Methods for manufacturing a tandem guide vane segment that includes an outer platform, a front guide vane, and a rear guide vane, wherein the front guide vane and the rear guide vane are arranged in a firmly fixated manner with respect to one another. One method includes manufacturing an integral front segment section that includes the front guide vane and a front section of the outer platform, manufacturing an integral rear segment section that includes the rear guide vane and a rear section of the outer platform, and connecting the two segment sections to each other.

A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending attachment feature that is received in the disk. The platforms each have an axially extending attachment feature that is received in the disk.

A strut and IGV configuration in a gas turbine engine positioned at an upstream of a rotor includes a plurality of radial struts, for example for bearing engine loads, and a plurality of inlet guide vanes positioned axially spaced apart from the struts. The number of inlet guide vanes is greater than the number of struts. The struts are circumferentially aligned with the inlet guide vanes.

A method of manufacturing a variable pitch torque converter stator includes positioning a framework, including an outer ring, a plurality of blades, a plurality of pivot members, and a plurality of actuation members, so the pivot members are seated in a stator body and the actuation members are coupled to a stator piston, with the pivot and actuation members being non-rotatably coupled to opposite ends of corresponding blades. The method includes removing the outer ring from the framework.

A method of fabricating a composite component is provided. The method includes manufacturing a cast metallic component including a surface and defining an attachment point along the surface, placing a fugitive mold defining an element feature against the surface such that the element feature aligns with the attachment point, filling the element feature with powdered metallic material and heating the cast metallic component and the powdered metallic material to a temperature above a sintering temperature of the powdered metallic material and below a melting temperature of the cast metallic component.

The present invention is directed to a method for producing a rotating disk for a turbomachine, forming blade root uptakes on a plurality of circumferential positions, for which, in each case, an axially extending profile groove that is bounded circumferentially by inner wall surfaces of the rotating disk is introduced on a respective circumferential position, in which production method, initially first profile grooves are introduced in a disk on first circumferential positions, and subsequently, a second profile groove is introduced in the disk on a second circumferential position located circumferentially between the first profile grooves.

Various implementations include a method of manufacturing a ring molded article. The ring molded article has two convex portions which respectively protrude on both sides of the ring molded article in a direction of a center axis thereof and extend in a direction of a circumference of the ring molded article. The ring material is placed inside two molds on which concave portions respectively corresponding to the convex portions are formed. The ring material is supported by a region on an outer peripheral side from an outer peripheral side corner in the concave portion of one of the two molds and a region on an inner peripheral side from an inner peripheral side corner in the concave portion of another of the two molds. The ring material is then forged so as to be pressed by the two molds in a direction of a center axis of the ring material.

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

A compressor wheel arrangement for an electrically powered turbocharger, which can be connected with a rotor shaft of the turbocharger, having a compressor wheel made of a first metallic material, a shaft made of a second metallic material, which is tightly connected with the compressor wheel, at least one permanent magnet, which is non-rotatably arranged on the section of the shaft, in a ring-shaped area around a section of the shaft that extends behind the compressor wheel, between a casing and the shaft.

A rotor for a turbomachine and a method of manufacturing the same. The method includes providing a lug with a lug body and an interface material disposed on the lug body. The method also includes friction welding the lug to a hub member via the interface material to define a projected structure for an outer radial area of a disc assembly of the rotor. The projected structure is configured to support a first side of a rotor blade of the rotor in cooperation with a second projected structure of the disc assembly supporting a second side of the rotor blade. The lug body and the hub member are made from different materials.