted.

Abstract: A bladed stator sector for a turbo-engine reduces the occurrence of thermally-induced stress cracks in stator blades by increasing the flexibility of the sectors by using one or more cutouts. The stator sector includes at least one stator blade between inner and outer platforms and at least one flange on one or more of the platforms. Each flange has a first end portion fixed to one of the platforms and a second end portion that is not fixed to either of the platforms. The one or more cutouts may be located on the flange and may be non-opening.

Abstract: The invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also comprises a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots, said retaining ring being housed in the groove of the disk, being held outwardly in the notches of the blade roots, and being constituted by a plurality of angular segments placed end to end.

Abstract: The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk having a plurality of slots and a flange. The device also comprises blades, each having its root mounted in a respective slot, a retaining annulus having one end mounted against the upstream radial face of the disk, and a flange disposed around the flange of the disk and co-operating therewith to define a space forming a cooling air diffusion cavity that opens out into the bottom of each of the slots, together with air admission orifices opening out into the diffusion cavity at the upstream end thereof, the end of the retaining annulus that is mounted against the upstream radial face of the disk including a plurality of openings that open out radially into the bottom of each of the slots in the disk, at the upstream ends thereof.

Abstract: The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices.

Abstract: The present invention relates to a bladed stator for a turbo-engine, in particular a bladed stator sector comprising an inner platform (3) and an outer platform (4), at least one blade (2) fixed between said platforms (3, 4), at least one of said platforms (3, 4) comprising at least one flange (5, 6) having a first end (5a, 6a) fixed to the platform (3, 4) and a second, free end (5b, 6b), said flange (5, 6) comprising at least one non-opening free flexibility-increasing cutout (10).

Abstract: The invention relates to a part (110) of the distributor of the first stage of a turbojet low-pressure turbine. A part of this type comprises an outer platform segment (104) and an inner platform segment (102) between which a plurality of hollow blades (106), intended to be supplied with cooling air, extend, a cap (132) covering a base portion (138) of the outer platform segment (104) so as to define with this base portion a chamber (140), which communicates with the interior of said blades (106) via communication openings (130), air inlets (137) being provided in said cap (132) in order to allow said chamber (140) to be supplied with cooling air.