A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.

A device and a method for producing a blade airfoil from a workpiece which comprises at least two gaps and at least one blank arranged between the two gaps, wherein the blank comprises two opposite lateral faces which are bounded by a base, a top and a first and a second edge. The method comprises: (a) arranging the first and second electrodes in the first and second gaps, the surface of the workpiece forming an annular space surface at the gaps, (b) applying a positive voltage to the blank and applying a negative voltage to the first and second electrodes, (c) moving the first and second electrode in the direction of the first and second lateral faces.
Step (b) is preceded by passing electrolyte between the two electrodes over the top toward the base.

A method of forming a component for a gas turbine engine, including: casting a component around a ceramic core, wherein the ceramic core forms a pilot channel (40) in the component, the pilot channel oriented from a base (176) to a tip (20) of the component; sinking an ECM electrode into the pilot channel; and enlarging the pilot channel to form an inner surface of an external wall (120) of the component via electro-chemical machining, wherein a contour (94) of the inner surface is different than a contour of the pilot channel.

The invention relates to a method for manufacturing a housing of a turbomachine, in particular a gas turbine. The method comprises at least the steps: providing a housing blank (10), manufacturing a housing element (14), producing an assembly opening (12) corresponding to the housing element (14) in the housing blank (10), arranging the housing element (14) in the assembly opening (12), and joining the housing element (14) to the housing blank (10) by means of a welding method. In addition, the invention relates to a turbomachine housing.

A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.

A method for producing a rotary disk/blisk for a high-pressure compressor or a high-speed turbine and to a corresponding geared turbofan engine. The method involves providing a Ni base alloy comprising, in % by weight, 15.5-16.5 Cr, 14.0-15.5 Co, 4.75-5.25 Ti, 2.75-3.25 Mo. 2.25-2.75 Al, 1.00-1.50 W, as well as optionally 0.0250-0.0500 Zr, 0.0100-0.0200 B, 0.0100-0.0200 C, remainder Ni. The base alloy is shaped by forging to obtain a preform of the disk/blisk, the final contour thereof being produced by electrical discharge machining or electrochemical machining.

The present invention relates to a method for manufacturing a plate of a turbomachine having a plurality of receiving grooves, which are formed on the cylindrical peripheral surface of the plate in order to receive blade roots of blades of the turbomachine. The receiving grooves extend in a straight line from one face of the plate to the other face of the plate, such that a straight line delimits the receiving groove from each point on the cross section of the receiving groove on one of the faces to the corresponding point on the cross section on the other face. A circular plate is provided and a plurality of receiving grooves are introduced into the plate simultaneously on opposing regions relative to a central axis of rotation of the plate.

A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.

Methods of repairing a part having a firtree-shaped feature requiring rework are disclosed. An embodiment of the method includes receiving the part having the firtree-shaped feature requiring rework. The part is installed in a machine configured for wire electrical discharge machining (EDM). A location of the firtree-shaped feature relative to a datum of the machine is then determined. Wire EDM is performed on the firtree-shaped feature.

A method for producing a rotor disk or a rotor blade for a gas turbine compressor stage or turbine stage of an aeroengine, wherein at least one blade groove of the rotor disk for arrangement of a blade foot of a rotor blade for fastening the rotor blade to the rotor disk, or a blade foot of the rotor blade for arrangement in a blade groove of a rotor disk for fastening the rotor blade to the rotor disk is fabricated using an electrochemical material removal and in the axial direction has a profile which is curved once or more.