Am aircraft engine including an axially extending inlet wall surrounding an inlet flow path. A radial distance between the inlet wall and the inner wall adjacent the fan defines a downstream height of the inlet flow path. A plurality of vanes are circumferentially spaced around the inlet, each of the vanes extending radially inwardly from the inlet wall, a maximum radial distance between a tip of each of the vanes and the inlet wall defining a maximum height of the vane. The maximum height of the vane is at most 50% of the downstream height of the flow path. In another embodiment, the maximum height of the vane is at most 50% of the maximum fan blade span. A method of reducing a relative Mach number at fan blade tips is also discussed.

A fan impeller includes a hub, a shaft, a metal housing, a magnetic ring and a plurality of blades. The outer periphery of the hub has a curved surface. The shaft is disposed in the hub and connected to the hub. The metal housing has an annular shape and is disposed in the hub. The magnetic ring is disposed at the inner side of the metal housing. The blades are disposed around the outer periphery of the hub.

A drive includes a dynamoelectric rotational machine, an electronic add-on part, and a fan unit arranged axially behind one another. The fan unit generates a cooling air flow and is embodied as a two-zone fan having axial fan elements which define a first zone to generate essentially an axial air flow and include an articulated joint with an elastic region with sufficient restoring force, and radial fan blades which define a second zone that radially adjoins the first zone and generate essentially a radial air flow. Free spaces are provided at least between a housing arrangement and the fan unit and/or between the housing arrangement and a bearing shield of the dynamoelectric rotational machine and/or between the housing arrangement and/or a shaft of the dynamoelectric rotational machine, with the free spaces being acted upon during operation of the fan unit by the cooling air flow and a Venturi effect.

A radial fan (1) or centrifugal blower is provided having a fan housing (2) with a spiral pressure chamber (D) and a rotor assembly (10) comprising an internally axially open bearing tube (20), in which a shaft (40) carrying a fan wheel (30) is mounted with a rotor (50) of a canned motor. An air-guiding channel (L) between a first pressure-chamber region (2a) and a second pressure-chamber region (2b) of the spiral pressure chamber (D) is formed between the bearing tube (20) and the wall (W) of the canned motor, so that an air flow flows through the air-guiding channel (L) from one pressure-chamber region (2a, 2b) to the other and in the process dissipates heat from the bearing tube (20) into the pressure chamber (D).

A pump arrangement including a magnetic clutch pump arrangement, the pump arrangement including an inner chamber formed by a housing arrangement, a separating can which hermetically seals a chamber enclosed by it with respect to the inner chamber, an impeller shaft that can be driven in rotation about an axis of rotation, an impeller arranged on one end of the impeller shaft, an inner rotor arranged on the other end of the impeller shaft, a drive device, a drive shaft that can be driven in rotation about the axis of rotation by the drive device, and an outer rotor arranged on the drive shaft and cooperating with the inner rotor. The outer rotor includes a first carrier element and a second carrier element connected to the first carrier element. The first carrier element includes a thermal barrier device.

A turbo-molecular pump comprises: a turbine pump portion having rotor blades and stator blades arranged in multiple stages in an axial direction; a drag pump portion provided on a downstream side of the turbine pump portion; a case housing the turbine pump portion; a base housing the drag pump portion; and a temperature adjustment unit provided between the case and the base. The temperature adjustment unit includes a temperature adjustment spacer forming a pump casing together with the case and the base and, the temperature adjustment unit includes a cooler, a heater, and a temperature detector which are provided at the temperature adjustment spacer.

An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.

A vacuum pump and a vacuum pump rotor blade that can effectively limit deposition of reaction products are provided. The vacuum pump includes a rotating shaft held rotationally, a drive mechanism for the rotating shaft, a first rotor blade made of a first material, a second rotor blade made of a second material having higher heat resistance than the first material, and disposed further toward a downstream side than the first rotor blade, and a casing enclosing the rotating shaft, the first rotor blade, and the second rotor blade. The second rotor blade is disposed, via a heat insulating portion, on the first rotor blade.

A rotor for a machine under this disclosure could be said to include a hub having a plurality of blades extending radially outwardly of the hub. At least one of the hub and the plurality of blades is formed of at least two metal materials. The two metal materials are selected to have different thermal expansion coefficients such that the overall rotor will be more resistant to forces it may experience as temperature or speed increases. There are layers of each of the two metal materials, with an intermediate gradient wherein the two materials are mixed. Alternatively, a shape memory alloy may be used. A method is also disclosed.

A turbocharger includes a turbine housing that is a cast component, a turbine scroll passage, a discharge port, and a discharge port defining member. The turbine scroll passage surrounds the circumference of a turbine chamber defined in the turbine housing and the circumference of the turbine chamber. Exhaust gas that has passed through the turbine chamber is conducted to the discharge port. The discharge port defining member constitutes a wall surface of the discharge port. The discharge port defining member includes a tubular main body wall and an outer circumferential edge. The main body wall constitutes a wall surface of the discharge port. The outer circumferential edge extends from the distal end of the main body wall and outward in the radial direction of the impeller shaft. The outer circumferential edge is fixed between the turbine housing and a downstream exhaust pipe, which is connected to the discharge port.