A vacuum pump comprises: a rotor; a stator; a first heating section configured to heat the stator cylindrical portion to a temperature for reducing product accumulation; an exhaust pipe provided at a housing storing the rotor and the stator to discharge gas discharged by the rotor and the stator to an outside of the housing; a second heating section configured to heat the exhaust pipe to a temperature for reducing product accumulation; and a gas passage container arranged in the housing, having an inlet port into which gas discharged through a gap between the rotor cylindrical portion and the stator cylindrical portion flows and an outlet port from which inflow gas flows to the exhaust pipe, and heated to a temperature for reducing product accumulation. A gas-inflow-side end portion of the exhaust pipe is inserted into the outlet port of the gas passage container through a clearance.

A turbocharger is provided and includes a compressor housing and a recirculation slit and a recirculation passage provided at an inlet of the compressor housing to enable air flowing into the compressor to be recirculated. A gas supply part supplies blow-by gas towards the inlet of the compressor housing to allow blow-by gas to be joined with air recirculated through the recirculation slit and the recirculation passage and to guide recirculating air towards a compressor wheel.

A diffuser for a compressor of a gas turbine engine is disclosed. The diffuser has a plurality of diffuser pipes circumferentially distributed about an axis of the compressor, each of the plurality of diffuser pipes extending from an inlet to an outlet and having a bend section between the inlet and the outlet, a low pressure side and an opposite high pressure side. A recirculation conduit defines a recirculation path from a first flow region to a second flow region in one or more of the plurality of the diffuser pipes, the first flow region having a greater static pressure than that of the second region, the recirculation conduit having a conduit inlet and a conduit outlet, at least the conduit outlet located within the low pressure side of one of the plurality of the diffuser pipes.

The invention relates to a blade assembly 30 for a large dimension axial fan 32 having a rotation axis X. The blade assembly of the invention comprises: a root structure 34 intended to mechanically connect the blade assembly to a hub 36; a blade, wherein at least one portion of the blade has a composite airfoil 46 comprising a fore semi-airfoil 48 and an aft flap 50, wherein: the semi-airfoil is intended to be assembled at a predefined pitch angle α.sub.c with respect to the hub 36 by means of the root structure; the flap 50 is mounted on the blade such that it can be fixed in a position comprised between a maximum deflection position and a minimum deflection position with respect to the pitch angle α.sub.c; and between the fore semi-airfoil and the aft flap a channel 54 is defined suitable for allowing a fluid flow from the face v to the back d of the composite airfoil. The invention further relates to a fan comprising a plurality of blades.

A fan includes blades and a side plate. The side plate includes a fan ring portion having a cylindrical shape centered on a fan axis. A guide part that is annular is arranged on one side of the fan ring portion in the axial direction and forms a suction port through which the air sucked into the fan passes. A communication path that allows an upstream space located on the one side in the axial direction with respect to the guide part to communicate with a gap between the fan ring portion and the guide part is formed outside the guide part in a radial direction of the fan axis. The fan ring portion is located outside in the radial direction with respect to an innermost peripheral portion of the guide part located on an innermost side in the radial direction.

The present invention relates to a jet structure of a fan rotor, which comprises a fan wheel and at least one connecting channel. The fan wheel has a hub and plural blades disposed on the circumferential side of the hub. The hub has a top portion and a sidewall. Each of the blades has an upper surface and a lower surface which form a high-pressure zone and a low-pressure zone, respectively. The connecting channel is provided with at least one first inlet disposed in the high-pressure zone and at least one first outlet disposed in the low-pressure zone. The first inlet and the first outlet are a first end and a second end of the connecting channel, respectively. By means of the design of the present invention, the effect of noise reduction can be achieved.

A method to control flow separation over an airfoil, turbine blade or compressor blade includes providing an airfoil having a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge; providing a flow separation control device having a plurality of openings on the upper surface of the body and a plurality of capillary tubes in gaseous communication with the plurality of openings; and injecting gas through the plurality of capillary tubes into a portion of the airstream passing over the uppers surface of the body.

An impeller includes a shroud including an inlet, a hub facing the shroud; and a plurality of blades disposed between the hub and the shroud and arranged circumferential direction along a circumference of the inlet. Wherein each of the plurality of blades has a slot which is positioned adjacent to the inlet.

A compressor for a heating, ventilating, air conditioning, and refrigeration (HVAC&R) system includes an impeller that has a hub defining an impeller tip, a plurality of blades coupled to the hub and defining a plurality of flow paths configured to direct a primary flow of working fluid therethrough, and a shroud coupled to the plurality of blades. The shroud includes a shroud tip disposed upstream of the impeller tip relative to a flow direction of the primary flow of working fluid through the plurality of flow paths.

A combination of an airfoil, turbine blade, or compressor blade with a flow separation control device includes an airfoil, a flow separation control device, and an injection system. The airfoil includes a body with an upper surface and a lower surface that extend from a leading edge to a trailing edge. The flow separation control device includes a plurality of openings on the upper surface of the body. The injection system includes an inlet tube, a pump in gaseous communication with the inlet tube, and a flow regulator in gaseous communication with the pump and the plurality of capillary tube.