Abstract: A fan assembly for a robot vacuum cleaner and a robot vacuum cleaner are provided. The fan assembly includes an electric motor, a stator impeller, a rotor impeller and a fan cover. The stator impeller defines a shaft hole, the electric motor is mounted on a side of the stator impeller, and an output shaft of the electric motor passes through the shaft hole. The fan cover is mounted on another side of the stator impeller, and an end surface of the fan cover away from the stator impeller defines an air inlet. The rotor impeller is mounted to the output shaft of the electric motor and located between the fan cover and the stator impeller.

Abstract: A holding apparatus for securing a fan for cooling a component of a vehicle, having a main body made from foam material. The main body has a fan receptacle for receiving the fan in a positively locking manner at least in sections. The fan receptacle has an air inlet for feeding in air to the fan and an air outlet for discharging air from the fan. The main body also has at least one inlet opening with an adjoining inlet duct and at least one outlet opening with an adjoining outlet duct. The inlet duct is in a fluid-communicating connection with the air inlet and the outlet duct is in a fluid-communicating connection with the air outlet.

Abstract: A locking spacer, which is fitted in a dovetail slot provided on an outer circumferential surface of a disk put on a rotor shaft, includes: a pair of first blocks each provided with a dovetail joint, and configured to have a size occupying a portion of an internal space of the dovetail slot; a pair of second blocks having a size occupying a portion of the internal space of the dovetail slot, the portion not being occupied by the pair of first blocks, and each being provided with a locking groove; and a locking block having a size occupying a portion of the internal space of the dovetail slot, the portion not being occupied by the first and second blocks, and being provided with a rotating locking arm configured such that opposite end portions thereof are inserted into the locking grooves.

Abstract: A propeller blade comprises a fibre reinforced blade structure spar having a blade retention section formed at one end thereof, and at least one metallic formation spray deposited onto said blade retention section.

Abstract: Aspects of the disclosure are directed to a floating, non-contact seal comprising: a shoe, and at least three beams, each beam having a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure. Aspects of the disclosure are directed to an engine comprising: a first structure, a second structure configured to rotate relative to the first structure, and a floating, non-contact seal that interfaces the first structure and the second structure, where the seal includes: a shoe, and at least three beams, where each beam has a first axial end and a second axial end, where the first axial ends are coupled to the shoe and the second axial ends are coupled to a ring structure.

Abstract: A centrifugal pump assembly has an electric drive motor (2) and at least one impeller (10; 10?), which is movable in an axial direction (X) between at least two functional positions. In one functional position a flow path through the impeller (10; 10?) is essentially closed and in another functional position the flow path through the impeller (10; 10?) is opened. The impeller (10; 10?) in a first functional position is held by a magnetic force (FM) or a spring force and in a second functional position is held by a hydraulic force (FH) produced by a delivered fluid. An impeller is provided for the centrifugal pump assembly.

Abstract: An inner peripheral edge of a first annular member includes a plurality of first inner edge portions belonging to an angular range in which support holes exist in the circumferential direction of a turbine rotor and a plurality of second inner edge portions belonging to an angular range in which the support holes do not exist in the circumferential direction of the turbine rotor. At least one second inner edge portion of the plurality of second inner edge portions comprises a recess portion recessed outward in a radial direction of the turbine rotor, the recess portion extending in an axial direction of the turbine rotor from the side of exhaust gas.

Abstract: One aspect of the invention relates to a pump device comprising an impeller; a pump housing surrounding an interior region and having an inlet and an outlet. The impeller is provided in the interior region of the pump housing. The wall of the pump housing has at least one first subregion and at least two further subregions in at least one plane perpendicular to the longitudinal extension of the pump housing. The at least one first subregion comprises at least 60% by weight, based on the total mass of the at least one first subregion, of at least one nonmagnetic material. The further subregions comprise at least 41% by weight, based on the total mass of the further subregions, of at least one ferromagnetic material, wherein each further subregion is adjacent to at least one first subregion in the plane.

