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    <title>UTas ePrints - A Converging Slot-Hole Film-Cooling Geometry Part 1: Low-Speed Flat-Plate Heat Transfer and Loss</title>
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    <meta content="Sargison, Jane E." name="eprints.creators_name" />
<meta content="Guo, S.M." name="eprints.creators_name" />
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<meta content="A Converging Slot-Hole Film-Cooling Geometry Part 1: Low-Speed Flat-Plate Heat Transfer and Loss" name="eprints.title" />
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<meta content="This paper presents experimental measurements of the
performance of a new film cooling hole geometry - the
Converging Slot-Hole or Console. This novel, patented
geometry has been designed to improve the heat transfer and
aerodynamic loss performance of turbine vane and rotor blade
cooling systems. The physical principles embodied in the new
hole design are described, and a typical example of the console geometry is presented.
The cooling performance of a single row of consoles was
compared experimentally with that of typical 35° cylindrical
and fan-shaped holes and a slot, on a large-scale, flat-plate model at engine representative Reynolds numbers in a low speed tunnel with ambient temperature main flow. The hole throat area per unit width is matched for all four hole geometries. By independently varying the temperature of the heated coolant and the heat flux from an electrically heated, thermally insulated, constant heat flux surface, both the heat transfer coefficient and the adiabatic cooling effectiveness were deduced from digital photographs of the colour play of narrowband thermochromic liquid crystals on the model surface.
A comparative measurement of the aerodynamic losses
associated with each of the four film-cooling geometries was
made by traversing the boundary layer at the downstream end of the flat plate.
The promising heat transfer and aerodynamic performance
of the console geometry have justified further experiments on an engine representative nozzle guide vane in a transonic
annular cascade presented in Part 2 of this paper [1]." name="eprints.abstract" />
<meta content="2002" name="eprints.date" />
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<meta content="[1] Sargison, J.E., Guo, S.M., Oldfield, M.L.G., Lock, G.D.,
and Rawlinson, A.J., 2001, “A Converging Slot-Hole Film-
Cooling Geometry. Part 2: Transonic Guide Vane Heat Transfer
and Loss”, ASME Paper 2001-GT-0127
[2] Denton, J.D., 1993, “Loss Mechanisms in Turbomachines”,
Journal of Turbomachinery, 115, pp.621-656
[3] Eckert, E.R.G. and Drake, R.M., 1972, “Analysis of Heat
and Mass Transfer”, McGraw Hill pp 453-466
[4] Farmer, J.P., Seager, D.J., and Liburdy, J.A. 1997 “The
Effect of Shaping Inclined Slots on Film Cooling Effectiveness
and Heat Transfer Coefficient” ASME Paper 97-GT-399
[5] Ligrani, P., Ciriello, S., and Bishop, D.T. 1992 “Heat
Transfer, Adiabatic Effectiveness and Injectant Distributions
Downstream of a Single Row and Two Staggered Rows of
Compound Angle Film-Cooling Holes”, ASME Journal of
Turbomachinery, 114, pp. 687-700
[6] Sen, B., Schmidt, D.L. and Bogard D.G., 1996 “Film
Cooling with Compound Angle Holes: Heat Transfer” ASME
Journal of Turbomachinery, 118, 800-806
[7] Schmidt, D.L., Sen, B. and Bogard, D.G., 1994, “Film
Cooling with Compound Angle Holes: Adiabatic Effectiveness”
ASME Paper 94-GT-312
[8] Gritsch, M., Schulz, A., and Wittig, S., 1998, “Heat Transfer
Coefficient Measurements of Film-Cooling Holes with
Expanded Exits” ASME Paper 98-GT-28
[9] Gritsch, M., Schulz, A., and Wittig, S., 1997, “Adiabatic
Wall Effectiveness Measurements of Film-Cooling Holes with
Expanded Exits” ASME Journal of Turbomachinery, 120, pp.
560-567
[10] Thole, K., Gritsch, M., Schulz, A., and Wittig, S., 1996,
“Flowfield Measurements for Film-Cooling Holes with
Expanded Exits” ASME Journal of Turbomachinery, pp. 327-
336
[11] Day, C.R.B., Oldfield, M.L.G. and Lock, G.D., 2000,
“Aerodynamic Performance of an Annular Cascade of Film
Cooled Nozzle Guide Vanes Under Engine Representative
Conditions”, Experiments in Fluids, 29, pp. 117-129
[12] Schlichting, H., 1979, “Boundary-Layer Theory”,
McGraw-Hill Book Company, Seventh Edition, New York.
