A rotor wheel for an engine includes a plurality of impeller vanes and a plurality of fluid passages defined by adjacent impeller vanes. The fluid passages are radially disposed across at least a portion of the rotor wheel. One or more impeller inserts may be disposed within one or more of the plurality of fluid passages, respectively. The impeller inserts define an impeller passage with a passage shape that controls a flow of fluid through the one or more of the plurality of fluid passages.

Profiled blade for a fan wheel, with a profile body produced from at least one curved metal strip, whereby adjacent end zones of the at least one metal strip are connected to each other in an adhesively bonded and/or form-fit manner wherein a second end zone at a distance from a second end zone edge is equipped with at least one embossed area for forming a contact surface enabling a first end zone to, at least in sections, be brought into contact with it.

A monopropellant thruster according to an exemplary aspect of the present disclosure includes, among other things, a first part having a catalyst bed, a thrust chamber, and a nozzle. The first part is integrally formed via a single additive manufacturing process. The thruster further includes a second part, which is a closeout. A method is also disclosed.

Embodiments of the present invention relate to an inner casing component configured to form part of a steam flow path of a last stage of an axial flow steam turbine, the steam turbine inner casing component having a base made of nodular cast iron and a coating, on the base, in a region exposed to the steam flow path, consisting of manganese austenitic steel.

The present disclosure relates to a rotor for a gas turbine having a plurality of rotor disks arranged one behind the other in a rotor axis and connected to one another, where the geometrical form of the disks leads to the formation of cavities between adjacent disks. The rotor extends from a compressor part to a turbine part and has a central part between the compressor part and the turbine part, wherein the first turbine disk, the last compressor disk and the central part enclose a central cavity. A cooling system extends at least partially through the rotor with a central cooling section disposed between at least one inlet pipe and at least one outlet pipe, at least partially through the first turbine disk and/or the last compressor disk.

A lever for a VTG guide vane arrangement of a radial turbine with a main body with a fork-shaped coupling section with two limbs. A wear-resistant contact block is arranged on an inner side of at least one of the limbs. The wear-resistant contact block is designed for operative engagement with an adjusting ring of the VTG guide van arrangement, giving rise to the effect of increased wear resistance at least in the region of the engagement with the VTG guide vane arrangement. Furthermore, a VTG guide vane arrangement having such a lever, a radial turbine having such a VTG guide vane arrangement, and a supercharging device having such a radial turbine.

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 turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.

An impeller (100) for a fluid pump according to the present invention comprises a shroud (150) that has a disk shape and is drivingly rotated about a center axis, and a cover (110) comprising a cover main body (120) having a truncated cone shape with an inlet port (123) for a fluid formed at a center and a plurality of blades (130) arranged around a center axis of the cover main body (120). The cover (110) and the shroud (150) are joined to each other with a welding contacting portion (135) and a welding contacted portion (177) welded to each other in a center axis direction, in a state where another end surface of the shroud (150) and a distal end portion (131) of the blades (130) are in parallel with each other.

Disclosed is an adjustable guide vane for a turbomachine, especially for a turbine stage or compressor stage of a gas turbine, which comprises a vane airfoil for deflecting a working fluid of the turbomachine and which is produced at least partially from a second material, and at least one first vane section which is produced from a first material which is different from the second material.