A variable nozzle device 20 for a variable geometry turbocharger includes: a nozzle mount 21; a nozzle plate 22 disposed so as to face the nozzle mount, the nozzle plate forming a nozzle flow passage 4 having an annular shape between the nozzle plate 22 and the nozzle mount 21; and a plurality of variable nozzle vanes 6 disposed at a predetermined interval in a circumferential direction of the nozzle flow passage 4 so as to be individually rotatable about a pivot axis 02. The nozzle plate 22 includes a first surface 33 facing the nozzle mount 21, a second surface 34 opposite to the first surface 33, and at least one through hole 36 formed through the first surface 33 and the second surface 35. The at least one through hole 36 has a first opening 36a formed on the first surface 33 at an inner side of the pivot axis with respect to a radial direction, and a second opening 36b formed on the second surface 35 at an outer side of the first opening 36a with respect to the radial direction or at the same position as the first opening 36a with respect to the radial direction. Accordingly, as the working fluid ‘g’ injected from the through hole 36 joins the working fluid G flowing through the nozzle flow passage 4 toward the turbine wheel 3 through the plurality of variable nozzle vanes 6, the flow of the working fluid G is guided toward the inner surface at the hub 32 side, and thereby it is possible to suppress deviation of flow of the working fluid G toward the shroud, that is, suppress the drift of the working fluid G.

A gas turbine engine has: an annular gaspath extending around a central axis and defined between a first casing and a second casing; and a variable guide vane (VGV) assembly having: variable guide vanes, the variable guide vanes having airfoils extending between first and second stems at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes; a unison ring rotatable about the central axis, the unison ring operatively connected to the variable guide vanes for rotating the variable guide vanes about the respective spanwise axes, and a segmented bushing having bushing segments circumferentially distributed around the central axis, the bushing segments radially supported and axially constrained by the first casing, the unison ring rollingly engaged to the first casing via the bushing segments, the unison ring axially and radially constrained to the first casing via the bushing segments.

The invention relates to a distributor for a turbomachine radial turbine, comprising an annular grill (26) extending about a central axis (10) and comprising a plurality of variable-pitch blades (31), defining between them an air passage cross section, characterized in that each blade is rotatably mounted about a pivot shaft (32), itself moveable in a translation direction, comprising at least one radial component, such that said blade may, upon actuation of control means (40), be pivoted about the pivot shaft and/or moved in relation to the central axis in said translation direction so as to be able to modify the air passage cross section by respectively controlling the metal angle (α3) and the radial spacing (ΔR).

The present application relates to an abnormality determination device for a variable geometry turbocharger having a nozzle mechanism capable of changing a flow path area of exhaust gas with an actuator. The abnormality determination device includes: a first detection part configured to be capable of detecting at least one of a load of the actuator or supply energy to the actuator; and a determination part configured to determine that an abnormality is present, if a detection result by the first detection part is out of an allowable range corresponding to an operational state of the variable geometry turbocharger.

A turbine impeller includes: a hub portion coupled to an end of a rotational shaft; a plurality of main blades disposed at intervals on a peripheral surface of the hub portion; and a short blade disposed between two adjacent main blades among the plurality of main blades. An inter-blade flow channel is formed between the two adjacent main blades so that a fluid flows through the inter-blade flow channel from an outer side toward an inner side of the turbine impeller in a radial direction. In a meridional plane, a hub-side end of a leading edge of the short blade is disposed on an inner side, in the radial direction, of a hub-side end of a leading edge of the main blade.

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

A rod assembly includes a turnbuckle that extends along a central axis, a first rod that is to be screwed into a first adjustment hole of the turnbuckle, a second rod that is to be screwed into a second adjustment hole of the turnbuckle, a first nut that is fitted to a first adjustment end portion of the first rod, and a second nut that is fitted to a second adjustment end portion of the second rod. A first turnbuckle-welded portion is provided between the first nut and the turnbuckle, and a second turnbuckle-welded portion is provided between the second nut and the turnbuckle. A first rod-welded portion is provided between the first nut and the first rod, and a second rod-welded portion is provided between the second nut and the second rod.

A disk spring may include an annular base body, a central longitudinal axis of which defines an axial direction of the base body. A profile of the base body in a profile plane containing the central longitudinal axis may have a wave-shaped contour with two minima including a radially inner minimum and a radially outer minimum and with an intermediate maximum disposed between the two minima. The wave-shaped contour may extend from a radially inner end point to a radially outer end point. The radially inner end point may be arranged offset in the axial direction with respect to the radially outer end point.

A variable capacity turbocharger includes: a nozzle flow path which allows a gas to pass from a scroll flow path toward a turbine impeller; a shroud side ring and a hub side ring which face each other in a rotation axis direction of the turbine impeller and form a nozzle flow path therebetween; a bearing hole which is provided in the shroud side ring; a bearing hole which is provided in the hub side ring; and a nozzle vane which is disposed in the nozzle flow path and is supported by both bearing holes, wherein a center axis line of the bearing hole is located on the inside in a radial direction in relation to a center axis line of the bearing hole at a room temperature and the center axis line is located on the outside in the radial direction in relation to the center axis line when a predetermined temperature difference is generated between the shroud side ring and the hub side ring during operation.

An impeller is configured to be rotated by a flowing fluid. A fluid stator includes a fixed ring parallel to a plane of rotation of the impeller. The fixed ring has a center in-line with a center of rotation of the impeller. A rotatable ring is rotatable relative to, and parallel to, the fixed ring. The rotatable ring has a center in-line with a center of rotation of the impeller. Stator vanes extend between the fixed ring and the rotatable ring. The stator vanes define an inlet cross sectional area upstream of the impeller. The cross sectional area is dependent upon a relative position of the fixed ring and the rotatable ring. An actuator is configured to rotate the rotatable ring. An electric rotor is coupled to, and configured to rotate in unison with, the impeller. An electric stator encircles the electric rotor. The electric stator includes coil windings.