Abstract: A fan assembly is described comprising a refrigeration system, an airflow generator and a condensation collector. The refrigeration system comprises a first heat exchanger and a second heat exchanger. The airflow generator is for generating an airflow over the second heat exchanger, and the condensation collector is for collecting condensate that forms on the second heat exchanger.

Abstract: Disclosed is a variable pitch propeller blade for an aircraft turbine engine. The blade includes an airfoil connected to a root, the root having a body housed in an annular barrel that extends around a pitch axis of the blade, the body including a free end opposite the airfoil; a shoulder towards the airfoil; and a bulb located between the free end and the shoulder. The bulb can have a cross-section, referred to as the middle section, that has a maximum value Sm, and the barrel can be affixed to the body and covers and matches at least a portion of the bulb and the shoulder.

Abstract: A turbine includes a first rotor and a second rotor that can rotate in opposite directions and are interleaved. The turbine further includes a ring to which abradable material is secured, the ring, unsegmented, extending between the first impellers of the first rotor and the second rotor, over a sector of between 350 and 360°, and, axially between an upstream end and a downstream end of the ring, the ring is held with the second rotor.

Abstract: A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.

Abstract: A pitch lock system including an outer member having a centerline axis, an inner member located radially inward of the outer member with respect to the centerline axis, and a plurality of clutch elements located between the outer member and the inner member. The pitch lock system has a disengaged position and an engaged position. In the engaged position, the plurality of clutch elements are constrained between the inner member and the outer member such that relative axial direction of the plurality of clutch elements is permitted in only one direction. An engine includes a pitch actuator and the pitch lock system.

Abstract: The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).

Abstract: A method for priming of a pump in response to a priming condition includes confirming that the liquid level in the reservoir is located at the same level or above the upper portion of the impeller, driving the impeller in a reverse direction of rotation for a time duration between 2 seconds and 5 seconds, stopping the impeller from rotating in the reverse direction of rotation, driving the impeller in a forward direction of rotation, detecting, during the forward operation of the impeller, whether too much gas is present in the volute, and in response to detection of too much gas in the volute, stopping the impeller from rotating in the forward direction of rotation and driving the impeller in the reverse direction of rotation, and in response to non-detection of too much gas in the volute, exiting the priming of the pump.

Abstract: A blood pump includes an impeller; a drive shaft coupled to the impeller and configured to rotate with the impeller; and a rotor coupled to the drive shaft and configured to rotate with the drive shaft. The rotor includes a driven magnet having an outer surface. A corrosion-resistant coating may be disposed on the outer surface of the driven magnet. A stator is disposed adjacent the rotor and configured to drive the rotor, causing the rotor to rotate; and a motor is configured to drive the stator. A protection assembly may be disposed adjacent the stator and configured to receive an end of the drive shaft, and may include a protection assembly housing enclosing a protective fluid chamber, the protective fluid chamber including the driven magnet and at least a portion of a bearing configured to engage the end of the drive shaft.

Abstract: An impeller of a centrifugal compressor includes: a hub; and at least one blade disposed on a hub surface of the hub. A hub-side end of a trailing edge of the at least one blade is located radially outward of an outer peripheral portion of the hub, and is located on either of a first line extending radially outward from the hub surface of the hub or a second line extending radially outward from a back surface of the hub.

Abstract: Present disclosure discloses a seal assembly for an actuator rod of a pitch actuator. The assembly includes at least one first ring annularly interposed between an actuator rod and a cylinder cover, and removably supported by a first split retainer half pair in an annular recess defined in the cylinder cover. A first seal is annularly interposed between the actuator rod and the cylinder cover. A second seal annularly is interposed between the actuator rod and the cylinder cover is supported by a retainer. The seal assembly also includes a wiper seal which is annularly interposed and supported by a third split retainer half pair between the actuator rod and the cylinder cover. Each of the first, second and third split retainer half pairs, and the retainer is removably connectable to the cover.

Abstract: A dual flow turbine engine includes at least one lubricant tank located in an annular space of the turbine engine body and at least one hatch which is provided on an external cowling of a nacelle, for filling the tank. The tank is configured to be filled, by means of a removable tubular pipe inserted from the hatch into the tank, through canisters. One of the canisters includes a first interface through which the pipe is configured to pass, and another canister includes a second interface for connecting the pipe to the tank.

Abstract: A gas turbine engine includes a rotor that has a seal surface and a shaft that is rotatable about an engine central axis. The shaft has an annular seal channel that opens to the seal surface. There is a seal for sealing against the seal surface. The seal has channels formed therein that define a tortuous seal wall with interconnected spring ligaments such that the seal is elastically diametrically expandable for installation clearance around the shaft and, once on the shaft, elastically diametrically collapsible into the annular seal channel.

