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 plurality of walls and a plurality of case segments. Each of the walls extends axially along and circumferentially about an axial centerline. The walls include a first wall and a second wall radially outboard of and axially overlapping the first wall. Each of the case segments is configured to form a respective portion of the first wall and a respective portion of the second wall. The case segments include a first case segment and a second case segment circumferentially adjacent and attached to the first case segment at a joint.

A component of a rotary machine formed from a blank, the component includes a center, a boundary surface, and at least one inner passage extending from the center up to the boundary surface and being at least partly closed. The inner passage is formed by a first subtractive machining in which a part of the passage that at least includes an opening of the passage into the boundary surface as well as a cut-out in the top surface is manufactured by machining production, and subsequently the passage is completed by a build-up production on the blank.

The invention relates to a method for producing a rotor of a flow engine, namely an integrally bladed rotor with an integral outer shroud, comprising at least the following steps: a rotor blank comprising the integral rotor blades and the integral outer shroud is first produced by means of a generative production method; the rotor blank is then subjected to a separating surface treatment at flow-guiding sections and is subjected, separately therefrom, to a machining surface treatment at non-flow-guiding sections.

The present invention concerns a method for the construction of bladed discs for radial turbomachines, comprising: preparing a disc (6, 14) provided with a front face (7); preparing a plurality of reinforcement rings (23) with different diameters. Preparing the disc (6, 14) comprises: realizing annular sets of blades (20) in one piece with the disc (6, 14), said sets (20) being concentric and coaxial with a central axis (X-X) and arranged on the front face (7), wherein each blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X); and/or preparing a plurality of reinforcement rings (23) comprises: realizing in one piece with each one of the reinforcement rings (23) an annular set of auxiliary blades (20) arranged around a central axis (X-X), wherein each auxiliary blade (20) has a leading edge (21) and a trailing edge (22) substantially parallel to the central axis (X-X). Each one of the reinforcement rings (23) is applied to the disc (6, 14) at one of the annular sets of blades (20) and/or auxiliary blades (20), so as to define on the front face (7) annular sets of blades (20) and/or auxiliary blades (20), each one provided with a respective reinforcement ring (23).

A method for producing a turbomachine impeller, which has a radially inner hub body, a radially outer shroud body and blades extending between the hub body and the shroud body. The blades, the hub body and the shroud body are designed as an integral, monolithic assembly includes providing a blank; milling the blank to form a basic contour of the hub body, the shroud body, and the blades; performing build-up welding or additive manufacturing at least once on the main contour that is formed and subsequently performing milling at least once on portions that are formed by the build-up welding.

A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

A tool for simultaneous local stress relief of each of a multiple of linear friction welds includes a columnar track defined along an axis, the columnar track having a helical slot; and a support structure engaged with the helical slot to translate and rotate a heat treat fixture portion along the axis.

A fully scalable turbomachine in which one or more of its components, in particular its bladed components, such as a blisk, is manufactured by controlled-fracture machining. The practical effects of the invention are (1) to improve the quality of current turbomachine components at greater rates of production and lower costs, (2) to increase the performance and the range of uses of current turbomachine functions, and (3) to enable new uses of turbomachines that are currently restricted by the lack of scalability and practicality in manufacturing. The most preferred embodiment of the invention is the gas turbine functioning as a jet engine or a turboshaft engine either for propulsion or for power generation.

Provided is a blade assembling method for a converter, wherein a blade 20 held by blade holding means (adsorption part 152) is further relatively moved with respect to a shell 10, whereby, while remaining claws 21B and 21C of the blade 20 are pressed against the upper surface of the shell 10 in an obliquely forward and downward direction by the holding force of the blade holding means (adsorption part 152), the claws 21B and 21C are slid toward grooves 11B and 11C from the near side of the corresponding grooves 11B and 11C and inserted so as to fall in the grooves 11B and 11C to thereby insert all the claws 21A to 21C into all the corresponding grooves 11A to 11C, respectively.

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.