Abstract: Control damper including a body, defining a duct with an axis of blowing, and a control device, including a flap for closing the duct, the flap being movable in rotation with respect to the body about a pivot axis orthogonal to the axis of blowing, means for adjusting a nominal position of the flap, and a return device returning the flap to the nominal position when the flap is moved away from the nominal position. For an improved control, the means for adjusting further includes a shaft pivotally mounted with respect to the body about an axis of adjustment, wherein an angular position of the shaft about the axis of adjustment is adjustable, and at least one control cam limiting movements of the flap between the nominal position and an open position, wherein the return device includes a spring that is tensioned when the flap is in the nominal position.

Abstract: A turbine stator sector includes a plurality of vanes extending along a radial direction between a first end and a second end and along an axial direction between a leading edge and a trailing edge. The sector further includes an internal shroud linked to the first end of the vanes and an external shroud linked to the second end of the vanes. The sector includes at least one annular portion forming all or part of the internal shroud or of the external shroud. The annular portion includes a first partition present at the junction with the first or the second end of the vanes and a second partition held spaced from the first partition along the radial direction by a three-dimensional structure including a plurality of cutouts.

Abstract: An oil distribution device for a rotating planet carrier of a step-down gear of a turbomachine is configured to be fixedly joined to a tubular member for supporting a bearing of the planet carrier, said oil distribution device having an oil inlet and a row of oil outlets at the external periphery thereof, said oil distribution device having at least two internal cavities which are connected in series by at least one calibrated port, one of these cavities, referred to as the receiving cavity, being connected to said oil inlet, and internal calibrated channels for conveying oil which extend substantially radially from said cavities as far as ports of the periphery of the device in order to form said oil outlets.

Abstract: A turbine stator sector includes a plurality of vanes extending along a radial direction between a first end and a second end and along an axial direction between a leading edge and a trailing edge. The sector further includes an internal shroud linked to the first end of the vanes and an external shroud linked to the second end of the vanes. The sector includes at least one annular portion forming all or part of the internal shroud or of the external shroud. The annular portion includes a first partition present at the junction with the first or the second end of the vanes and a second partition held spaced from the first partition along the radial direction by a three-dimensional structure including a plurality of cutouts.

Abstract: A rotary planet carrier for a mechanical reduction gear of a turbomachine having an annular row of tubular members for supporting bearings that are parallel to one another and to an axis of rotation (X) of the planet carrier. The tubular members include grooves for oil to flow through that are connected to oil ducts that extend from the grooves to an external peripheral surface. The grooves are rectilinear and parallel to one another and to an axis of revolution (Y) of an internal cylindrical surface of a corresponding tubular member. Some of the grooves have a width about the axis of revolution that is greater than the diameter of the ducts connected to this groove. Some of the ducts are connected to the corresponding groove that is closest to the axis of rotation (X) of the planet carrier.

Abstract: The invention relates to a rotary planet carrier for a mechanical reduction gear (10) of a turbomachine, this planet carrier having an annular row of tubular members (16, 50) for supporting bearings (17) that are parallel to one another and to an axis of rotation (X) of the planet carrier, characterized in that each of the tubular members comprises grooves (72) for oil to flow through that are connected to oil ducts (58) that extend from the grooves to said external peripheral surface, these grooves being substantially rectilinear and parallel to one another and to an axis of revolution (Y) of an internal cylindrical surface (16b) of the corresponding tubular member, at least some of said grooves having a width or angular extent about said axis of revolution that is greater than the diameter of the ducts connected to this groove, and at least some of said ducts being connected to the corresponding groove at one of the longitudinal edges (72a) of this groove, namely the one that is closest to said axis of rota

Abstract: An oil distribution device for a rotating planet carrier of a step-down gear of a turbomachine is configured to be fixedly joined to a tubular member for supporting a bearing of the planet carrier, said oil distribution device having an oil inlet and a row of oil outlets at the external periphery thereof, said oil distribution device having at least two internal cavities which are connected in series by at least one calibrated port, one of these cavities, referred to as the receiving cavity, being connected to said oil inlet, and internal calibrated channels for conveying oil which extend substantially radially from said cavities as far as ports of the periphery of the device in order to form said oil outlets.

Abstract: The invention relates to a turbomachine blade comprising a vane. The vane comprises a leading edge, a trailing edge, a pressure face and a suction face spaced apart from each other and connecting the leading edge to the trailing edge. The vane further comprises at least one internal cavity between the pressure face and the suction face, wherein air is intended to flow. The vane comprises intersecting transverse partitions, downstream of the cavity, so that air can flow from the cavity in the direction of the trailing edge between the intersecting partitions.

Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.

