Chromalloy Gas Turbine Corporation

Other

David S Kang

Frank J Goodwater

Lang D Huynh

Chunghee Kimberly Kang

Lang Huynh

Kevin J Updegrove

Hon Li

James M Lizotte

Brian G Doyle

Brian Doyle

James Lizotte

There is provided a composition for the prevention and treatment of age-related physical and mental disorders that includes phospholipids that have been extracted from chick embryos aged between about 6 days old and about 14 days old. Also provided is a method for extracting these phospholipids by incubating them for between about 6 days to about 14 days. The chick embryos are then prepared for chemical extraction, and the lipids are extracted from the chick embryos. Further provided is a method for preventing and treating age-related physical and mental disorders, in human subjects in need thereof, by administering a sufficient dosage of a composition including phospholipids extracted from chick embryos incubated for between about 6 days and about 14 days to a human subject.

Composition and method for treating age-related disorders

The present invention provides a method of avoiding rapid development of extreme hyperammonemia and metabolic acidosis in undiagnosed metabolically abnormal infants having an inherited metabolic disorder.

Method of preventing development of severe metabolic derangement in inborn errors of metabolism

A method for refurbishing turbine engine vanes in which the airfoils are removed and replaced. The original configuration of the vanes can be modified from a single casting or welded pair to a multi-piece component assembly comprising individual airfoil segments attached to the inner and outer platforms. The component assembly allows replacement of airfoils and/or platforms with improved castings in the form of improved alloys, improved physical geometry, or both. Modifications can be made in the vane class area without the need to modify the airfoil contour by brazing or other contour alteration processes. According to the method, the platforms are separated from the airfoils, the openings in the platforms are sealed, new airfoil sockets are cut into the platforms, and the vane is reassembled.

Method for replacing a turbine vane airfoil

A method of refurbishing turbine engine vanes in which an alloy blend of a cobalt based superalloy and a nickel based superalloy corresponding to the base material of the turbine vane cobalt platform and the base nickel material of the replacement turbine vane airfoils is laser clad to the gaspath surfaces of the turbine vane platform. Laser cladding with the alloy blend allows the use of replacement airfoils with improved castings in the form of improved nickel based superalloys, and allows a coating to be uniformly applied to the gaspath surfaces of the vane. According to the method, the platforms are separated from the airfoils and laser clad with a blend of cobalt based superalloy and nickel based superalloy. The vane is then reassembled using the laser clad platform and at least one replacement airfoil.

Laser cladding a turbine engine vane platform

A process is provided for plating a coating onto a gas turbine engine component without detrimentally effecting air flow through cooling holes by injecting a maskant into the cooling passage to fill the cooling holes with the maskant, plating the external surface of the component with a coating, then removing the maskant from the component.

Plating turbine engine components

A process and apparatus is provided for laser welding a nickel and/or cobalt based superalloy article comprising: preheating the entire weld area and adjacent region to a ductile temperature with an induction heat coil and maintaining such temperature during welding and solidification of the weld; and welding the preheated article utilizing a laser with a powder alloy feed with a control means controlling the laser, power feed and motion system on which the article is fixtured, wherein the control means includes a vision system which digitizes the weld area providing a path for the laser welding to follow.

Interactive laser welding at elevated temperatures of superalloy articles

An apparatus is provided for separating components of a brazed vane assembly by preheating the assembly to a temperature below the solidus of the base metal of the vane assembly and above the liquidus of the braze, then maintaining such temperature while separating the airfoil from the platform by pulling/pushing the airfoil and platform apart.

Gas turbine engine vane assembly repair apparatus

A process and apparatus are provided for separating components of a brazed vane assembly by preheating the assembly to a temperature below the solidus of the base metal of the vane assembly and above the liquidus of the braze, then maintaining such temperature while separating the airfoil from the platform by pulling/pushing the airfoil and platform apart.

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Carson City, NV, United States of America

David S Kang