A rotor for a fluid machine includes a wheel that is supported for rotation about an axis of rotation. The wheel includes a back wall with an outer rim edge. The rotor also includes a plurality of blades that are attached to the back wall and that are spaced apart about the axis of rotation. Moreover, the rotor includes an inter-blade area on the back wall between neighboring ones of the plurality of blades. Furthermore, the rotor includes a balancing feature that is included in the inter-blade area on the back wall. The balancing feature intersects and defines part of the outer rim edge.

A mixed-flow turbine wheel includes: a plurality of rotor blades disposed on a circumferential surface of the hub at intervals in a circumferential direction and configured such that each of the plurality of rotor blades has a leading edge which includes, in a meridional view, an oblique edge portion where a distance between the leading edge and an axis of the rotational shaft decreases from a tip side toward a hub side, and a sensor detection surface having a flat shape and being applied with a marking which is detectable by an optical sensor device. The sensor detection surface is formed on at least one of the circumferential surface of the hub or an edge portion of a reference rotor blade being one of the plurality of rotor blades, such that, in the meridional view, a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the sensor detection surface is smaller than a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the oblique edge portion.

A turbine wheel for a hydrokinetic torque converter. The turbine wheel is rotatable about a rotational axis and comprises a substantially annular turbine shell member coaxial with the rotational axis, and a plurality of turbine blade members axially extending from the turbine shell member. The turbine wheel is a single-piece component such that the turbine blade members are unitarily formed with the turbine shell member. The turbine wheel (22) is made by an additive manufacturing process from a polymeric material.

Methods of balancing a workpiece, in which the workpiece is rotated about an axis of rotation. The forces and/or torques that result from an unbalance of the workpiece during the rotation of the workpiece are measured, and material is removed from the workpiece to reduce the unbalance. The method includes removal of material from the rotating workpiece during measuring or as the workpiece is continuously rotated between measuring and material removal.

Methods of balancing a workpiece, in which the workpiece is rotated about an axis of rotation. The forces and/or torques that result from an unbalance of the workpiece during the rotation of the workpiece are measured, and material is removed from the workpiece to reduce the unbalance. The method includes removal of material from the rotating workpiece during measuring or as the workpiece is continuously rotated between measuring and material removal.

A rotor disk for an exhaust turbocharger is mounted in a housing of the exhaust turbocharger so as to be able to rotate about an axis of rotation. The rotor disk has a disk hub including a disk back and a disk front facing away from the disk back. A plurality of rotor disk blades are formed on the disk hub in a manner extending between the disk back and the disk front. A balancing mark is arranged in a blade channel formed between a first blade of the plurality of rotor disk blades and a second blade, arranged adjacent to the first blade, of the plurality of rotor disk blades. The balancing mark is triangle-like. The disclosure also relates to an exhaust turbocharger comprising such a rotor disk and to a method for balancing a rotor assembly for such an exhaust turbocharger.

For a vulcanized tire, after executing a third inspection step of inspecting an internal defect, a first inspection step of inspecting uniformity and a second inspection step of inspecting dynamic balance are executed. For the tire of which an internal defect is detected in the third inspection step, the first inspection step and the second inspection step are not executed and the inspection is over.

For a vulcanized tire, after executing a third inspection step of inspecting an internal defect, a first inspection step of inspecting uniformity and a second inspection step of inspecting dynamic balance are executed. For the tire of which an internal defect is detected in the third inspection step, the first inspection step and the second inspection step are not executed and the inspection is over.

This invention relates to both process and tooling for machining exemplary Hamilton Sundstrand 7111 and 7121 aircraft propeller blade taper bores, or equivalent to comply with government and or industry standards or specifications for such refurbishment. The tooling and process invented are an Improvement over previous and current taper bore machining methods in improved repeatability and cost effectiveness, as this machining method can quickly and repeatedly machine propeller blades to meet fit, form, and function requirements. The process makes use of a specially constructed horizontal mill, specially constructed blade-holding fixture, specially constructed probing system, specially constructed reamers, and specially constructed air gauges. A blade holding fixture assembly including a base plate, a blade holding fixture and a blade alignment fixture hold an aircraft propeller blade in a horizontal milling machine for refurbishment of the taper bores. Refurbishment includes reaming shot peened surfaces, testing the reamed surfaces with an air gauge and a fluorescent penetrant emersion fixture.

This invention relates to both process and tooling for machining exemplary Hamilton Sundstrand 7111 and 7121 aircraft propeller blade taper bores, or equivalent to comply with government and or industry standards or specifications for such refurbishment. The tooling and process invented are an Improvement over previous and current taper bore machining methods in improved repeatability and cost effectiveness, as this machining method can quickly and repeatedly machine propeller blades to meet fit, form, and function requirements. The process makes use of a specially constructed horizontal mill, specially constructed blade-holding fixture, specially constructed probing system, specially constructed reamers, and specially constructed air gauges. A blade holding fixture assembly including a base plate, a blade holding fixture and a blade alignment fixture hold an aircraft propeller blade in a horizontal milling machine for refurbishment of the taper bores. Refurbishment includes reaming shot peened surfaces, testing the reamed surfaces with an air gauge and a fluorescent penetrant emersion fixture.