Gm Global Technolgoy Operations, Inc.

Other

Rolls-royce Corporation

Lawrence E Brown

Stephen Norman Hammond

Kenneth R Cross

David L Clingman

Michael J Barber

Peter W Heitman

Joseph Jefferson Beaman, Jr

Timothy Fuesting

Suman Das

Donald M Wieland

Mark C Nordin

William H Beierwaltes

Elizabeth J Holmes

John F Kroemer

Jiann-long Wu

An electrospark alloying apparatus includes a main body member, a collet coupled to the main body member, and a heat sink adjacent the collet. The collet is adapted to receive and hold a consumable electrode. The apparatus can also include a drive for rotating the electrode. Further, the apparatus can include an inert gas supply and a discharge opening in the main body member for facilitating lamellar gas flow of insert gas from the inert gas supply around the electrode. A method of electrospark alloying includes electrospark alloying a workpiece with a consumable electrode and cooling the electrode during the electrospark welding.

Method and apparatus for electrospark alloying

The present invention relates to a method an apparatus for fabricating a component by a direct laser process. One form of the present invention contemplates a gas turbine engine blade having an abrasive tip formed directly thereon.

Method and apparatus for making components by direct laser processing

An abrasive system and a processing procedure is provided which permits the direct installation of a thick abrasive blade tip cap onto a cast turbine rotor blade during a heating schedule which requires two furnace operations. The composition of the abrasive blade tip cap advantageously utilizes the high temperature performance capabilities of equiaxed or single crystal rotor blade alloys without significantly affecting their mechanical properties as a consequence of the processing necessary to permanently bond the abrasive blade tip cap to the rotor blade. A semi-rigid mat consisting of the preferred abrasive composition is first consolidated in a first vacuum furnace operation. Blade tip cap preforms are then cut from the mat and positioned on the tip of the rotor blade. The preform and rotor blade are then heated in a vacuum furnace according to a temperature schedule entailing heating rates, holding temperatures and durations which are sufficient to bond the preform to the rotor blade. The rotor blade is then rapidly cooled in the vacuum furnace to retain the microstructure and mechanical properties of the rotor blade.

Method for bonding abrasive blade tips to the tip of a gas turbine blade

An abrasive system and a processing procedure is provided which permits the direct installation of a thick abrasive blade tip cap onto a cast single crystal turbine rotor blade during a single heating schedule requiring only one furnace operation. The composition of the abrasive blade tip cap advantageously utilizes the high temperature performance capabilities of the single crystal alloy without significantly affecting its mechanical properties as a consequence of the processing necessary to permanently bond the abrasive blade tip cap to the rotor blade. A semi-rigid blade tip cap preform is first formed and positioned on the tip of the rotor blade. The preform and rotor blade are then heated in a vacuum furnace according to a temperature schedule entailing heating rates, holding temperatures and durations which are sufficient to bond and consolidate the preform. The rotor blade is then rapidly cooled in the vacuum furnace to retain the single crystal structure of the rotor blade.

Abrasive blade tips for cast single crystal gas turbine blades

Braze filler alloy is specifically applied and metallurgically bonded to a desired region of a nickel based superalloy workpiece using an electrospark deposition technique. The braze filler alloy is deposited onto, and concurrently metallurgically alloyed into, the desired region of the base metal by transfer of the material from the electrode using a short duration electrical impulse. The time and energy involved are small enough that total heat input to the base metal is minimal so that distortion and metallurgical structure changes of the base metal are negligible.

Method for depositing braze alloy to base metal surfaces using electric

Single crystal, nickel based superalloy turbine blades are formed by fusion welding together two matched blade halves. The matched blade halves are joined by an electrospark deposition process which deposits a weld filler metal along the matched faying surfaces. The deposited weld filler metal is preferably the same nickel based superalloy used to form the single crystal turbine blades. Total heat input to the base metal is minimal so that distortion and metallurgical structure changes of the base metal are virtually nonexistent.

Method for joining single crystal turbine blade halves

A new radiopharmaceutical composition for use in nuclear medicine comprises a radioiodinated meta-iodobenzylguanidine. The composition is used as an imaging agent for the heart, adrenal medulla, and tumors of the adrenal medulla and can be used for treatment of tumors of the adrenal medulla.

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Indianapolis, IN, United States of America

Lawrence E Brown