General Electric Company

United Technologies Corporation

Other

Peter W Schilke

Melvin Robert Jackson

Shyh-Chin Huang

Don Mark Lipkin

Thomas Robert Raber

Reed Roeder Corderman

Raymond Alan White

David N Duhl

Swami Ganesh

John R Rairden, Iii

Francis Alexander Reed

Robin Carl Schwant

Robert V Falsetti

Ling Yang

John Zhiqiang Wang

William F Schilling

Myron C Muth

Michael Patrick Manning

Peter V Dembowski

Gerard F Johnson

Sidney Perham Young

A monolithic rotor comprising first and second rotor regions axially aligned within the monolithic rotor and a transition zone therebetween. The first and second rotor regions are formed of different alloys and the transition zone having a composition that differs from and varies between the first and second rotor regions. The first rotor region is located within a high pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of CrMoV low alloy steels, martensitic stainless steels containing about 11 to about 14 weight percent chromium, Fe&#x2014;Ni alloys, and nickel-base alloys. The second rotor region is located within a low pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of NiCrMoV low alloy steels and martensitic stainless steels containing about 11 to about 14 weight percent chromium.

Multiple alloy rotor

A system and method for repairing defects such as bumper holes, cracks, freckles and inclusions, in a cast article, such as a turbine component. The system comprises a device for locating a defect in a cast article, a repair material that is disposable at a defect site, at least one heat source capable of heating the repair material and a portion of the cast article to a molten state. The method of using the system comprises locating a defect in the cast article, providing a repair material to the defect site, melting the repair material and cast article at the defect site, and cooling the molten repair material and portion of the casting article such that they resolidify and fuse together. The method may further comprise removing a portion of the cast article at the defect site, removal of excess repair material and inspecting the cast article following repair of the defect.

System and method for repairing cast articles

A threaded fastener and a method by which the fastener exhibits sufficiently enhanced fatigue strength so as to be suitable for use in gas compressors and turbines operating at relatively high service temperatures. The method entails a selective heat treatment to achieve a dramatic improvement in fatigue properties while not interfering with other required properties for the fastener. The heat treatment process preferentially develops a case-hardened region in those threads nearest a transition region between the threads and an unthreaded portion of the fastener. In contrast, the unthreaded portion and the threads furthest from the transition region need not be case-hardened. The hardening pattern in the threads yields a martensitic steel fastener that exhibits fatigue properties which are dramatically superior to otherwise identical fasteners.

Threaded fastener and method of improving the fatigue life thereof

A method of creating a controlled interior surface configuration of passages within a substrate, particularly cooling passages of nozzles or buckets of a gas turbine, involves the hot isostatic pressing of a leachable passage insert whose surface carries the female image of the desired interior surface configuration inside the substrate followed by leaching of the insert from the substrate.

Method of creating a controlled interior surface configuration of

In the method for fabrication of water-cooled composite nozzle and bucket hardware for high temperature gas turbines, a high thermal conductivity copper alloy is applied, employing a high velocity/low pressure (HV/LP) plasma arc spraying process, to an assembly comprising a structural framework of copper alloy or a nickel-based super alloy, or combination of the two, and overlying cooling tubes. The copper alloy is plamsa sprayed to a coating thickness sufficient to completely cover the cooling tubes, and to allow for machining back of the copper alloy to create a smooth surface having a thickness of from 0.010 inch (0.254 mm) to 0.150 inch (3.18 mm) or more. The layer of copper applied by the plasma spraying has no continuous porosity, and advantageously may readily be employed to sustain a pressure differential during hot isostatic pressing (HIP) bonding of the overall structure to enhance bonding by solid state diffusion between the component parts of the structure.

Fabrication of gas turbine water-cooled composite nozzle and bucket

Disclosed is an improved abrasive material particularly useful as a dispersoid in metal matrices to provide articles of use having superior abrasive properties, especially at elevated temperatures. The improved abrasive material typically comprises silicon carbide particulate, the individual particles of which have a predominantly alumina coating thereon to inhibit dissolution of the particles in the metal matrix at high temperatures. The invention finds special application in abrasive blade tips for service in gas turbine engines, the tips comprising a nickel base or cobalt base superalloy having the alumina coated silicon carbide particles dispersed therein.

Alumina coated silicon carbide abrasive

A nickel base superalloy having a composition which provides a desirable combination of good oxidation and corrosion resistance and hot hardness is described. The alloy contains 21-25% Cr, 4.5-7% Al, 4-10% W, 2.5-7% Ta, 0.5-0.15% Y and 0.1-0.3% C. This alloy is useful as a blade tip element in a composite gas turbine blade.

Gas turbine blade tip alloy and composite

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Scotia, NY, United States of America

Peter W Schilke