A helical coiled seal for sealing a barrel-shaped cylinder piston-cylinder assembly, comprising: a piston-sealing C-shaped ring; a connecting C-shaped ring comprising an inward wing protruded inwardly from a section near a first end on an inner perimeter of the connecting C-shaped ring, and an outward wing protruded outwardly from a section near a second end on an outer perimeter of the connecting C-shaped ring; and a cylinder-sealing C-ring; wherein the piston-sealing C-ring is connected end-to-end to the first end of the connecting C-ring and cylinder-sealing C-ring is connected end-to-end to the second end of the connecting C-ring forming a three-ring helical structure having a contraction-dilation response time sufficiently short required for the up-down stroke speed of the cylinder piston-cylinder assembly.

The invention relates to a method for manufacturing a turbine shroud (24) for a turbomachine, the method comprising manufacturing at least one turbine shroud sector (28), positioning the turbine shroud sector (26) in a bottom mold so that an outer surface of the turbine shroud sector is in contact at least in part with the bottom mold, and depositing a powder layer on an inner surface (28) of the turbine shroud sector (26). Thereafter, a top mold is positioned on the powder layer and an abradable layer (32) is made by subjecting the powder layer to a method of SPS sintering, the abradable layer (32) being for being disposed facing a turbine wheel.

A method for the construction of bladed rings for radial turbomachines, including: preparing an annular block; roughing the annular block by removing material to define a first, second, third and fourth axial section, wherein the first axial section defines a reinforcement ring, wherein the third axial section defines a base ring; roughing the second axial section by removing material to delimit a plurality of separate elements, wherein the separate elements axially connect the base ring to the reinforcement ring; finishing each of the separate elements by removing material to provide the separate element with the shape of an airfoil blade, wherein a leading edge of the blade and a trailing edge of the blade develop substantially parallel to a central axis of the bladed ring; roughing the fourth axial section by removing material for delimiting an annular anchoring appendage of the base ring to a radial turbomachine.

A method of forming a guide vane is disclosed. The method includes forming a vane blank with sufficient material to fabricate the guide vane in accordance with any one of a plurality of different vane classes. The vane blank is inspected for material inconsistencies, and material is removed from the vane blank to form a desired guide vane in accordance with one of the plurality of vane classes. The inspection process includes disregarding at least one material inconsistency in a region of the vane blank that is removed to form the guide vane.

An exhaust-gas turbocharger (1) having a turbine housing (2) which has a turbine spiral (16); and a compressor housing (3) which has a compressor spiral (17). An internal flow-guiding spiral surface (18 or 19 respectively) of the turbine spiral (16) and/or of the compressor spiral (17) is machined in a material-removing process.

A method for manufacturing a blisk includes an intermediate product molding step of molding a blisk intermediate product including a circular disk-corresponding part, a plurality of rotor blade-corresponding parts, and bridges each connecting a front edge of one of each pair of the rotor blade-corresponding parts adjacent to each other and a rear edge of the other one of the rotor blade-corresponding parts. The method for manufacturing the blisk further includes a disk finishing step of cutting the disk-corresponding part so as to finish the disk-corresponding part into the disk in a product form, and a rotor blade finishing step of cutting each bridge so as to finish the respective rotor blade-corresponding parts into the respective rotor blades in a product form.

A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered projecting from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered projecting from and formed in one piece with the coupling root; an upper connecting fin cantilevered projecting 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 turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered projecting from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered projecting from and formed in one piece with the coupling root; an upper connecting fin cantilevered projecting 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 component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment.

Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.