A stator wheel for a turbomachine turbine. This wheel includes an inner shroud formed by an upstream portion and a downstream portion configured to be assembled with the blades by axial translation in a respective direction.

The invention relates to a bearing assembly for an exhaust gas turbocharger for rotatably supporting a rotor shaft on a bearing housing, having at least one bearing outer ring of a radial bearing, which at least one bearing outer ring is placed in a bearing bore of the bearing housing and consists of at least one part, and at least one securing element, which consists of at least one part and by which the bearing outer ring is axially fastened in relation to the bearing housing. In order to simplify the assembly of a corresponding bearing assembly and to reduce the production costs thereof, at least one circumferential groove, according to the invention, is arranged on an outer lateral surface of a compressor-side end section of the bearing outer ring, in which at least one groove the securing element engages, and the securing element is arranged outside of the bearing bore on the compressor side and is supported at least indirectly on a compressor-side end of the bearing housing.

A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ≤2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

A turbine vane assembly adapted for use in a gas turbine engine includes a spar, a turbine vane, and load transfer pins. The spar comprises metallic materials and is configured to support other components of the turbine vane assembly relative to an associated turbine case. The turbine vane comprises ceramic matrix composite materials and is shaped to include an airfoil configured to direct the flow of hot gasses through a primary gas path of the turbine vane assembly.

A turbine nozzle assembly for use in a turbine engine is provided. The assembly includes an inner barrel and a turbine nozzle support ring. The inner barrel has a forward end and an aft end. The turbine nozzle support ring includes an annular body that defines a forward end, an opposite aft end, an inner surface, and an opposite outer portion. The forward end of the annular body is coupled to the aft end of the inner barrel. The annular body includes a first arcuate segment and a second arcuate segment removably coupled to the first arcuate segment. The first arcuate segment has a first arcuate length and the second arcuate segment has a second arcuate length. The second arcuate length is shorter than the first arcuate length.

The composite seal structure includes a carrier ring and a seal element housed in an annular groove formed between a circumferential outer wall and two side walls of the carrier ring. The seal element has a first region in surface-to-surface contact with the annular groove and a second, seal-ing region protruding from the annular groove. A fastening arrangement couples the seal element and the carrier ring to one another. The fastening arrangement comprises a plurality of fastening pins circumferentially arranged around the axis of the carrier ring. Also disclosed is a method for manufacturing the seal structure.

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.

For alignment of rotational shafts, two devices for attachment to circular faces of two shaft segments. Each of the two devices has a laser photoelectric device for ascertaining a dimension of displacement of the two shafts from a desired axis of rotation relative to each other. Each of the two devices having a base surface with two linear contact edges designed to engage with a circumferential surface of a shaft and to ensure alignment between the device and an axis of rotation of the shaft to within a tolerance compatible with alignment tolerances of the shaft. Each of the two linear contact edges includes at least two terminal end regions and a center region together defining a line contact at linear intersection of two surfaces meeting at a non-zero angle linear contact edges designed to affix and release from the shaft surface, and to ensure parallel alignment between the device and an axis of rotation of the shaft to a precision allowing measurements to within tolerances required by machinery driven by the shaft. The base surface of at least one of the devices has been modified from its commercially-delivered condition to provide raised rails designed to improve tactile feedback of to a user of the alignment between the base and an axis of rotation of the shaft, and has affixed thereto two rails designed to improve tactile feedback of to a user of the alignment between the base and an axis of rotation of the shaft. Each base has a magnet and a switch to vary magnetic flux for affixation and release from the shaft surface. Each device has brackets designed to securely and reproducibly position laser photoelectric devices relative to the base and axis of rotation of the shaft. The attaching includes a human placing at least one of the devices slightly askew relative to the axis of rotation of the shaft, and the human gently twisting the device to allow the liner contact edges to seat on the circumferential surface of the shaft, to provide tactile feedback to the human to confirm parallel alignment between the at least one device's laser photoelectronic device and the axis of rotation of the shaft.

A ceiling fan assembly having a motor with a rotor with multiple blade mounts, multiple blades having a removable blade tip, a balancing weight mount carried by the multiple blades and covered by the removable tip, and where each of the multiple blades are pre-balanced and indexed to a corresponding one of the multiple blade mounts.