A rim seal located between a stator and a rotor in a gas turbine engine includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.

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 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.

The present disclosure provides a rotary friction welding process including: providing an outer axisymmetric workpiece having a front first annular weld surface at a radially inward extent and a rear first annular weld surface at a radially inward extent; providing a front inner axisymmetric workpiece, the front inner workpiece having a front second annular weld surface at a radially outward extent of the front inner workpiece; providing a rear inner axisymmetric workpiece, the rear inner workpiece having a rear second annular weld surface at a radially outward extent of the rear inner workpiece; and rotary welding the workpieces together.

The impeller comprises: an impeller body (21) which includes a surface part (27) formed to a fixed depth (D) from a surface (21a) thereof, and which is made of Al or an Al alloy; and an NiP-based electroless-plated film (23) covering the surface (21a) of the impeller body (21), wherein the surface part (27) has a first compressive residual stress (P1).

Disclosed is a method of making an integrally bladed rotor. According to the method, a titanium alloy rotor disk with 15-50% by volume of primary alpha grains with a grain size less than 10 m and secondary alpha grains comprising widmanstatten grains with a grain size less than 1.0 m is subjected to thermal processing. After thermal processing, a blade having an airfoil and a base is positioned such that a base surface is in contact with an outer rim surface of the disk. Heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the disk outer rim surface.

Various implementations include a ring material used for producing a ring molded article. The ring molded article has two convex portions which respectively protrude on opposite 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. A straight line passing through centers of gravity of first and second side regions is inclined by an angle relative to the center axis of the ring material, the first and second side regions are obtained by virtually dividing a one half section of the ring material based on a middle of a maximum height of the ring material in the direction of the center axis of the ring material, and a range of the angle is 7 degrees to 40 degrees.

Turbomachines having close-coupling flow guides (CCFGs) that are designed and configured to closely-couple flow fields of adjacent bladed elements. In some embodiments, the CCFGs may be located in regions extending between the adjacent bladed elements, described herein as coupling avoidance zones, where conventional turbomachine design would suggest no structure should be added. In yet other embodiments, CCFGs are located upstream and/or downstream of rows of blades coupled to the bladed elements, including overlapping one of more of the rows of blades, to improve flow coupling and machine performance. Methods of designing turbomachines to incorporate CCFGs are also provided.

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.

The method comprises the steps of: a) cutting the shaft of the rotor at a section plane perpendicular to the axis of rotation of the shaft so as to separate the end portion of the shaft on which the bladed discs to be replaced are mounted from the remaining portion of the shaft; b) providing, for each bladed disc to be replaced, a corresponding new bladed disc with a respective hub having a solid cross-section; c) providing a new end portion of the shaft with a solid cross-section; and d) clamping the new bladed discs between the remaining portion of the shaft and the new end portion of the shaft, securing them to the remaining portion of the shaft by anchor bolts.