Turbine component cooling channel mesh with intersection chambers
Abstract
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).
- Inventors:
- Publication Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1130956
- Patent Number(s):
- 8,714,926
- Application Number:
- 12/884,486
- Assignee:
- Siemens Energy, Inc. (Orlando, FL); Mikro Systems, Inc. (Charlottesville, VA)
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2010 Sep 17
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Lee, Ching-Pang, and Marra, John J. Turbine component cooling channel mesh with intersection chambers. United States: N. p., 2014.
Web.
Lee, Ching-Pang, & Marra, John J. Turbine component cooling channel mesh with intersection chambers. United States.
Lee, Ching-Pang, and Marra, John J. 2014.
"Turbine component cooling channel mesh with intersection chambers". United States. https://www.osti.gov/servlets/purl/1130956.
@article{osti_1130956,
title = {Turbine component cooling channel mesh with intersection chambers},
author = {Lee, Ching-Pang and Marra, John J},
abstractNote = {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).},
doi = {},
url = {https://www.osti.gov/biblio/1130956},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue May 06 00:00:00 EDT 2014},
month = {Tue May 06 00:00:00 EDT 2014}
}
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Works referenced in this record:
Film cooling of turbine airfoil wall using mesh cooling hole arrangement
patent, December 1994
- Lee, Ching-Pang
- US Patent Document 5,370,499
Internal cooling of turbine airfoil wall using mesh cooling hole arrangement
patent, November 1997
- Lee, Ching-Pang
- US Patent Document 5,690,472
Converging pin cooled airfoil
patent, January 2006
- Lee, Ching-Pang; Bunker, Ronald Scott; Prakash, Chander
- US Patent Document 6,981,840
Hot gas path component with mesh and turbulated cooling
patent, January 2006
- Bunker, Ronald Scott; Bailey, Jeremy Clyde; Lee, Ching-Pang
- US Patent Document 6,984,102
Thermal shield turbine airfoil
patent, March 2006
- Lee, Ching-Pang; Bunker, Ronald Scott
- US Patent Document 7,011,502
Hot gas path component with mesh and impingement cooling
patent, February 2007
- Bunker, Ronald Scott; Lee, Ching-Pang
- US Patent Document 7,182,576
Hot gas path component with mesh and dimpled cooling
patent, March 2007
- Bunker, Ronald Scott; Bailey, Jeremy Clyde; Lee, Ching-Pang
- US Patent Document 7,186,084
Multiple vortex cooling circuit for a thin airfoil
patent, May 2010
- Liang, George
- US Patent Document 7,722,327
Hot gas path component with mesh and impingement cooling
patent-application, June 2005
- Bunker, Ronald Scott; Lee, Ching-Pang
- US Patent Application 10/881506; 20050118023
Vortex Cooling of Turbine Blades
patent-application, December 2005
- LIang, George
- US Patent Application 10/791575; 20050265837