A compressor system includes a compressor housing and a driveshaft rotatably supported within the compressor housing. The compressor system further includes an impeller that imparts kinetic energy to incoming refrigerant gas upon rotation of the driveshaft, a thrust disk coupled to the driveshaft, and a bearing assembly mounted to the compressor housing. The impeller includes an impeller bore having an inner surface, and the thrust disk includes an outer disk and a hub. The bearing assembly rotatably supports the outer disk of the thrust disk. The hub is disposed within the impeller bore, and includes a hub outer surface in contact with the inner surface of the impeller bore. A first contact force between the hub outer surface and the inner surface of the impeller bore increases with increased rotational speed of the driveshaft.

A method of repairing a piston seal assembly comprises removing worn material from a piston seal groove to generate a worked seal groove, applying a groove buildup member to the worked seal groove, and disposing a seal member proximate the groove buildup member.

A gas turbine engine has: a first component and a second component defining a respective first gaspath surface and a second gaspath surface of an annular gaspath, the first and second gaspath surfaces axially spaced apart from one another by an annular recess in the first component; a bushing ring disposed within the annular recess and defining stem pockets therein; variable guide vanes pivotable about respective vane axes extending between first and second stems; and a biasing member received within the annular recess and disposed axially between the bushing ring and one of the first component and the second component, the biasing member exerting a force against the bushing ring in an axial direction relative to the central axis and towards the other of the first component and the second component.

A thermal shielding arrangement for a turbine probe extending through an exhaust case and a turbine housing of a gas turbine engine comprises a sleeve having a radially inner end fixedly mounted to the turbine housing and a radially outer end floatingly received in a probe boss on the exhaust case. The radially outer end of the sleeve opens to an air cavity between the exhaust case and a surrounding engine nacelle to allow for air circulation around the probe.

A variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.

A rotor has a rotor body having: a flange with a circumferential array of discontiguous apertures; and a surface spaced apart from the flange. One or more rotor balance weight assemblies each have a weight and a fastener. The weight has: a passageway having a first end and a second end; an internal thread along the passageway; and a boss at the first end of the passageway. The boss is in a respective one of the apertures. The fastener has: a shank having a first end and a second end and an external thread engaged to the passageway internal thread; an engagement feature at the shank first end for engagement by a tool to turn the fastener; and a head at the second end contacts the surface.

A rotor blade for a gas turbine, in particular an aircraft gas turbine, including a blade root, a blade neck that adjoins the blade root in the radial direction, an airfoil that adjoins the blade neck in the radial direction, a radially outer partition wall that forms a radially inner delimiting section of an annular space of a gas turbine, an axially front partition wall and an axially rear partition wall that are connected to the radially outer partition wall so that the partition walls surround the blade neck on three sides, the partition walls protruding beyond the blade neck in the circumferential direction. For placement in a blade root receptacle of a rotor disk, the rotor blade is provided with a blade root protective plate that is situated between the blade root and the rotor disk. The blade root protective plate includes at least one sealing section that extends in the axial direction from the front partition wall to the rear partition wall, and whose radial outer side is situated opposite from the radially outer partition wall when the blade root protective plate is situated at the blade root. One or multiple ribs are situated at the blade neck for supporting the sealing section and are integrally joined to the blade neck.

A variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.

A valve for an air system in an aircraft engine, comprising: a housing defining a chamber having a valve axis circumscribed by a sealing surface; and a piston assembly within the chamber including: a sealing ring; and a body extending annularly about a piston axis collinear with the valve axis, having a first and a second piston surface axially spaced apart, a radially outer piston surface extending axially and located between the first and second piston surfaces, and an annular groove extending radially inwardly from the radially outer piston surface having first and second groove walls spaced apart and axially facing one another, the sealing ring within the annular groove, the body including: a first member defining the first piston surface and the first groove wall; and a second member defining the second piston surface and the second groove wall, the first member and the second member in mating engagement.

A blower includes a drive device, a shaft, a fan and a rotation limiter member. The fan includes: a main plate that has an axial hole which is securely press-fitted to the shaft; a shroud that is opposed to the main plate and has a suction inlet, which is formed at a center part of the shroud; and a plurality of blades that are placed between the shroud and the main plate and are arranged one after another around a central axis of the fan. The rotation limiter member is fixed to the shaft and the main plate. The main plate includes: a slope portion that is placed on an outer side of the rotation limiter member; and at least one planar surface part which is perpendicular to the central axis and is formed around the central axis at a part of the slope portion.