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 centrifugal compressor assembly is provided. The centrifugal compressor assembly includes a scroll assembly having a suction plate defining an inlet fluid passage, a suction plate housing, a diffuser plate, and a collector. The suction plate is detachably coupled to the suction plate housing, the suction plate housing is detachably coupled to the collector, and the diffuser plate is detachably coupled to the collector. The centrifugal compressor assembly further includes an impeller rotatably mounted in the scroll assembly for compressing fluid introduced through the inlet fluid passage, and a variable geometry diffuser system.

This compressor inserting and removing device (1) is provided with: an intermediate supporting portion (4) which supports a bundle (32), prior to insertion from a horizontal axis (L1) direction into a compressor casing (34) taking the form of a tube centered around the horizontal axis (L1), from an outer peripheral side of the bundle (32), at a position that is closer to the insertion side of the bundle (32) than an end portion (32d) on the side opposite to the insertion side of the bundle (32); a moving portion (10) which makes it possible for the intermediate supporting portion (4) and the compressor casing (34) to move relative to one another in the horizontal axis L1 direction; a threaded rod (12) which extends parallel to the horizontal axis (L1), and which is fixed at a distal end (12a) thereof to a fixing hole (34b) formed in an end surface (34a) at the insertion side of the compressor casing (34), and which passes through through-holes (6a and 7a) formed in the intermediate supporting portion (4); and a nut (13) which is attached to the threaded rod (12), in such a way as to be capable of coming into contact with the intermediate supporting portion (4), from the side that is closer to the rear end portion (32d) of the bundle (32) than the intermediate supporting portion (4).

A compressor housing for a turbocharger including a housing body having an inner circumferential recess recessively formed on an annular inner circumference surface thereof; an annular abradable seal disposed in the inner circumferential recess, an inner circumference surface of which forms a shroud surface; and a ring member formed in a ring shape along the inner circumferential recess and press-fitted into the inner circumferential recess. The inner circumferential recess includes a recess press-contact surface that is formed along a press-fitting direction of the ring member, and press-contacts a radial-direction outside surface of the ring member; and a recess opposing surface that opposes a press-fitting direction forward surface of the ring member. The abradable seal includes a flange that projects outwardly in a radial direction of the abradable seal. The flange is held between the press-fitting direction forward surface and the recess opposing surface to fix the abradable seal.

A geared compressor includes a plurality of compression units and a compression-unit-driving mechanism which drives the plurality of compression units. The compression-unit-driving mechanism includes a plurality of driven gears which are provided in respective rotation shafts of the plurality of compression units and a plurality of large-diameter gears which are directly or indirectly driven by a drive source and have outer diameters larger than those of the plurality of driven gears. The plurality of large-diameter gears is arranged side by side in a horizontal direction and each of the plurality of large-diameter gears meshes with two or more of the plurality of driven gears.

Turbomachines such as air dynamometers are disclosed that include a radial outflow compressor and gas collector. In some examples, the gas collector is designed as a separate component that is coupled to the machine, such as coupled to a frame. In some examples, the collector and frame are intentionally spaced and coupled at discrete points to minimize the transfer of mechanical and thermal energy therebetween. Aspects of the present disclosure also include turbomachines that include at least one impeller bypass flow path for the direct transfer of air between ambient and a location in the collector downstream of the impeller blades. In some examples, such flowpath(s) may allow for the inflow of external ambient air into the collector.

A motor assembly includes an impeller, a first diffuser at a downstream side of the impeller, a second diffuser at a downstream side of the first diffuser, an impeller cover coupled to the second diffuser and accommodating the impeller and the first diffuser, and a motor provided at the downstream side of the second diffuser to drive the impeller. The second diffuser includes a hub, an outer wall concentrically disposed outside the hub, and a plurality of blades having one side connected to the hub and the other side connected to the outer wall. The impeller cover is coupled to the outer wall of the second diffuser. A communicating portion for allowing fluid communication between inside and outside of the hub of the second diffuser is provided at the hub of the second diffuser.

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

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 thermal driver coupled between the impeller shroud and engine casing by hinged linkages. The thermal driver includes an annular ring and annular seal which together define thermal driver cavity. Relatively warm or relatively cool air supplied to the thermal driver cavity cause expansion and contraction, respectively, of the annular ring which is translated by linkages into axially forward and aft motion, respectively.