The present invention provides a centrifugal multistage compressor adapted to inhibit corrosion of an intermediate stage labyrinth. More particularly, the present invention provides a centrifugal multistage compressor adapted to inhibit carbon dioxide corrosion of the intermediate stage labyrinth. The centrifugal multistage compressor of the present invention includes: a rotary shaft equipped with a plurality of impellers; an ejection flow path extended between a first stage of the impellers and a last stage of the impellers and serving to discharge a fluid once from the compressor; a suction flow path extended between the first stage of the impellers and the last stage of the impellers and serving to inject the discharged fluid once again into the compressor; an intermediate diaphragm disposed between the ejection flow path and the suction flow path; and an intermediate stage labyrinth for sealing between the ejection flow path and the suction flow path, and has a configuration where the intermediate diaphragm includes a bypass flow path for supplying the intermediate stage labyrinth with some of the fluid flowing to the ejection flow path.

The present invention relates to a modularized pump. The pump has end lids 12, 13 with an inlet and an outlet for pumped fluid, and at least two pump modules 7 sandwiched between the end lids 12,13. Each pump module includes a casing 1 with an enclosed volume 20 and at least two pump stages 6. At least one coolant inlet 10 and outlet and a separate power connection 16 for connection to a VSD is included in each module. Each pump stage 6 includes an impeller 5 with a rotor 4, a stator 2 surrounding the rotor 4, provided to drive the rotor and a can 3 between the impeller 5 and the stator 2.

A fan motor includes: a motor housing; a rotating shaft; a rotor; a stator disposed outside the rotor; an impeller having at least one blade and a hub; and an impeller cover surrounding an outer circumference of the impeller and defining an air suction inlet. The impeller cover includes: a shroud having an inner diameter that expands in an air flow direction; and a non-metallic coating layer coated on an inner circumferential surface of the shroud and having a lower strength than the blade. The non-metallic coating layer includes: a first area having a first thickness; a second area having a second thickness thinner than the first thickness and defining a stepped portion with the first area, thereby minimizing leakage flow caused by the pressure difference from a pressure-side surface to a suction-side surface of the blade to reduce flow path loss and improving efficiency of the fan motor.

A small gas turbine engine, such as is used to power a UAV, that includes at least one centrifugal compressor having an impeller with blades that form a gap between the blade tips and stationary shroud of the gas turbine engine, and where a resistance heating element is secured to or bonded to a compressor casing of the gas turbine engine in order to use heat to control the gap between the impeller blades and the stationary shroud. The resistance heating element is activated at cruise mode to move the shroud toward the impeller. Additionally or alternatively, the compressor casing is heated with bled-off compressed air to move the shroud toward the impeller. A capacitance tip clearance sensor can be mounted on the impeller shroud to monitor and control tip clearance in real time.

A turbomachine housing element, having a flow channel for accommodating a rotor blade assembly and a first cavity at least partially produced by primary shaping; the first cavity being adapted for passive thermal insulation and/or the assemblable turbomachine housing element not being adapted for the active circulation of fluid through the first cavity; and/or, between the first cavity and the flow channel, a separate seal being attached to turbomachine housing element; and/or the first cavity extending in the axial direction of the flow channel over at least 20% of a minimum axial length of the turbomachine housing element at the level of the cavity and/or over a minimum axial length of the separate seal and/or being filled with air or a thermally insulating fluid, whose specific thermal conductivity λ is at least 10% lower than the specific thermal conductivity λ of air.

A seal assembly for use in a turbomachine, the seal assembly comprising an oil seal plate; a rotatable component which defines a central axis and is received in a central aperture of the oil seal plate; and an annular seal which comprises a base and a sealing portion, the base being held by the rotatable component; wherein the sealing portion is configured to form a seal with the oil seal plate when the rotatable component and annular seal are rotating below a predetermined rotational speed; and wherein the sealing portion is configured to move radially outwards with respect to the central axis such that the sealing portion loses contact with the oil seal plate when the rotatable component and annular seal are rotating above the predetermined rotational speed.

A centrifugal pump includes a radial impeller surrounded by a housing. The housing has a channel associated with a front side space between a cover of the impeller and the casing. Flow is led through the channel from a pressure region of the pump to a radial gap at a suction region of the pump. The flow in the channel reduces angular momentum and results in an increase in pressure in the front side space which acts of in the cover side of the impeller to offset axial force from a rear side of the impeller.

A radial fan (1) is provided with a motor (2) and a fan housing, an outer part (4) and an inner part (5) that form a spiral-like pressure chamber (D). A pressure connector (33) which forms an outlet (44) of the radial fan (1) is arranged on the outer part. The fan housing is equipped with a fan wheel (3) which is arranged on a shaft (7) connected to the motor (2), wherein an annular flow divider (8) which surrounds the fan wheel (3) is arranged adjacently to the fan wheel (3) in a radial direction. The flow divider together with the fan housing forming a diffuser (9), which transitions directly into the pressure chamber (D), about the fan wheel (3).

A centrifugal pump which includes a tubular structure which extends into an eye of an impeller and which directs a medium to be pumped into the eye, and wherein an axially extending annular cylindrical sealing clearance is formed between opposing surfaces of the impeller and the structure.

In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90°.