Abstract: Provided is a wind turbine blade, with a generally hollow blade body including half shells and webs, with each web including flanges with the first and second webs being supported via respective reinforcement structures relative to the respective half shell, which reinforcement structures are arranged between an outer and an inner layer of the upper and lower half shell of the shells and extend in the lengthwise direction of the blade, wherein the first and second reinforcement structures each include at least one stack composed of several pultruded composite strips including carbon fibers with the strips being fixed in the resin, wherein at least one stiffening element extending parallel to the reinforcement structures over at least a part of their length comprising at least one stack composed of several glass fiber layers infused with resin is arranged between the reinforcement structures.

Abstract: A bearing chamber housing (20) for bearing a shaft (3) of a turbomachine (1), including a housing outer shell (21) that delimits an oil chamber (33) of the bearing chamber housing (20) radially outwardly in relation to a rotational axis (4) of the shaft (3), and a housing inner shell (22) for bearing the shaft (3). The housing inner shell (22) is radially connected to the housing outer shell (21) via support ribs (23) that in each case extend axially, at least in part, and the housing inner shell (22), the housing outer shell (21), and two support ribs (23) that are next-adjacent to one another jointly delimit a cavity (41) that is axially open at the rear, and thus lead into a rear opening (32). The rear opening (32), viewed in tangential sections, has a clearance (35) in each case that constitutes at least 50% of a circumferential distance (43) between the next-adjacent support ribs (23).

Abstract: A turbocharger includes a bearing housing, a variable displacement mechanism, and a restricting member. The variable displacement mechanism includes a nozzle ring and a drive ring. The restricting member includes a flange part, a drive ring guide pin part, and a phase determining pin part. The flange part straddles a first surface of the nozzle ring facing the bearing housing and a second surface of the drive ring facing the bearing housing so that a position thereof with respect to the nozzle ring is fixed. The drive ring guide pin part is formed integrally with the flange part and disposed in a first hole formed on the first surface. The phase determining pin part is formed integrally with the flange part and disposed in a second hole formed on a third surface of the bearing housing facing the variable displacement mechanism.

Abstract: A module including a device for changing the pitch of the vanes about the pitch axes thereof, the device including: a hydraulic actuator capable of rotating about the longitudinal axis (X) and configured to rotate the vanes about their pitch axes (C), a supply pump for supplying fluid to the hydraulic actuator, the supply pump including a drive shaft capable of rotating about the longitudinal axis (X) and a shell that is rotationally fixed relative to the longitudinal axis (X), and an electric machine configured to operate the supply pump, the electric machine having a rotary member for driving the drive shaft and a fixed member that is rotationally fixed relative to the longitudinal axis (X).

Abstract: A modular wind turbine blade includes a blade root, an intermediate portion and a blade tip. The intermediate portion includes a plurality of modular blades, two adjacent modular blades being provided at edge thereof with a first connecting portion and a second connecting portion that cooperate with each other, and wherein the plurality of modular blades includes a trailing edge shell, a leading edge shell and a main beam, respectively, the first connecting portion at the edge of the trailing edge shell and the leading edge shell being fixedly connected to the second connecting portion at the edge of the main beam. The wind turbine blade according to the present invention adopts segmented modular structural design, which effectively reduces the mold occupancy time of the blade, shortening the production cycle and improving the molding efficiency.

Abstract: The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.

Abstract: A passive auxiliary lubrication system for supplying lubricant to a gearbox assembly of an engine. The passive auxiliary lubrication system includes an auxiliary tank for storing lubricant. The auxiliary tank is passively pressurized. The passive auxiliary lubrication system also includes an auxiliary tank feed line fluidly coupled with the auxiliary tank and a primary lubrication system. The lubricant is supplied to the auxiliary tank from the primary lubrication system through the auxiliary tank feed line and the lubricant is passively pressurized in the auxiliary tank. The passive auxiliary lubrication system further includes an auxiliary supply line fluidly coupled with the auxiliary tank and the gearbox assembly. The lubricant in the auxiliary tank is supplied to the gearbox assembly through the auxiliary supply line.

Abstract: A gearbox assembly for a gas turbine engine includes a hollow gear. The hollow gear has one or more reservoirs configured to store a lubricant and one or more passages configured to supply the lubricant to one or more gear meshes in the gearbox assembly. The hollow gear provides a dampening system configured to absorb vibrations and loading experienced in the gearbox assembly and configured to provide impact resistance for the gearbox assembly.