A method for producing an enhanced property integrally bladed rotor includes solution heat treating a stub-containing rotor hub forging; water quenching the solution heat treated stub-containing rotor hub; aging the water quenched stub-containing rotor hub forging; linear friction welding airfoils onto each of a multiple of stubs of the stub-containing rotor hub forging; and concurrently stress relieving the linear friction welds of each of the multiple of stubs within a predefined area while ensuring that a hub inner diameter does not exceed a predetermined temperature.

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.

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 disc for use in a turbine rotor is provided including a hub, a plurality of webs extending outwardly from the hub, and a plurality of rims. Each of the plurality of webs are separate from each other by a gap. Each rim is positioned at an outward end of one of the webs. Each rim is configured to receive a respective set of turbine blade.

An integrally bladed rotor for a gas turbine engine includes a rotor portion with an outer periphery. At least one airfoil includes a suction side and a pressure side extending between a leading edge and a trailing edge. The at least one airfoil extends radially from the outer periphery and has an airfoil thickness between the suction side and the pressure side. A first thickness on at least one of the pressure side and suction side of the airfoil in addition to the airfoil thickness that extends radially from the outer periphery defines a crack propagation boundary. A method of fabricating an integrally bladed rotor for a gas turbine engine is also disclosed.

A cooling device for a rotor assembly of a gas turbine engine includes an airflow nozzle configured to be installed at a cooling location of the rotor assembly. The airflow nozzle extends entirely around a circumference of the rotor assembly and includes a plurality of airflow inlets and a nozzle outlet to direct an airflow toward the cooling location. An airflow source is operably connected to the plurality of airflow inlets.

A method for manufacturing a metal alloy part for an aircraft turbine engine, the method including the steps of: (a) producing a blank of the part by additive manufacturing by laser fusion on a powder bed, and (b) abrasively machining the blank to obtain the part, the machining being carried out by vibratory finishing by immersing the blank in an abrasive composition contained in a tank subjected to a vibratory movement, the abrasive composition having an abrasive element formed by alumina particles, a carrying element formed by copper particles, and a liquid.

A turbine blisk is provided. The turbine blisk includes an inner rim, a plurality of adjacent rotor blades extending radially outward from said inner rim, a shroud segment integrally coupled to each of the plurality of adjacent rotor blades, thereby forming a plurality of adjacent shroud segments, and a gap defined between each of the adjacent shroud segments. The gap has a geometry that facilitates interlocking the plurality of adjacent shroud segments when a torsional force is applied to the plurality of adjacent rotor blades.

When a closed type impeller is manufactured from one block, a rough cutting process of cutting a flow path region of a block using a rough cutting tool, and a residue-cutting process of cutting a cutting residue in the cutting process using a residue-cutting tool are executed. The residue-cutting tool has a tool main body having a blade formed on an outer periphery thereof, and a handle having the tool main body fixed to a distal end thereof. A maximum outer diameter of the tool main body is larger than a minimum outer diameter of the handle. Further, the tool main body has a rear blade directed in a direction including a tool rear side component.

The invention relates to the manufacturing of a rotor (23) of a high-pressure compressor. Various installation constraints are proposed in terms of temperature, angle and unevenness and/or runout defects to be considered. For example, when installing the sealing disk (25) on the first drum (27) of the rotor and/or the intermediate disk (29) on the first drum assembled with the sealing disk, axial packing (X1) is applied with a pressure ranging from 40 to 6010.sup.5 Pa.