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Title: Turbine component cooling channel mesh with intersection chambers

Patent ·
OSTI ID:1130956
;

A mesh (35) of cooling channels (35A, 35B) with an array of cooling channel intersections (42) in a wall (21, 22) of a turbine component. A mixing chamber (42A-C) at each intersection is wider (W1, W2)) than a width (W) of each of the cooling channels connected to the mixing chamber. The mixing chamber promotes swirl, and slows the coolant for more efficient and uniform cooling. A series of cooling meshes (M1, M2) may be separated by mixing manifolds (44), which may have film cooling holes (46) and/or coolant refresher holes (48).

Research Organization:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42644
Assignee:
Siemens Energy, Inc. (Orlando, FL); Mikro Systems, Inc. (Charlottesville, VA)
Patent Number(s):
8,714,926
Application Number:
12/884,486
OSTI ID:
1130956
Resource Relation:
Patent File Date: 2010 Sep 17
Country of Publication:
United States
Language:
English

References (12)

Film cooling of turbine airfoil wall using mesh cooling hole arrangement patent December 1994
Internal cooling of turbine airfoil wall using mesh cooling hole arrangement patent November 1997
Tapered tip turbine blade patent July 2000
Cooling system for a turbine blade patent June 2005
Converging pin cooled airfoil patent January 2006
Hot gas path component with mesh and turbulated cooling patent January 2006
Thermal shield turbine airfoil patent March 2006
Hot gas path component with mesh and impingement cooling patent February 2007
Hot gas path component with mesh and dimpled cooling patent March 2007
Multiple vortex cooling circuit for a thin airfoil patent May 2010
Hot gas path component with mesh and impingement cooling patent-application June 2005
Vortex Cooling of Turbine Blades patent-application December 2005

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