skip to main content
OSTI.GOV title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: Hot gas path component cooling system

Patent ·
OSTI ID:1125003

A cooling system for a hot gas path component is disclosed. The cooling system may include a component layer and a cover layer. The component layer may include a first inner surface and a second outer surface. The second outer surface may define a plurality of channels. The component layer may further define a plurality of passages extending generally between the first inner surface and the second outer surface. Each of the plurality of channels may be fluidly connected to at least one of the plurality of passages. The cover layer may be situated adjacent the second outer surface of the component layer. The plurality of passages may be configured to flow a cooling medium to the plurality of channels and provide impingement cooling to the cover layer. The plurality of channels may be configured to flow cooling medium therethrough, cooling the cover layer.

Research Organization:
General Electric Company, Schenectady, NY, USA
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
8,651,805
Application Number:
12/765,372
OSTI ID:
1125003
Resource Relation:
Patent File Date: 2010 Apr 22
Country of Publication:
United States
Language:
English

References (24)

Laminated porous metal patent June 1971
Coolable wall patent October 1978
Perforated laminated material patent September 1979
Transpiration cooled ceramic blade for a gas turbine patent January 1982
Method of manufacturing a transpiration cooled ceramic blade for a gas turbine patent March 1983
Diffusion bonding method patent September 1988
Nozzle guide vane structure for a gas turbine engine patent January 1989
Perforated two layered sheet for use in film cooling patent June 1993
Double-wall airfoil patent May 1997
Method for making a double-wall airfoil patent June 1997
Turbine blade tip having thermal barrier coating-formed micro cooling channels patent October 2002
Cooled thermal barrier coating on a turbine blade tip patent October 2002
Turbine airfoil trailing edge with micro cooling channels patent December 2002
Multi-layer thermal barrier coating with transpiration cooling patent January 2003
Process for creating structured porosity in thermal barrier coating patent March 2003
Process for forming micro cooling channels inside a thermal barrier coating system without masking material patent April 2003
Gas-turbine blade and method of manufacturing a gas-turbine blade patent June 2003
Directly cooled thermal barrier coating system patent September 2003
Double wall combustor liner segment with enhanced cooling patent July 2004
Network cooled coated wall patent June 2005
Lazy tracking of user system web cache patent June 2021
Methods and apparatus for cooling gas turbine engine components patent-application May 2006
Turbine nozzle with trailing edge convection and film cooling patent-application October 2006
Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages patent-application August 2007

Cited By (4)

Hot gas path component having near wall cooling features patent November 2017
Components with microchannel cooling patent March 2017
System and method for removing heat from a turbine patent March 2016
Backstrike protection during machining of cooling features patent February 2016