The invention relates to an abradable coating for a turbomachine, comprising a mineral compound having a Mohs hardness of 6 or less and a melting temperature of more than 450° C. or even 800° C., and a polymeric compound with a content of between 40% and 70% by volume.

Disclosed is a covering of a fan unit of an information handling system. The covering contains a bottom covering and a top covering. The bottom covering contains i) copper and an first aluminum alloy, or ii) 10 wt. % to 50 wt. % of a thermally conductive plastic, and 50 wt. % to 90 wt. % of a post-consumer-recycled (PCR) plastic and/or biodegradable plastic. The top covering contains copper and a second aluminum alloy. The bottom covering houses a motor and blades of a fan of the fan unit, the top covering abuts against the bottom covering, and the fan is positioned in a space formed between the bottom and top covering. Fan unit containing the covering, and an information handling system containing the fan unit is also disclosed.

A non-collapsible flexible sealing membrane (or bellows) for incorporation in a mechanical seal assembly and use in rotary shaft equipment. The sealing membrane includes a substantially radially outward extending first flange portion, which can be urged into an axially shiftable ring by a biasing mechanism. The sealing membrane further includes a substantially axially outboard extending second coaxial portion, substantially radially inward of the balance diameter of the seal. The horizontal portion is advantageously held fixed to a stub sleeve by an annular band. The angle between the vertical portion and the horizontal portion of sealing membrane enables directional control of the forces acting on stub sleeve and primary ring.

A rotor assembly being an injection molded piece, and comprising a first shaft sleeve and a rotor; a first injection molded body is formed by using the rotor and the first shaft sleeve as injection molding inserts to pass through injection molding; a second injection molded body is formed by at least using the first injection molded body as an injection molding insert to pass through injection molding; the second injection molded body comprises a lower cover plate and a wrapping layer, the wrapping layer wrapping around at least a portion of the outer peripheral surface of the first injection molded body; the rotor assembly further comprises blades, the blades being fixedly connected to the lower cover plate or the blades forming an integrated structure with the lower cover plate.

A method is provided involving a fairing for a turbine engine. During this method, a detail is provided. The detail includes a carrier and an exterior layer bonded to the carrier. The carrier is configured from or otherwise includes fiber-reinforced composite material. The exterior layer is configured from or otherwise includes polymer material. The detail is arranged with the fairing. The fairing includes an exterior side and an edge. The detail covers and extends along at least a portion of the exterior side. The detail wraps at least partially around the edge. The carrier and at least a first overhang portion of the exterior layer are bonded to the fairing.

An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.

A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

A composite platform for a fan of an aircraft turbine engine. The platform includes an elongate wall and is configured to extend between two fan blades. The wall includes an aerodynamic outer surface and an inner surface, on which a fastening tab is located, wherein the fastening tab is configured to be attached to a fan disc. The fastening tab is integrally formed with a metal reinforcement which has a plate having an elongate shape and which extends over more than 50% of the longitudinal extent of the wall, the wall being produced by overmolding a resin on the plate so as to be integrated into the wall.

A bearing assembly for a turbo-engine with a bearing and parts of a bearing temperature detecting device. The bearing includes a main body having a thermoplastic bearing layer. A space is defined in the interior of the main body and of the thermoplastic bearing layer for accommodating parts of the bearing temperature detecting device. The space has a through hole having a first opening in the thermoplastic bearing layer and a second opening located in the main body. The parts include a temperature conducting element, a temperature sensor, and a securing fixture that attaches the temperature conducting element. The first opening of the through hole has a chamfer and the first end of temperature conducting element has a head which is correspondingly shaped to the chamfer in a form fitting manner. The center-axis of the temperature sensor extends transversely to the center-axis of the temperature conducting element.

The invention relates to a side-channel compressor (1) for a fuel cell system (37) for conveying and/or compressing a gaseous medium, in particular hydrogen, comprising a housing (3); a compressor chamber (30) which is situated in the housing (3) and which has at least one encircling side channel (19, 21); a compressor impeller (2) which is situated in the housing (3) and which is arranged so as to be rotatable about a rotational axis (4), wherein the compressor impeller (2) has conveying cells (5) arranged on the impeller circumference in the region of the compressor chamber (30); and in each case one gas inlet opening (14) formed on the housing (3) and one gas outlet opening (16), which are fluidically connected together via the compressor chamber (30), in particular the at least one side channel (19, 21). The housing (3) has a respective first and second end face (32, 34) radially to the rotational axis (4), each end face facing the compressor impeller (2), and a first and second functionally relevant gap dimension (36, 38) is formed in the region of each gap surface. According to the invention, the compressor impeller (2) is designed in multiple parts and has a first impeller shell (10) and a second impeller shell (12). The impeller shells (10, 12) are arranged adjacently to each other axially to the rotational axis (4) in particular, and each impeller shell is at least partly made of a plastic.