Embodiments provide an integrated motor-compressor assembly including a rotating impeller to compress a fluid passing therethrough, and diffuser vanes radially spaced from the impeller, each of the diffuser vanes including a stator winding therearound, the stator windings being supplied with current to generate sufficient magnetic flux for rotating the impeller. Embodiments provide an integrated motor-compressor assembly including a volute casing housing a rotating impeller to compress a fluid passing therethrough, a stator fixedly positioned in the volute casing proximate to the impeller, the stator including stator poles axially spaced from the impeller, each of the stator poles including a stator winding, the stator windings being supplied with current to generate sufficient axial magnetic flux for rotating the impeller.

A compressor housing may include a shroud portion which is axially spaced from an inlet portion and configured to at least partially surround the compressor wheel. The compressor housing may be further configured to include a recirculation cavity which is formed between an exterior surface of the shroud portion and an interior surface of the compressor housing. Furthermore, a recirculation slot may define an airflow pathway between the recirculation cavity and the compressor wheel. Additionally, the compressor housing may include an angled shroud support extending radially through the recirculation cavity from the exterior surface of the shroud portion to the interior surface of the compressor housing. The angled shroud support may be spaced an axial distance away from the recirculation slot to reduce turbulence in the airflow as the airflow moves from the recirculation cavity to the compressor wheel.

An impeller of a centrifugal compressor according to the present disclosure includes: a hub; a plurality of full blades disposed on a peripheral surface of the hub at intervals in a circumferential direction; and a plurality of splitter blades each of which is disposed between adjacent full blades of the plurality of full blades on the peripheral surface of the hub. When a blade height ratio which is a ratio of a blade height (Hf) of each full blade to a blade height (Hs) of each splitter blade on a meridional plane of the impeller is defined as Hs/Hf, the blade height ratio satisfies Hs/Hf<1 at least at a leading edge of each splitter blade.

Provided is a method of manufacturing an impeller assembly, the method including providing an impeller including: a rotary shaft; a base portion radially extending outward from the rotary shaft; and a plurality of blades extending radially outward from the rotary shaft and disposed on the base portion, each of the plurality of blades provided apart from one another in a circumferential direction around the rotary shaft; providing a mold in an area between the plurality of blades; and forming a shroud covering upper portions of the plurality of blades and an upper portion of the mold, wherein the forming the shroud comprises applying a melted metal on the upper portions of the plurality of blades and the upper portion of the mold.

A state observation device (30) uses an ADC (37) to digitize a detection signal from a gap sensor (21) at a low-speed sampling period and uses a separation unit (38) to separate the digitized detection signal into vane detection signals considered to be for the detection of a vane of a compressor impeller and non-vane detection signals considered not to be for the detection of a vane. Further, the determination unit (39) extracts a vane peak detection signal considered to be for a vane peak by comparing a vane detection signal with vane detection signals corresponding to other vanes and non-vane detection signals, and a shaft vibration and tip clearance are determined as states of the compressor impeller on the basis of the extracted vane peak detection signal. Thus, the state observation device (30) is capable of observing the state of a rotary machine without carrying out high-speed sampling.

A method of manufacturing a component of a rotary machine, the component has at least one inner passage that extends from a center up to a boundary surface of the component and is at least partly closed, and a blank is provided that includes the boundary surface and a top surface. The Method includes a first subtractive machining step that is carried out in which a part of the passage that at least includes an opening of the passage into the boundary surface as well as a cut-out in the top surface are manufactured by machining production, and subsequently the passage is completed by build-up production on the blank.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a two-piece integral impeller shroud with a fixed inner member and a variable outer member. An actuator is coupled to an aft end of the variable outer member and imparts axially forward and aft motion on the aft end, causing deflection of the outer member.

A centrifugal compressor including: a casing; at least one impeller supported for rotation in the casing and provided with a hub, a shroud and an impeller eye; an impeller-eye sealing arrangement, for sealing the impeller in the region of said impeller eye. The centrifugal compressor further includes at least one cooling-medium portlocated at the impeller-eye sealing arrangement, arranged for delivering a cooling medium around the impeller eye.

Compressor rotor structure and methodology for harmonizing compressor aerodynamics and rotordynamics are provided. Disclosed embodiments benefit from a compressor design effective for improving rotordynamics (e.g., stiffer rotor structure) without reducing a usable aerodynamics range of the compressor. This design may involve variation of the rotor structure along the rotor axis to locate respective surfaces defined by respective inlets of the one or more impellers at a varying distance relative to the rotor axis based on respective ratios selected for the configuration of the impeller bodies. This arrangement may be effective for improving rotordynamics while satisfactorily meeting the respective varying aerodynamics requirements at the various compression stages by the impeller bodies.