An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.

A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.

A process for cold working of the inner surface of a bore in a centrifugal compressor wheel along only a fractional portion of the bore length (i.e., along less than a full axial length of the bore), thereby creating a zone of compressive residual hoop stress in the metal surrounding the bore where the wheel needs the beneficial residual stress. The process purposefully avoids cold working of the bore at locations adjacent to high-stress areas and features of the wheel, where cold working in such locations could negatively impact the wheel's overall life.

A manufacturing system manufactures a rotating assembly by attaching a plurality of attached target members in a circumferential direction of a rotating main body portion. A storage member capable of storing the plurality of attached target members is placed on a stand. A measurement device measures a physical amount of the attached target member An attachment device attaches one attached target member to a predetermined position in the circumferential direction of the rotating main body portion based on the physical amount measured by the measurement device A transfer device transfers the attached target member.

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.

In one aspect, a fan assembly is provided that can be manufactured while producing a significantly reduced amount of scrap material. More specifically, the fan assembly utilizes a hub ring and one or more hub strips to support a plurality of blades rather than a solid center disc or end disc used by some prior approaches. In another aspect, a method is provided that includes bending a member into an annular configuration and joining end portions of the member together to rigidly fix the member in the annular configuration. The rigid annular member may be used as an end ring, a hub ring, an orifice, or other component, while producing significantly less scrap material than traditional approaches.

A process for treating a centrifugal compressor wheel includes a combination of cold expansion of at least part of the bore of the wheel to induce residual compressive stresses in a region around the bore, and surface peening at least parts of the compressor wheel such as the back disk and portions of the blades.

A turbine rotor disk and a method of making the turbine rotor disk using solid state bonding techniques are disclosed. The turbine rotor disk includes a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F. The turbine rotor disk also includes a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.