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Title: Hot gas path component and methods of manufacture

Patent ·
OSTI ID:1568474
; ; ;

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.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
10,322,575
Application Number:
15/661,126
OSTI ID:
1568474
Resource Relation:
Patent File Date: 07/27/2017
Country of Publication:
United States
Language:
English

References (4)

Apparatus and methods for relieving thermally induced stresses in inner and outer bands of thermally cooled turbine nozzle stages patent May 2002
Method for manufacturing a hot gas path component and hot gas path turbine component patent-application June 2013
Turbine shroud segment with serpentine cooling channels patent January 1996
Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud patent-application February 2009

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42 ENGINEERING
36 MATERIALS SCIENCE