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 present disclosure generally relates to methods for additive manufacturing (AM) that utilize integrated ribs to support thin walled annular structures. An annular wall fabricated using AM has a thickness less than 0.022 inches across a majority of a surface of the annular wall and a plurality of ribs having a thickness greater than 0.030 inches. The annular wall has a mean thickness less than 0.100 inches. The annular wall conforms to a surface of the component and a mean distance between the annular wall and the component is less than 0.080 inches.

A turbine blade disposed along a radial direction of a turbine includes: an airfoil portion positioned in a fluid flow passage of the turbine; and a shroud portion positioned on an inner side or an outer side of the airfoil portion in the radial direction, and having an opening with which an end portion of the airfoil portion is to be engaged. A clearance is formed between a wall surface forming the opening of the shroud portion and an outer peripheral surface of the end portion of the airfoil portion. The wall surface of the shroud portion and the outer peripheral surface of the airfoil portion are joined to each other. At least one of the shroud portion or the airfoil portion has a cooling hole formed thereon, the cooling hole having an opening into the clearance and being configured to supply the clearance with a cooling fluid.

A moving blade 21d is disposed in a last stage closest to a diffuser 10 among a plurality of stages of a turbine 9 including a turbine rotor 12 and a stationary body 14. The diffuser 10 is connected to an outlet side of the stationary body 14. A distal end of the moving blade 21d is opposed to a seal fin 38 provided in the stationary body 14. The moving blade 21d includes a blade section 26, a cover 27 and a guide 32 provided on a moving blade distal end face 31, which is a surface of the cover 27. The moving blade distal end face 31 extends in a rotation axis direction of the turbine rotor 12, and the guide 32 includes a guide surface 41 located on a side close to the diffuser 10 with respect to the seal fin 38 and formed to incline upward in a direction from the seal fin 38 toward the diffuser 10.

A moving blade 21d is disposed in a last stage closest to a diffuser 10 among a plurality of stages of a turbine 9 including a turbine rotor 12 and a stationary body 14. The diffuser 10 is connected to an outlet side of the stationary body 14. A distal end of the moving blade 21d is opposed to a seal fin 38 provided in the stationary body 14. The moving blade 21d includes a blade section 26, a cover 27 and a guide 32 provided on a moving blade distal end face 31, which is a surface of the cover 27. The moving blade distal end face 31 extends in a rotation axis direction of the turbine rotor 12, and the guide 32 includes a guide surface 41 located on a side close to the diffuser 10 with respect to the seal fin 38 and formed to incline upward in a direction from the seal fin 38 toward the diffuser 10.

A turbine rotor blade that includes a tip shroud attached to the outboard tip of the airfoil. The tip shroud may include an axially and circumferentially extending planar component in which an inboard surface opposes an outboard surface, and a shroud edge that connects the inboard surface to the outboard surface and defines an outboard profile of the tip shroud. The tip shroud may include a seal rail protruding from the outboard surface of the tip shroud and a cutter tooth disposed on the seal rail. The cutter tooth may be formed as a circumferential section of the seal rail that is axially thickened. The seal rail may further include a leakage gap formed therethrough that is configured to increase a leakage level during operation.

A turbomachine blade system, in particular for a compressor or turbine stage of a gas turbine, which includes at least one blade, in particular a moving or guide blade, and at least one moving body for reducing the vibrations of this blade, at least one area of a guide for guiding the body and/or at least one area of a supporting structure for resiliently mounting the body and/or at least one area of the body being or becoming generatively manufactured together with at least one area of the blade, in particular of a vane and/or blade root and/or a shroud situated thereon.

A blade for a turbo machine is provided. The blade for a turbo machine includes an airfoil body extending in a radial direction and including a suction side surface and a pressure side surface opposite to the suction side surface with respect to a circumferential direction extending across the radial direction, and a snubber structure including a first snubber element protruding in the circumferential direction from the suction side surface of the airfoil body and a second snubber element protruding in the circumferential direction from the pressure side surface of the airfoil body, wherein the first snubber element is connected to the suction side surface of the airfoil body by a concave curved first transition portion having a first radius, and the second snubber element is connected to the pressure side surface of the airfoil body by a concave curved second transition portion having a second radius, the first radius being smaller than the second radius.

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 turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.