Abstract: An angular diffuser sector for a turbine engine compressor is provided. The sector includes an inner shroud; an outer shroud; a vane; a casing element mounted at least in part around one of the shrouds and having an open groove facing an axial end of the corresponding shroud; a wedge-forming fitting interposed between the casing element and the corresponding shroud, the wedge presenting a first surface that contacts with a bearing surface of the axial end of the corresponding shroud, and a second surface that is inclined relative to the first surface and that contacts with a corresponding sloping surface of the groove in the casing element; and a device that exerts an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its second surface in contact with the sloping surface of the groove in the casing element.

Abstract: A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.

Abstract: The invention relates to a turbomachine blade comprising a vane. The vane comprises a leading edge, a trailing edge, a pressure face and a suction face spaced apart from each other and connecting the leading edge to the trailing edge. The vane further comprises at least one internal cavity between the pressure face and the suction face, wherein air is intended to flow. The vane comprises intersecting transverse partitions, downstream of the cavity, so that air can flow from the cavity in the direction of the trailing edge between the intersecting partitions.

Abstract: The invention provides an angular diffuser sector (16) for a turbine engine compressor, the sector comprising an inner shroud (20), an outer shroud (22), at least one vane (24), a casing element (36?) mounted at least in part around one of the shrouds and having an open groove (42) facing an axial end of the corresponding shroud, a wedge-forming fitting (44) interposed between the casing element and the corresponding shroud, the wedge presenting a first surface (46) for coming into contact with a bearing surface (22a) of the axial end of the corresponding shroud, and a second surface (48) that is inclined relative to the first surface and that is to come into contact with a corresponding sloping surface (50) of the groove in the casing element, and means (52) for exerting an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its bearing surface in contact with the sloping surface of the groove in the casing element.

Abstract: A turbomachine stator stage including two coaxial shrouds, respectively an inner shroud and an outer shroud with substantially radial vanes extending therebetween, the radially outer ends of the vanes being welded to the outer shroud and the radially inner ends of the vanes passing through orifices in an outer ring of the inner shroud, the inner ends being held by elastomer spacers in an annular cavity formed between the outer ring and an inner ring that is fastened to the outer ring.

Abstract: A compressor rotor for a turbomachine including at least two disks on a common axis carrying blades and connected together by a tubular wall, forming a surface of revolution, and a centripetal air bleed mechanism including air passages passing through the tubular wall, together with a wall extending along the tubular wall from the through passages up to one of the disks to channel the air stream inside the tubular wall.

Abstract: A turbine engine including at least one shaft and at least one bearing for rotatably guiding the shaft about an axis of the turbine engine, the bearing including a first radially inner ring and a second radially outer ring enclosing rolling members, wherein the first ring is floatingly mounted on the shaft via a fluid damping film.

Abstract: A pressure-balancing device for balancing pressure in at least one bearing enclosure of a turbojet, the enclosure including a mechanism feeding the bearing with lubricating liquid, an air intake, at least one sealing system placed between the stator and the rotor in front of and/or behind the bearing, a recovery mechanism recovering the lubricating liquid, and a removal mechanism removing the mixture of air and of traces of lubricating liquid towards a venting circuit. Downstream from the bearing enclosure and in the venting circuit, the balancing device includes a regulator system regulating the air removal flow rate, thereby enabling the flow rate to be variable as a function of the speed of the engine, to remain non-zero, and, at high speeds, to be lower than when the regulator system is not included.

Abstract: A method and a system for lubricating a turbine engine including at least three separate housings each including at least one roller bearing. The method pressurizes the housings through seals, of which two main housings are pressurized at a pressure higher than that of a remaining secondary housing, lubricates a secondary roller bearing only by injecting an oil mist from at least one of the main housings, the oil mist being supplied by a pressure difference between the main housings and the secondary housing, recovers a remainder of the lubrication oil injected into the main housings to supply the same to an oil tank, and supplies the air/oil mixture from the secondary housing to an oil separator.

Abstract: An aircraft engine annular shroud includes, on its internal surface, a peripheral annular groove able to accept a plurality of blade roots; an insertion opening for inserting the blade roots into the annular groove; and a closure device for closing off the insertion opening.

Abstract: A device for regulating the flow rate of air feeding a turbine ventilation cavity of a turbomachine turbine section is disclosed. The device includes at least one tubular duct opening into a take-off cavity and leading into a turbine ventilation cavity, the pressure inside the take-off cavity being higher than the pressure inside the turbine ventilation cavity; an air flow rate regulation valve disposed in the tubular duct, the valve being suitable for moving under the effect of the pressure difference between the take-off cavity and the turbine ventilation cavity; and a mechanical return device for holding the valve in a maximum closure position for the duct so long as the pressure difference between the take-off cavity and the turbine ventilation cavity remains below a predetermined threshold pressure.