General Electric Company

Charles William Carrier

Chen-Yu Jack Chou

Charles Robert Wojciechowski

Daniel Edward Wines

Gary Mac Holloway

Robert William Bruce

Andrew J Lammas

Steven Alan Ross

Richard G Menzies

Jon Raymond Groh

Mark Dean Pezzutti

Gary Edward Trewiler

Adrian M Ablett

James Grooms

Brian J Humke

Steven Andrew Strang

Barbara Ann Link

Terrence Owen Dyer

Mark Steven Habedank

Bernard Harold Lawless

Chris League

John Absi

Mark Wesley Johnson

Gregory Stephen Bechtel

Frank W Gorsler

Randy Joseph Ketterer

Robert R Kursmark

A method of manufacturing turbine engine casings having at least one boss includes, in one exemplary embodiment, forming an engine casing having an outer wall, machining a tapered opening through the casing outer wall, and machining a tapered portion in a metal plug where the tapered portion is sized to mate with the tapered opening in the casing outer wall. The method also includes inserting the metal plug into the tapered opening in the casing outer wall, and welding the metal plug to the casing.

Method for manufacturing aircraft engine cases with bosses

Friction welding systems and methods including a welding arrangement configured to impart kinetic friction between at least one surface of a first workpiece and at least one surface of a second workpiece to form a weld, a force providing mechanism arranged and disposed for applying a force to one or both of the first workpiece and the second workpiece, and a sensor arranged and disposed to measure a parameter of the welding arrangement, wherein an amount of vibration is determinable from the measured parameter.

Friction weld vibration quality monitoring system and methods

A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

System for manufacturing a rotor having an MMC ring component and a unitary airfoil component

A method for fabricating a rotor assembly for a turbine, the turbine including a central rotational axis is provided. The method includes forging a first rotor component from a first material, separately forging a second rotor component from a second material, and coupling the second rotor component to the first rotor component at a location radially inward of the first rotor component. The second rotor component is coupled to the first rotor component in at least one axial-circumferential plane that is at least one of substantially parallel and obliquely oriented with respect to the central rotational axis.

Rotary machine components and methods of fabricating such components

A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing conical surface; an airfoil component, wherein the airfoil component further includes a plurality of individual airfoil blades, wherein at least a portion of each individual airfoil blade has been reinforced with at least one metal matrix composite, and wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

System for manufacturing a rotor having an MMC ring component and an airfoil component having MMC airfoils

A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a plurality of radially outwardly facing blade conical surfaces; an airfoil component, wherein the airfoil component further includes: a plurality of individual airfoil blades, wherein each of the plurality of airfoil blades further includes a radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.

System for manufacturing a rotor having an MMC ring component and an airfoil component having monolithic airfoils

nethod for manufacturing a test bar from a turbo-machinery component, test bar made in accordance with the method, and turbo-machinery component associated with the method. A component section is obtained from the turbo-machinery component, wherein the component section includes a component portion, and wherein the component portion has a substantially rectangular cross section and has a width. First and second semi-circular cylinders are obtained having a diameter substantially equal to the width of the component portion. The component section is disposed between, and in contact with, the first and second semi-circular cylinders defining a component-section-cylinder assembly having first and second assembly ends. First and second end extensions are obtained. The first end extension is inertia welded to the first assembly end and the second end extension is inertia welded to the second assembly end defining a test-bar stock. The test-bar stock is machined creating the test bar.

Method for manufacturing a test bar

A method and apparatus for fabricating a workpiece is provided. The method includes applying a predetermined axial force to a tool, translating the axial force into a radial force in the workpiece using the tool, and generating a hoop stress in the work piece sufficient to relieve residual stress in the workpiece.

Method for fabricating rotary machines

A method for fabricating a component for a gas turbine engine includes providing a blisk forging fabricated from a first material, inertia welding a second material to the blisk forging to create a bi-alloy blisk forging, and machining the bi-alloy blisk forging to pre-determined dimensions.

Gas turbine engine components and methods of fabricating same

A centering and holding fixture includes a base, a piston disposed within a piston chamber at least partially located within the base, and a radially flexible ring connected to the piston by force transmission apparatus operable to contract and expand the radially flexible ring by upward and downward motions respectively of the piston. The flexible ring may be slotted and may include alternating inwardly and outwardly extending radial slots extending axially through the flexible ring and extending radially inwardly and radially outwardly from radially outer and inner surfaces of the flexible ring respectively to axial stress relief holes extending axially through the flexible ring. The apparatus may further be operable to contract the radially flexible ring when the piston chamber is pressurized and to expand it when the piston chamber is depressurized. Spring loaded clamps mounted to the base may be used to secure a workpiece to the holding fixture.

Machining fixture for centering and holding workpiece

A method is provided for assembling a shaft having a metal matrix composite mid shaft and monolithic high strength alloy forward and aft shafts. The forward and aft shafts are each inertia friction welded to separate annular transition pieces which include a barrier layer operative to prevent the formation of intermetallic compounds. Special tooling is used to avoid applying shear stresses to the transition piece during welding. The welded forward and aft subassemblies are subsequently heat treated before inertia friction welding them to the mid shaft.

Inertia welded shaft and method therefor

A rotor assembly of an axial flow turbine engine has a bladed ring including a ring, and a plurality of turbine blades affixed to the ring and extending radially outwardly from the ring. There is a solid state weld joint between a central disk hub and the ring of the bladed ring. In one approach, the rotor assembly is prepared by bonding the plurality of turbine blades to the coarse-grain ring so that the turbine blades extend outwardly from the ring, providing the fine-grain central disk hub, and solid-state inertia welding the central disk hub and the ring of the bladed ring at a solid state weld joint.

Tri-property rotor assembly of a turbine engine, and method for its preparation

A damper for reducing vibration in a least a portion of a component during inertia welding. The damper includes a generally annular body having a spiral slot formed therein.

Growing community of inventors

West Chester, OH, United States of America

Charles William Carrier