A method for creating an impeller and an impeller of a radial turbo fluid energy machine includes a wheel disc, cover disc, blades, and hub. The hub is mounted on a shaft which extends along an axis, the wheel disc extends substantially radially from the hub, and the cover disc is connected to the wheel disc by the blades such that flow channels separated from one another in the circumferential direction are defined by the blades. The impeller has a first flow passage in a substantially axial direction in the radial proximity of the hub, and the impeller has a second flow passage in a substantially radial direction radially farther away from the hub than the first flow path passage. The cover disc surface facing the wheel disc has a lower degree of roughness at least in some regions than the wheel disc surface facing the cover disc.

An axial- or diagonal-fan has a fan wheel (34) having profiled rotor blades (32). Each blade has a suction or intake side (46), a portion located forward, with respect to the rotation direction (36), and having a leading edge (44), and a portion located rearward, with respect to the rotation direction (36), and having a trailing edge (92). Between said portions, on the intake side (46) of the respective rotor blade (32), a trip or separation edge (66) is provided, said trip edge having an S-shaped contour in a meridian cross-section.

A centrifugal compressor having at least a diffuser is disclosed. The diffuser has an annular diffuser body having circumferentially spaced apart diffuser passages defining fluid paths through the diffuser body. The diffuser also has a plurality of diffusion members mounted to the annular diffuser body. Each diffusion member has a member inlet in fluid communication with a diffuser passage and a member outlet. Each diffusion member defines an aerodynamic throat disposed between the member inlet and the member outlet. The diffuser also has a fluid injection assembly with multiple injection conduits. Each injection conduit extends between a conduit inlet configured to receive a flow of compressible fluid from a supply and a conduit outlet communicating with a corresponding diffusion member downstream of the aerodynamic throat. The compressible fluid is injected through the conduit outlet into the diffusion members.

Centrifugal compressors can incorporate a side stream flow of intermediate pressure vapor between stages of that compressor. The side stream flow can be controlled by a side stream injection port controlled by a throttle ring disposed between stages of the compressor. The throttle ring can allow or obstruct flow through the side stream injection port. The throttle ring can extend and retract in a direction substantially perpendicular to the direction of flow from the first stage impeller to the second stage impeller. A method of operating a centrifugal compressor can include actuating a throttle ring by rotating a drive ring to adjust a flow of interstage fluid into the second stage impeller.

A multi or single-stage turbocompressor with at least one compressor wheel fastened to a shaft. The shaft is mounted in a turbocompressor housing which, behind the hub disc of the compressor wheel, includes an interior housing region as well as in front of the hub disc of the compressor wheel a front interior housing region. The driven compressor wheel delivers a fluid from an inlet channel to an outlet channel. The front interior housing region includes a wheel lateral space from which an extraction channel for the extraction of fluid is provided.

An arrangement for intentionally mistuning a cavity formed adjacent an impeller in a turbomachine, the arrangement including at least two bladed elements defined within a perimeter of a casing wall adjacent the impeller, wherein the bladed elements are configured to mistune cavity acoustic modes to minimize acoustic pulsations in the cavity.

An arrangement for intentionally mistuning a cavity formed adjacent an impeller in a turbomachine, the arrangement including at least two bladed elements defined within a perimeter of a casing wall adjacent the impeller, wherein the bladed elements are configured to mistune cavity acoustic modes to minimize acoustic pulsations in the cavity.

A return stage of a radial turbo fluid energy machine, in particular of a radial turbo compressor, having an axis of rotation, the return stage has an annular flow channel for feeding a flowing process fluid from a flow opening of a first impeller to a flow opening of a second impeller arranged downstream. In order to increase efficiency, the flow channel is defined by bounding surface areas, of which at least one certain rough area extending in the circumferential direction has a surface roughness that is increased in relation to the her areas.

An example centrifugal compressor includes a housing that defines an inlet chamber and includes first and second openings that define a recirculation passage in fluid communication with the inlet chamber. An impeller is disposed within the housing and is rotatable about a longitudinal axis to draw fluid into the inlet chamber. The first and second openings are at different axial locations along the longitudinal axis. A plurality of inlet guide vanes are rotatable and situated in the inlet chamber. The centrifugal compressor includes a ring and a controller for moving the ring along the longitudinal axis between a first position and a second position when rotating the inlet guide vanes. The ring obstructs at least one of the first and second openings more in the second position than in the first position.

The present disclosure relates to a diffuser for a radial compressor. The diffuser may comprise a diffusor duct portion formed by first and second side walls that are arranged so as to diverge at least partially from one another in a direction of flow, a blade ring having a number of blades arranged at least partially in the diffusor duct portion with each blade having a pressure side and a suction side delimited by a blade leading edge and by a blade trailing edge of the respective blade, a number of pressure equalizing openings incorporated into at least one of the first and second side walls of the diffuser duct portion in a region where the first and second side walls diverge from one another with each of the pressure equalizing openings being arranged between the pressure side of one blade and the suction side of an adjacent blade of the blade ring, and a first annular duct arranged behind the pressure equalizing openings and fluidically connected to the diffuser duct portion via at least two of the pressure equalizing openings, such that a number of regions between two adjacent blades of the blade ring in the diffuser duct portion are fluidically connectable together.