A method of replacing a module in a modular gas turbine engine having a first fan module; a first propulsor module including an engine core and a gearbox; and a first fan case module having a fan case; includes the steps of: disassembling the gas turbine engine, replacing one of the fan module, propulsor module or fan case module with a replacement fan module, a replacement propulsor module or a replacement fan case module, the replacement module, having the same configuration as the first module; and reassembling the gas turbine engine using the replacement module.

The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising:a step of producing a blank from at least two parts (50, 51), at least one of which is a solid part, the at least two parts being assembled by a diffusion connection technique and without melting, anda step of machining this blank in order to produce a blade with a defined profile.

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 compact axial turbine configured to operate with high density working fluid is described. The turbine comprises an axial majority cantilevered turbomachinery shaft. Rotor assemblies and nozzle spacers communicate torque through turbine shaft splines, allowing them to be slid off the shaft for quick replacement in the field. The compact axial turbine houses turbomachinery within a separable inner casing encircled by a cartridge sleeve, thereby forming a cartridge which can itself be removed as a single component.

The present invention relates to a method for obtaining a solid blade of a turbomachine, comprising a core, a tip and a root, the method comprising: a step of producing a blank from at least two parts (50, 51), at least one of which is a solid part, the at least two parts being assembled by a diffusions connection technique and without melting, anda step of machining this blank in order to produce a blade with a defined profile.

A method for producing turbine rotor blades or the base bodies thereof includes a) providing the base body, which has, following one another along a longitudinal axis, a blade root, a blade platform and a blade airfoil, b) sensing a value of at least one parameter of the base body, at least one of the parameters representing a vibrational property of the base body, c) comparing the sensed value with a predetermined target interval, d) if the sensed value lies outside the target interval, reducing the mass of the base body, wherein the reduction of the mass takes place at the blade root and/or on the blade platform by introducing at least one recess and/or by reducing a dimension below the corresponding target value.

A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.

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.

The invention relates to mechanical engineering, namely to pumping installations designed for pumping water, water solutions, as well as oil, oil products and the like through the main, process and auxiliary pipelines, and is directed toward providing a single-stage centrifugal pumping unit which demonstrates peak efficiency in non-nominal modes while having a simplified design and being universal in nature. To this end, a single-stage centrifugal pumping unit comprises a centrifugal single-stage double entry pump, an electric drive motor, a coupling, connecting their shafts, a support frame for mounting the pump housing and the electric motor thereon, a housing, which consists of a base and a cover, inlet and outlet manifolds, a rotor with an impeller mounted thereon, the rotor being installed in support bearings, and a volute configured according to the invention in the form of a separate, independent component, and parts of the outside surface thereof, which are intended to be accommodated in cradles provided for this purpose in the cover and the housing, correspond to the shape of the surfaces of said cradles. The impeller and the volute are replaceable as a pair, the parameters of the impeller and the volute in each pair are calculated to provide maximum efficiency while ensuring the requisite feed and pressure. The replaceable volutes are made as an integrated cast component and comprise a baffle separating the fluid flow during the movement.

The invention relates to a method for manufacturing an abradable plate (32) for a turbomachine turbine shroud (24, 26), the method comprising preparing a mixture comprising a cobalt- or nickel-based metal powder and a powder based on a fluxing element, depositing a layer of the powder mixture in a mold, and making the abradable plate (32) by subjecting the powder mixture layer to a method of SPS sintering.

The invention also provides a method of preparing a turbine shroud (24, 26) for a turbomachine.