A turbocharger includes a turbine housing, an annular metal plate, and a scroll passage defining plate. The metal plate defines a connecting passage in the turbine housing. The connecting passage connects a turbine chamber and a turbine scroll passage to each other. The scroll passage defining plate includes a passage defining portion that defines the turbine scroll passage and an inner circumferential edge portion that extends from the inner circumferential edge portion of the passage defining portion and along the metal plate. The scroll passage defining plate has an inner circumferential edge that is fixed between the turbine housing and the metal plate. The scroll passage defining plate is arranged in the turbine housing such that the outer circumferential edge portion of the passage defining portion is movable relative to the turbine housing.

A turbomachine component, particularly a gas turbine engine component, has at least one part built in parts from a curved or planar panel, particularly a sheet metal, the part having a plurality of cooling channels via which a cooling fluid, particularly air, is guidable, wherein at least one of the plurality of cooling channels has a continuously tapered section. The at least one of the plurality of cooling channels has a single inlet port from a first surface of the panel and a single outlet port for the cooling fluid to another surface, particularly a surface opposite to the first surface, or to the first surface. Further the panel is built via laser sintering or laser melting or direct laser deposition. A gas turbine engine is equipped with such a component. A method of manufacturing includes incorporating cooling channels having a continuously tapered section.

A vane arc segment includes an airfoil piece that has a first platform, a second platform, and an airfoil section between the first platform and the second platform. At least the first platform is formed of a fiber-reinforced composite (FRC) and defines a radial flange. A cap is fitted on the radial flange.

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 turbine housing includes: a scroll section configured to internally define a spiral space; a cylindrical exhaust gas introduction section having an exhaust gas introduction port and configured to internally define a connection passage connecting the exhaust gas introduction port and the spiral space; a sheet metal inner scroll member disposed in the spiral space to form a first heat-shielding space between the inner scroll member and an inner surface of the scroll section and configured to internally define a spiral flow passage through which exhaust gas entering through the exhaust gas introduction port flows; and a sheet metal inlet member separate from the inner scroll member, disposed in the connection passage to form a second heat-shielding space between the inlet member and an inner surface of the exhaust gas introduction section, and configured to internally define a connection flow passage connecting the exhaust gas introduction port and the spiral flow passage. An upstream end portion of the inner scroll member and a downstream end portion of the inlet member overlap along an axial direction of the exhaust gas introduction section.

An object of the present invention is to provide a turbine external compartment, a frame for a turbine external compartment, and a method of constructing a frame for a turbine external compartment that can improve a flow of steam inside of the compartment and can enhance the rigidity of the compartment using a simple structure. A turbine external compartment according to the present invention is placed in a frame having a steel-plate reinforced concrete structure obtained by filling a space between a plurality of steel plates with concrete. The turbine external compartment includes a lower half part having a side plate part or an end plate part made of the steel plates that constitute the frame.

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.

A turbocharger includes a variable turbine nozzle formed between first and second walls. A variable-vane assembly has a fixed nozzle ring and a plurality of circumferentially spaced vanes disposed in the nozzle and rotatably mounted on the nozzle ring such that the vanes are pivotable. The nozzle ring defines the first wall of the turbine nozzle, each vane having a first end adjacent the first wall and a second end adjacent the second wall. The second wall of the turbine nozzle is formed by a gas pressure-responsive member that is arranged to be axially movable relative to the vanes. A first stop is positioned so that the gas pressure-responsive member is urged against the first stop by a differential gas pressure exerted on the gas pressure-responsive member so that there is a non-zero first value for a clearance between the second ends of the vanes and the second wall of the turbine nozzle.

Turbine housing assemblies and related fabrication methods are provided. A turbine housing assembly includes a bearing flange, a tongue member, a first sheet metal structure providing an inner contour of an inlet passage and joined to the tongue member, and a second sheet metal structure including an inlet portion providing an outer contour of the inlet and a volute portion providing an outer contour of a volute in fluid communication with the inlet. The volute portion is joined to the tongue member to define the volute, and the inlet portion of the second sheet metal structure is joined to the first sheet metal structure to define the inlet passage.

During operation, a bladed rotor disk typically experiences out-of-plane vibration which can result in deterioration and/or cracking at the interface between adjacent shrouds of the turbine blades. In an embodiment, slots are formed at the end of a labyrinth seal segment of each shroud. Preloaded spring strips are inserted through the slots to couple adjacent shrouds while preventing the natural frequency of the turbine blades from drifting to the operating speed range and/or providing vibration damping to the untuned blade mode.