The present disclosure relates to a bearing supporting assembly and a machining method thereof, and a centrifugal compressor. The bearing supporting assembly includes: bearing supports, provided with through holes for mounting radial bearings; and a fixing plate, detachably mounted at one end of each of the bearing supports along an axial direction, sides, away from the bearing supports, of the fixing plates being configured to mount first thrust bearings.

The present disclosure relates to an impeller and a method of manufacturing the same. The impeller includes: a hub in which a plurality of spiral first slots are formed; a shroud which is positioned opposite the hub, and has a plurality of spiral second slots formed therein; and a plurality of blades which is coupled to the hub and the shroud, and have an upper protrusion formed on one side and a lower protrusion formed on the other side; and wherein the upper protrusion is inserted into and coupled to a second hole formed in the second slot, and the lower protrusion is inserted into and coupled to a first hole formed in the first slot.

The disclosure relates to an asymmetrical double-outlet blower, including an upper case, a lower case and an impeller. The upper case includes an inlet. The lower case and the upper case are assembled to form a housing having an accommodation space, and form a first outlet and a second outlet. The accommodation space is in fluid communication with the first outlet, the second outlet and the inlet. The first outlet and the second outlet are disposed on a lateral periphery of the housing and face two opposite directions, respectively. An opening cross-sectional area of the first outlet is less than an opening cross-sectional area of the second outlet. The impeller is accommodated within the accommodation space of the housing, spatially corresponding to the inlet, and rotated around a rotation axis. An airflow is inhaled through the inlet and transported to the first outlet and the second outlet, respectively.

A compressor comprises a compressor housing, a compressor wheel mounted within the housing and having compressor blades, and a bearing housing. The compressor housing comprises a cover member and a diffuser member that is connected to both the cover member and the bearing housing. The diffuser member has a radially outer portion connected to the cover member and a radially inner portion connected to the bearing housing. The diffuser member has a first weakened region defined at a first position intermediate the radially outer portion and the radially inner portion, and a first strengthened region defined at a second position intermediate the radially outer portion and the radially inner portion, said second position being radially inwards or outwards of the first weakened region.

An alignment tool for aligning a plurality of diffuser pipes of a centrifugal compressor relative to a casing of an aircraft engine. The alignment tool includes a body defining a center axis and having at least one tool datum configured for abutting against the casing. A plurality of alignment members are fixed to the body and extend radially from the body relative to the center axis. Each alignment member of the plurality of alignment members has a respective fixed position relative to the at least one tool datum. The plurality of alignment members are configured to abut the plurality of diffuser pipes.

A suspending tool includes a suspending tool main body that extends to be parallel with an axial direction above a rotor main body, a pair of bearing supporting portions that are disposed at an interval in the axial direction and are detachable from the bearing portions, a pair of seal supporting portions that are disposed inside the pair of bearing supporting portions in the axial direction at an interval in the axial direction and are detachable from the seal portions, and a plurality of diaphragm supporting portions that are disposed inside the pair of seal supporting portions in the axial direction such that the diaphragm supporting portions are disposed at intervals in the axial direction and are detachable from the diaphragms.

A rotor loading system for an aircraft turbine engine has a first tool having first proximal and first distal ends. The first proximal end defines a traction interface about a first axis and a first surface radially outward of the traction interface. The first distal end defines first projections spaced circumferentially and extending to outward of the first surface. The system has a second tool with second proximal and second distal ends. The second proximal end defines a torque interface about a second axis and a second surface radially outward of the torque interface. The second distal end defines second projections spaced circumferentially and extending to outward of the second surface. One of the first and the second tool is received by the other one of the tools such that: the first and the second axis are colinear and each of the first projections is received between two second projections.

A compressor system includes: a first compressor including a first casing having a cylindrical shape, and a first bundle capable of being inserted into and pulled out from the first casing in an axial direction of the first casing; and a second compressor including a second casing having a cylindrical shape, and a second bundle capable of being inserted into and pulled out from the second casing in an axial direction of the second casing. The first and second compressors are arranged to face each other to cause pullout directions of the respective bundles to be opposite to each other. A maintenance space shareable for insertion and pullout operations of the first bundle and insertion and pullout operations of the second bundle is interposed between the first bundle and the second bundle, and is available for the bundle under the insertion and pullout operations.

A blower may include a first case and a second case provided above the first case and having a first tower and a second tower that have a passage therebetween. A display assembly is received in the second case at a position that does not interfere with air flowing in the passage. An inner surface of the second tower and an outer surface of a diffuser define a space in which the display assembly is received.

A fluid compressor device includes an integrated controller of an e-machine. The integrated controller has an arcuate support structure that extends about the axis of rotation of a rotating group. The support structure has a seat that is disposed at a radial area of the arcuate support structure. The integrated controller has an electronics component supported on the seat. The integrated controller includes a retainer clip that is resiliently flexible between a neutral position and a flexed position. The retainer clip is fixed to the support structure and in the flexed position to retain the electronics component on the seat.