[13] Sargison, J.E., Guo, S.M., Oldfield, M.L.G., Lock, G.D.,
Rawlinson, A.J., 2000, “The Variation of Heat Transfer
Coefficient, Adiabatic Effectiveness and Aerodynamic Loss
with Film Cooling Hole Shape” Proceedings of the Turbine-
2000, International Symposium on Heat Transfer in Gas
Turbine Systems, Turkey
[14] Kays, W.M. and Crawford, M.E., 1993, Convective Heat
and Mass Transfer, McGraw-Hill, New York.
[15] Jones, T.V., 1991, “Definition of Heat Transfer Coefficient
in the Turbine Situation”, IMechE 1991-3, C423/046,
Turbomachinery: Latest Developments in a Changing Scene,
pp. 201-206
[16] Jones, T.V., 1999, “Theory for the use of Foreign Gas in
Simulating Film Cooling”, International Journal of Heat and
Fluid Flow, 20, pp. 349-354
[17] Ekkad, S.V., Zapata, D. and Han, J.C., 1995 “Heat
Transfer Coefficient over a Flat Surface with Air and CO2
Injection Through Compound Angle Holes Using a Transient
Liquid Crystal Image Method” ASME Journal of
Turbomachinery, 119, pp. 580-586
[18] Ekkad, S.V., Zapata, D. and Han, J.C., 1995, “Film
Effectiveness over a Flat Surface with Air and CO2 Injection
Through Compound Angle Holes Using a Transient Liquid
Crystal Image Method”, ASME Journal of Turbomachinery,
119, pp. 587-592
[19] Mee, D.J., Ireland, P.T. and Bather, S., 1999,
“Measurement of the temperature field downstream of
simulated leading-edge film-cooling holes”, Experiments in
Fluids, 27, pp.273-283" name="eprints.referencetext" />
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<meta content="Lock, Gary D." name="DC.creator" />
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<meta content="This paper presents experimental measurements of the
performance of a new film cooling hole geometry - the
Converging Slot-Hole or Console. This novel, patented
geometry has been designed to improve the heat transfer and
aerodynamic loss performance of turbine vane and rotor blade
cooling systems. The physical principles embodied in the new
hole design are described, and a typical example of the console geometry is presented.
The cooling performance of a single row of consoles was
compared experimentally with that of typical 35° cylindrical
and fan-shaped holes and a slot, on a large-scale, flat-plate model at engine representative Reynolds numbers in a low speed tunnel with ambient temperature main flow. The hole throat area per unit width is matched for all four hole geometries. By independently varying the temperature of the heated coolant and the heat flux from an electrically heated, thermally insulated, constant heat flux surface, both the heat transfer coefficient and the adiabatic cooling effectiveness were deduced from digital photographs of the colour play of narrowband thermochromic liquid crystals on the model surface.
A comparative measurement of the aerodynamic losses
associated with each of the four film-cooling geometries was
made by traversing the boundary layer at the downstream end of the flat plate.
