Abstract: An aircraft turbomachine including a mechanical reduction gear including one sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, each planet gear including a first toothing for meshing with the sun gear, and a second toothing for meshing with the ring gear, the first toothing of each planet gear having a diameter greater than that of the second toothing of the planet gear, and a planet carrier, wherein the sun gear is coupled to a first rotor shaft of the turbomachine, the planet carrier is coupled to a second rotor shaft of the turbomachine, the ring gear is fixed to a stator of the turbomachine.

Abstract: A planet carrier for a speed reducer of an aircraft turbomachine, the planet carrier including a cage carrier and a cage. The cage can have two parts: a first part having a wall and bridges, these bridges projecting axially from a face of this wall and including first axial ends connected to this face and second free axial ends; and a second part having another of the walls, this other wall including a face to which the free ends of the bridges are applied. The two parts of the cage can be attached together by screws.

Abstract: A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element.

Abstract: A pre-assembly method for an aircraft turbomachine, having preliminary assembling, outside the turbomachine, the following components with each other a reduction gear configured to transmit a rotation between at least two rotors of the turbomachine while modifying the speed and torque ratio from one to the other of said at least two rotors, a shaft kinematically coupled to the reduction gear and configured to be kinematically coupled to one of said at least two rotors, a bearing support, and at least one bearing mounted on the bearing support and configured to rotatably support the shaft.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.

Abstract: A power transmission module for an aircraft, the module including a torque input connected to a turbine shaft, a first torque output and a second torque output, the power transmission module including a mechanical reducer including a sun gear forming the torque input, and planet gears carried by a planet carrier, wherein each of the planet gears includes at least three independent toothings and further includes a first toothing meshed with the sun gear, a second toothing meshed with an element forming one of the torque outputs, and a third toothing meshed with another element

Abstract: A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second loathing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of the plane (H) and separated from one another by the first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.

Abstract: A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.

Abstract: According to some implementations, a n medical interventional imaging device for monitoring an interventional procedure is described. The medical interventional imaging device includes a temporary data buffer configured to temporarily store medical interventional fluoroscopic image data, a signal processor configured to detect if an abnormal state occurs during an intervention and to record an instant at which the abnormal state has occurred, and a permanent data storage configured to permanently store at least a part of the medical interventional fluoroscopic image data stored temporarily before and/or at the recorded instant if the abnormal state is detected.

Abstract: A method for analyzing a biological fluid specimen. The collection cartridge is inserted into a reader. The plurality of reactive elements of the collection cartridge following insertion of the collection cartridge is optically read recurrently. The first color change of at least one reactive element of the collection cartridge is detected and dated following the recurrent optical reading. The biological fluid specimen from the collection cartridge is analyzed following the detection of the color change of at least one reactive element of the collection cartridge.

Abstract: A device to collect a biological liquid sample to be inserted into a portable reader to analyze the biological liquid. The device includes a strip, an absorbent assembly, a band and a housing having a housing bottom. The color-changing reactive elements are arranged one after the other on an upper face of the strip. The absorbent assembly includes a deposition portion on which the biological liquid is deposited thereon. The band to diffuse the biological liquid arranged over the top of the reactive elements. The strip is arranged on the housing bottom with a lower face of the strip facing the housing bottom. Each reactive element is arranged by transparency through the strip facing an opening in the housing bottom. A cover is arranged over the top of the band and includes a protruding pattern forming a pressing surface configured to press the band into contact with the reactive elements.

Abstract: A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.

Abstract: A vapor compression system includes a compressor configured to circulate a refrigerant through a refrigerant loop, a sump configured to receive a mixture of lubricant and the refrigerant from the compressor, and a controller having a memory and a processor. The processor is configured to receive a first signal indicative of a temperature of the mixture within the sump, receive a second signal indicative of a pressure of the mixture within the sump, determine a relative amount of the refrigerant in the mixture based on the first signal and the second signal, and output a control signal in response to the relative amount of the refrigerant in the mixture exceeding a threshold value.

Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, the reduction gear including a sun gear, a ring gear, planet gears which are meshed with the sun gear and the ring gear, hydrodynamic bearings for guiding the planet gears in rotation, these bearings being carried by a planet carrier and including cylindrical bodies which are engaged in the planet gears and which are configured so as to be supplied with oil and so as to form guiding oil films between the bodies and the planet gears, wherein each of the planet gears is guided by two hydrodynamic bearings independent of each other and disposed on either side of the plane.

Abstract: An impeller (130) for a planet carrier of a planetary gear speed reducer of a turbomachine, said impeller having a generally annular shape and comprising means (158) for supporting axes of rotation of planets of said reducer, said impeller comprising means for lubricating teeth of said planets and bearings of said axes, said lubrication means comprising an annular groove (138) located on the internal periphery of said impeller and opening radially towards the inside, said groove being connected to lubricant supply and/or spray means, characterised in that the impeller comprises dynamic annular sealing means (142, 144) located at the inner periphery of said impeller, on either side of the groove, and configured to interact with a stator (132) of the reducer or of the turbomachine intended to extend inside of and coaxially with the impeller.

Abstract: A mechanical gearbox for an aircraft turbomachine includes a sun gear having an axis (X) of rotation, a ring gear around the sun gear, and planet gears meshed with the sun gear and the ring gear. Each planet gear has a first toothing meshed with the sun gear and a second toothing meshed with the ring gear. The first toothing includes a series of upstream teeth and a series of downstream teeth located on either side of a plane (H) perpendicular to the axis (X) of rotation of the sun gear. The second toothing includes a series of upstream teeth and a series of downstream teeth located on either side of said plane (H) and separated from one another by said first toothing, these teeth being parallel to one another and to the axis (Y) of rotation of the planet gear.

Abstract: A mechanical reduction gear for turbomachine, in particular for aircraft. The reduction gear includes a sun gear having an axis of rotation, a ring gear which extends around the sun gear, planet gears which are meshed with the sun gear and the ring gear and which each includes a first toothing and a second toothing each including two series of teeth located on either side of a median plane, each of the planet gears being centred and guided in rotation by bearings, including an upstream bearing interposed axially between the series of upstream teeth of the second toothing and the plane, and a downstream bearing interposed axially between the series of downstream teeth of the second toothing and the plane.

Abstract: According to some implementations, a n medical interventional imaging device for monitoring an interventional procedure is described. The medical interventional imaging device includes a temporary data buffer configured to temporarily store medical interventional fluoroscopic image data, a signal processor configured to detect if an abnormal state occurs during an intervention and to record an instant at which the abnormal state has occurred, and a permanent data storage configured to permanently store at least a part of the medical interventional fluoroscopic image data stored temporarily before and/or at the recorded instant if the abnormal state is detected.

Abstract: A speed-reducing unit, particularly for transferring torque between a gas turbine and a fan in a turbine engine, includes an annular ring, at least one gear that is coupled to the ring, the ring including two annular half-rings that are offset relative to each other along the main axis of the speed-reducing unit and that are coupled with at least one gear, and a plate for supporting the two half-rings, in relation to which the two half-rings are rotationally fixed about the main axis of the speed-reducing unit. Each half-ring includes an internal helical tooth. Each half-ring is connected to the support plate so as to be able to be uncoupled from at least one gear when at least one gear exerts a disengaging action on each half-ring, with the amplitude of the action being greater than a determined amplitude value.

Abstract: The invention relates to a pressure cooking utensil comprising a vessel, a lid with an annular skirt, and a gasket interposed between the lid and the vessel, said gasket including a ring and a first lip in sealing contact with the top wall of the lid, said utensil being characterized in that it includes a leakage opening formed through said top wall, the annular skirt forming a stop abutment for the ring, said first lip presenting flexibility that is suitable, when the pressure that exists inside the enclosure exceeds a safety threshold, for causing the inside of the enclosure to communicate with the outside through the leakage opening.