Methods and apparatus are provided for an axi-centrifugal compressor in a gas turbine engine for a business aviation or rotorcraft propulsion unit. The compressor includes an axial compressor section operable to affect a first pressure ratio along the flow path between a compressor inlet and a first section exit, and a centrifugal compressor section operable to affect a second pressure ratio along the flow path between a second section inlet and the compressor exit. The pressure rise across the axial and centrifugal compressor section is configured to have a tuning factor is in a range between 2.8 and 4.5 and a loading factor in a range between 0.6 and 0.8.

An apparatus is disclosed. The apparatus has a first housing having a first cavity, a second housing disposed in the first housing and including a second cavity and at least one aperture, a first fan assembly configured to generate a first airflow through the first housing, and a second fan assembly configured to generate a second airflow from the second cavity to the first cavity via the at least one aperture.

A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.

An auxiliary shaft seal flushing system of a centrifugal pump and an axial flow pump, comprising a main running pump and a standby pump which are provided with a same shaft seal flushing system respectively, the shaft seal flushing system of the main running pump and that of the standby pump being connected in parallel to form a common shaft seal flushing system. The common shaft seal flushing system comprises: a first outlet pipe connected to an outlet of the main running pump and a first switch valve provided on the first outlet pipe for switching the flushing fluid, a second outlet pipe connected to an outlet of the standby pump and a second switch valve provided on the second outlet pipe for switching the flushing fluid, and a first fluid guide pipe connected to the outlets of the first outlet pipe and the second outlet pipe; the outlet of the first fluid guide pipe is respectively connected to a flushing fluid inlet on a sealing gland of the main running pump by a third outlet pipe and connected to a flushing fluid inlet on a sealing gland of the standby pump by a fourth outlet pipe. The present invention can keep the parameters of the fluid material in sealed cavities of the main and standby pumps the same at all times.

A compressor wheel for a turbocharger includes a hub portion defining a rotational axis and a plurality of blades extending radially outward from the hub portion. Each blade of the plurality of blades includes a leading edge, the leading edges of each blade of the plurality of blades forming an inducer portion of the compressor wheel. Each blade of the plurality of blades further includes a trailing edge, the trailing edges of each blade of the plurality of blades forming an exducer portion of the compressor wheel. The inducer portion is positioned longitudinally forward from the exducer portion along a rotational axis with respect to a flow of air along the compressor wheel. The hub portion and the plurality of blades include a substrate metal. The substrate metal of the hub portion and the plurality of blades has coated directly thereon a first coating layer including electroless nickel-phosphorous. The first coating layer has coated directly thereon a second coating layer including hard chrome. The second coating layer has a thickness that is greatest at the inducer portion, with the thickness of the second coating layer decreasing rearward towards the exducer portion such that the thickness of the second coating layer is about zero microns at or longitudinally forward of the trailing edges of each blade of the plurality of blades.

A composite cooling fan includes a frame, a fan blade and a lateral valve. The frame has an air hole penetrating the frame and a lateral air outlet locating on one side of the frame and connecting with the air hole. The fan blade is disposed in the air hole and includes an impeller, multiple axial blades surrounding the impeller and multiple centrifugal blades surrounding the axial blades. The lateral valve is disposed on the lateral air outlet and includes a valve stem and a switch baffle linked with the valve stem. The valve stem is used for making the switch baffle at the lateral air outlet open or close.

A refrigerant compressor assembly (20A, 20B, 20C) includes an axial compressor (22B, 22C, 22) that includes at least one axial stage. A downstream compressor (24) is located fluidly downstream of the axial compressor (22B, 22C, 22) and includes one of a mixed-flow impeller (46) or a centrifugal impeller (96). At least one motor (26, 27) is in driving engagement with at least one of the axial compressor (22B, 22C, 22) and the downstream compressor (24).

A gas compressor comprising a drum affixed to a rotating shaft, the drum including a plurality of compression channels between a common pressure zone and an interior surface of the drum distal to an axis of rotation. A static vane return assembly adjacent the compression channels includes vanes extending from an inlet at an outer circumference to the common pressure zone and directing gas into the common pressure zone, either through the vanes or via separate channels or ducts. Fluid inside the rotating dmm forms an annular lake that is drawn through the vanes and into the common pressure zone. Fluid is then forced into the compression channels where gas in the fluid is compressed as it travels from the common pressure zone toward the interior surface. The pressurized gas is separated from the liquid prior to leaving the compression channel assembly while the liquid is returned to the lake.

A turbocharger includes a compressor housing, a turbine housing, a bearing housing, a variable nozzle unit, and a fixing member. The variable nozzle unit includes a first plate, a second plate, a plurality of nozzle vanes, and an attitude changing mechanism. The fixing member includes an engagement portion that is engaged with at least one of the first plate and the second plate, a through shaft portion shaped to extend through the bearing housing toward the compressor housing, and a fixing portion that fixes an end portion of the through shaft portion on the compressor housing side to the hearing housing.

A diffuser for a radial compressor of a turbomachine is provided. The diffuser has a plurality of diffuser channels, wherein the diffuser channels extend across a radial area of the diffuser across a bent area into an axial area of the diffuser, wherein, in the radial area of the diffuser, the diffuser channels have diffuser walls in particular at v-shaped blades that are bent in the movement direction of the radial compressor or are straight.