The promising heat transfer and aerodynamic performance
of the console geometry have justified further experiments on an engine representative nozzle guide vane in a transonic
annular cascade presented in Part 2 of this paper [1]." name="DC.description" />
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    <h1 class="ep_tm_pagetitle">A Converging Slot-Hole Film-Cooling Geometry Part 1: Low-Speed Flat-Plate Heat Transfer and Loss</h1>
    <p style="margin-bottom: 1em" class="not_ep_block"><span class="person_name">Sargison, Jane E.</span> and <span class="person_name">Guo, S.M.</span> and <span class="person_name">Oldfield, Martin L.G.</span> and <span class="person_name">Lock, Gary D.</span> (2002) <xhtml:em>A Converging Slot-Hole Film-Cooling Geometry Part 1: Low-Speed Flat-Plate Heat Transfer and Loss.</xhtml:em> Transactions of the ASME: Journal of Turbomachinery, 124 (3). pp. 461-471. ISSN 0889504x</p><p style="margin-bottom: 1em" class="not_ep_block"></p><table style="margin-bottom: 1em" class="not_ep_block"><tr><td valign="top" style="text-align:center"><a href="http://eprints.utas.edu.au/2308/1/2001-GT-0126.pdf"><img alt="[img]" src="http://eprints.utas.edu.au/style/images/fileicons/application_pdf.png" class="ep_doc_icon" border="0" /></a></td><td valign="top"><a href="http://eprints.utas.edu.au/2308/1/2001-GT-0126.pdf"><span class="ep_document_citation">PDF</span></a> - Full text restricted - Requires a PDF viewer<br />871Kb</td><td><form method="get" accept-charset="utf-8" action="http://eprints.utas.edu.au/cgi/request_doc"><input accept-charset="utf-8" value="2958" name="docid" type="hidden" /><div class=""><input value="Request a copy" name="_action_null" class="ep_form_action_button" onclick="return EPJS_button_pushed( '_action_null' )" type="submit" /> </div></form></td></tr></table><p style="margin-bottom: 1em" class="not_ep_block">Official URL: <a href="http://www.asme.org">http://www.asme.org</a></p><div class="not_ep_block"><h2>Abstract</h2><p style="padding-bottom: 16px; text-align: left; margin: 1em auto 0em auto">This paper presents experimental measurements of the&#13;
performance of a new film cooling hole geometry - the&#13;
Converging Slot-Hole or Console. This novel, patented&#13;
geometry has been designed to improve the heat transfer and&#13;
aerodynamic loss performance of turbine vane and rotor blade&#13;
cooling systems. The physical principles embodied in the new&#13;
hole design are described, and a typical example of the console geometry is presented.&#13;
The cooling performance of a single row of consoles was&#13;
compared experimentally with that of typical 35° cylindrical&#13;
and fan-shaped holes and a slot, on a large-scale, flat-plate model at engine representative Reynolds numbers in a low speed tunnel with ambient temperature main flow. The hole throat area per unit width is matched for all four hole geometries. By independently varying the temperature of the heated coolant and the heat flux from an electrically heated, thermally insulated, constant heat flux surface, both the heat transfer coefficient and the adiabatic cooling effectiveness were deduced from digital photographs of the colour play of narrowband thermochromic liquid crystals on the model surface.&#13;
A comparative measurement of the aerodynamic losses&#13;
associated with each of the four film-cooling geometries was&#13;
made by traversing the boundary layer at the downstream end of the flat plate.&#13;
The promising heat transfer and aerodynamic performance&#13;
of the console geometry have justified further experiments on an engine representative nozzle guide vane in a transonic&#13;
annular cascade presented in Part 2 of this paper [1].</p></div><table style="margin-bottom: 1em" cellpadding="3" class="not_ep_block" border="0"><tr><th valign="top" class="ep_row">Item Type:</th><td valign="top" class="ep_row">Article</td></tr><tr><th valign="top" class="ep_row">Subjects:</th><td valign="top" class="ep_row"><a href="http://eprints.utas.edu.au/view/subjects/290501.html">290000 Engineering and Technology &gt; 290500 Mechanical and Industrial Engineering &gt; 290501 Mechanical Engineering</a></td></tr><tr><th valign="top" class="ep_row">ID Code:</th><td valign="top" class="ep_row">2308</td></tr><tr><th valign="top" class="ep_row">Deposited By:</th><td valign="top" class="ep_row"><span class="ep_name_citation"><span class="person_name">Dr Jane Sargison</span></span></td></tr><tr><th valign="top" class="ep_row">Deposited On:</th><td valign="top" class="ep_row">29 Oct 2007 08:55</td></tr><tr><th valign="top" class="ep_row">Last Modified:</th><td valign="top" class="ep_row">09 Jan 2008 02:30</td></tr><tr><th valign="top" class="ep_row">ePrint Statistics:</th><td valign="top" class="ep_row"><a target="ePrintStats" href="/es/index.php?action=show_detail_eprint;id=2308;">View statistics for this ePrint</a></td></tr></table><p align="right">Repository Staff Only: <a href="http://eprints.utas.edu.au/cgi/users/home?screen=EPrint::View&amp;eprintid=2308">item control page</a></p>
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