Deposition on film-cooled turbine components was studied in an accelerated test facility. The accelerated deposition facility seeds a natural-gas burning combustor with finely ground coal ash particulate at and 180 m/s . Both cylindrical and shaped holes, with and without thermal barrier coating, were studied over a range of blowing ratios from 0.5 to 4.0. Coolant density ratios were maintained at values from 2.1 to 2.4. Deposition patterns generated with the cylindrical film cooling holes indicated regions of low deposition in the path of the coolant with heightened deposition between film holes. This distinctive pattern was more accentuated at higher blowing ratios. Optical temperature measurements of the turbine component surface during deposition showed elevated temperatures between coolant paths. This temperature nonuniformity became more accentuated as deposition increased, highlighting a mechanism for deposition growth that has been documented on in-service turbines as well. The shaped-hole components exhibited little or no deposition in the region just downstream of the holes due to the distributed coolant film. Close cylindrical hole spacing of 2.25d displayed similar behavior to the shaped-hole configuration.
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July 2012
Research Papers
Deposition Near Film Cooling Holes on a High Pressure Turbine Vane
Weiguo Ai,
Weiguo Ai
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
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Nathan Murray,
Nathan Murray
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
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Thomas H. Fletcher,
Thomas H. Fletcher
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
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Spencer Harding,
Spencer Harding
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
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Scott Lewis,
Scott Lewis
Department of Mechanical Engineering,
Ohio State University
, Columbus, OH 43210
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Jeffrey P. Bons
Jeffrey P. Bons
Department of Aerospace Engineering,
Ohio State University
, Columbus, OH 43210
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Weiguo Ai
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
Nathan Murray
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
Thomas H. Fletcher
Department of Chemical Engineering,
Brigham Young University
, Provo, UT 84602
Spencer Harding
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602
Scott Lewis
Department of Mechanical Engineering,
Ohio State University
, Columbus, OH 43210
Jeffrey P. Bons
Department of Aerospace Engineering,
Ohio State University
, Columbus, OH 43210J. Turbomach. Jul 2012, 134(4): 041013 (11 pages)
Published Online: July 21, 2011
Article history
Received:
October 12, 2010
Revised:
November 30, 2010
Online:
July 21, 2011
Published:
July 21, 2011
Citation
Ai, W., Murray, N., Fletcher, T. H., Harding, S., Lewis, S., and Bons, J. P. (July 21, 2011). "Deposition Near Film Cooling Holes on a High Pressure Turbine Vane." ASME. J. Turbomach. July 2012; 134(4): 041013. https://doi.org/10.1115/1.4003672
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