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Title: Hot gas path component

Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
; ; ;
Issue Date:
OSTI Identifier:
General Electric Company NETL
Patent Number(s):
Application Number:
Contract Number:
Resource Relation:
Patent File Date: 2014 Dec 29
Research Org:
General Electric Company, Schenectady, NY (United States)
Sponsoring Org:
Country of Publication:
United States

Other works cited in this record:

Turbine shroud segment with serpentine cooling channels
patent, January 1996

Apparatus and methods for relieving thermally induced stresses in inner and outer bands of thermally cooled turbine nozzle stages
patent, May 2002

Laser machining cooling holes in gas turbine components
patent, July 2002

Heat processing apparatus
patent, June 2004

Laser drilling shaped holes
patent, March 2006

Process of masking cooling holes of a gas turbine component
patent, December 2006

Percussion drilled shaped through hole and method of forming
patent, October 2010

Method for producing a hole
patent, April 2012

Laser shaped film cooling hole
patent, August 2012

Method for repairing a cold section component of a gas turbine engine
patent-application, November 2005

Forming structures by laser deposition
patent-application, March 2006

Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud
patent-application, February 2009

Method for manufacturing a hot gas path component and hot gas path turbine component
patent-application, June 2013

Turbine shroud cooling assembly for a gas turbine system
patent-application, October 2013

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