Abstract: Bleed air system includes bleed port with annular bleed slot in a compressor inner casing surrounding flowpath circumscribing a centerline in compressor inner casing. Inner and outer slot walls bound bleed flow passage through the bleed slot. Annular array of arcuate shields radially inwardly bound the bleed flow passage downstream and aft of inner slot wall. Each shield includes integrally-formed axially forward retaining portion, downstream portion, and upstream portion therebetween. Clipping means clips retaining portion to aft facing radial wall of annular lip on inner slot wall. Clipping means may be arcuate or annular clip having forward annular portion attached to annular aft flange substantially perpendicular to the centerline and forward annular portion disposed in annular slot extending into inner slot wall. Forward annular portion and annular slot may be cylindrical or conical. Clip may include aft conical portion radially offset from forward conical portion and transition portion therebetween.

Abstract: A centrifugal compressor casing, comprising a bundle which rotatably supports a rotating shaft, and an impeller fixed to the rotating shaft and that rotates with the rotating shaft about an axis of the rotating shaft, and in which an annular suction flow channel centered on the axis introduces fluid into the flow channel of the impeller, and an annular discharge flow channel centered on the axis that discharges the fluid from the flow channel of the impeller, are formed; a casing main body which covers the bundle from the outer circumferential side; and a volute piece which is provided on an inner surface of the casing main body in the discharge flow channel.

Abstract: A device for controlling clearance at the tops of turbine rotating blades. The device comprises shroud supporting rings, abradable ring sectors, elastic centering elements, and a shroud supporting ring sectors inserted radially to the supporting shroud, between the elastic elements and the abradable ring sectors, which are attached to said supporting shroud, which has a volume varying according to temperature, due to the action of fluid supply elements.

Abstract: Disclosed is a flutter damper, including a chamber having an internal space, a movable diaphragm disposed at least partially within the chamber, the diaphragm separating the chamber into a first chamber and a second chamber, the second chamber forming an acoustic volume, wherein a size of the acoustic volume configures the chamber for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes, and a biasing member that moves the diaphragm responsive to a signal from an aircraft or engine electronic control (EEC) unit, wherein movement of the diaphragm increases or reduces the size of the acoustic volume of the second chamber.

Abstract: A propulsive assembly for an aircraft includes a nacelle and a turbojet. The nacelle includes an upstream air inlet section. The turbojet includes a fan with removable blades. The air inlet section extends longitudinally. The fan includes a rotary disk including an annular peripheral wall and a plurality of curvilinear recesses positioned circumferentially in the wall. Each blade includes a blade body extending between a blade root and a blade head in a blade axis which is roughly radial relative to a fan rotation axis. Each blade root includes a curvilinear attachment housed in a respective recess of the rotary disk. Each attachment has a support surface forming an arc. The function of the support surface is to hold the attachment in the recess. The arc extends in or parallel to an attachment plane containing the blade axis or forming with the blade axis an angle of less than 15°.

Abstract: A pump assembly (2) includes an electric drive motor (14) and with at least one impeller (18) which is driven by the motor. The impeller is movable in an axial direction (X) between at least one first and one second position. The impeller in the first axial position is situated in a first flow path through the pump assembly and delivers a fluid through this first flow path. The impeller in the second position is situated in a second flow path through the pump assembly and delivers a fluid through this second flow path. The pump assembly (2) is configured such that a movement of the impeller (18), between the first and the second position at least in one direction, is effected by a hydraulic force which acts on the impeller (18) and is produced by the delivered fluid. A heating installation is provided with such a pump assembly.

Abstract: A centrifugal compressor to be used in a chiller system includes a casing, an impeller, a motor and a diffuser. The casing has an inlet portion and an outlet portion. The impeller is attached to a shaft rotatable about a rotation axis, and has an impeller shroud which encloses the impeller. The motor rotates the shaft in order to rotate the impeller. The diffuser is disposed in the outlet portion downstream of the impeller. The centrifugal compressor further includes a seal bearing. The seal bearing is attached to the inlet portion to seal the impeller shroud, and rotatably supports the impeller and the shaft.

Abstract: A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion.

Abstract: A method for repairing a blade connection of a generator rotor is disclosed. The generator rotor includes an internally threaded hole formed in the generator rotor and an externally threaded blade root. The method includes the steps of removing the blade from the generator rotor, removing material of a first section of the root extending from an end of the root closest to the airfoil, and screwing the blade back into the threaded hole. Additionally, a reworked blade and a reworked blade generator rotor connection is disclosed.

Abstract: A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner.

Abstract: The invention relates to an autogyro having a rotor (12). According to the invention, a gas pressure spring (32) is provided and is arranged for trimming the rotor (12).