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    <title>UTas ePrints - A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane 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 2:
Transonic nozzle guide vane heat transfer and loss" name="eprints.title" />
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<meta content="This paper presents the first experimental measurements on
an engine representative nozzle guide vane, of a new film
cooling hole geometry, a Converging Slot-Hole or Console.
The patented console geometry is designed to improve the heat
transfer and aerodynamic performance of turbine vane and
rotor blade cooling systems. These experiments follow the
successful validation of the console design in low-speed flatplate
tests described in Part 1 of this paper (Sargison et al [1]).
Stereolithography was used to manufacture a resin model
of a transonic, engine representative nozzle guide vane in
which 7 rows of previously tested fan-shaped film-cooling
holes were replaced by 4 rows of consoles. This vane was
mounted in the annular vane ring of the Oxford Cold Heat
Transfer Tunnel for testing at engine Reynolds numbers, Mach
numbers and coolant to mainstream momentum flux ratios
using a heavy gas to simulate the correct coolant to mainstream
density ratio.
Heat transfer data were measured using wide band
thermochromic liquid crystals and a modified analysis
technique. Both surface heat transfer coefficient and the
adiabatic cooling effectiveness were derived from computervideo
records of hue changes during the transient tunnel run.
The cooling performance, quantified by the heat flux at engine
temperature levels, of the console vane compares favourably
with that of the previously tested vane with fan-shaped holes.
The new console film cooling hole geometry offers
advantages to the engine designer due to a superior
aerodynamic efficiency over the fan-shaped hole geometry.
These efficiency measurements are demonstrated by results
from mid span traverses of a four hole pyramid probe
downstream of the nozzle guide vane." name="eprints.abstract" />
<meta content="2002" name="eprints.date" />
<meta content="published" name="eprints.date_type" />
<meta content="Transactions of the ASME: Journal of Turbomachinery" name="eprints.publication" />
<meta content="124" name="eprints.volume" />
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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, &quot;A Converging Slot-Hole Film-Cooling
Geometry. Part 1: Low Speed Flat-Plate Heat Transfer and
Loss&quot;, ASME Paper 2001-GT-0126
[2] Denton, J.D., 1993, “Loss Mechanisms in Turbomachines”,
ASME Journal of Turbomachinery, 115, pp. 621-656
[3] Ito, S., Goldstein, R.J., Eckert, E.R.G., 1978 “Film Cooling
of a Gas Turbine Blade”, ASME Journal of Engineering for
Power, 100 pp. 476-481
[4] Schwarz, S.G., and Goldstein, R.J., 1989, “The Two-
Dimensional Behaviour of Film Cooling Jets on Concave
Surfaces”, ASME Journal of Turbomachinery 111, pp. 124-130
[5] Ko, S.Y., Yao, Y.Q., Xia, B., and Tsou, F.K., 1986,
“Discrete-Hole Film Cooling Characteristics over Concave and
Convex Surfaces”, Proceedings of the 8th International Heat
Transfer Conference, Hemisphere Publishing Corp., New York,
3, pp. 1297-1301
[6] Ligrani, P.M., and Camci, C., 1985 “Adiabatic Film Cooling
Effectiveness from Heat Transfer Measurements in
Compressible, Variable-Property Flow”, ASME Journal of Heat
Transfer, 107, pp. 313-320
[7] Arts, T., and Bourguignon, A.E., 1990, “Behaviour of a
Coolant Film with Two Rows of Holes Along the Pressure Side
of a High-Pressure Nozzle Guide Vane”, ASME Journal of
Turbomachinery, 112, pp 512-521
[8] Camci, C., and Arts, T., 1985, “Short Duration
Measurements and Numerical Simulation of Heat Transfer
Along the Suction Side of a Film Cooled Gas Turbine Blade”,
ASME Journal of Engineering for Gas Turbines and Power,
107, No.4, pp. 991-997
[9] Drost, U., Bolcs, A., Hoffs, A., 1997, “Utilization of the
Transient Liquid Crystal Technique for Film Cooling
Effectiveness and Heat Transfer Investigations on a Flat Plate
and a Turbine Airfoil”, ASME Paper 97-GT-28
[10] Schlichting, H. and Gersten, K., 2000, Boundary Layer
Theory, Springer, Berlin
[11] Martinez-Botas, R.F., Main, A.J., Lock, G.D., and
Oldfield, M.L.G., 1993, “A Cold Heat Transfer Tunnel for Gas
14 Copyright © 2001 by ASME
Turbine Research on an Annular Cascade”, ASME Paper 93-
GT-248
[12] Moss, R.W. and Oldfield, M.L.G., 1991, “Measurements
of Hot Combustor Turbulence Spectra”, ASME Paper No. 91-
GT-351
[13] Springer, A., 1998, “Evaluating Aerodynamic
Characteristics of Wind-Tunnel Models Produced by Rapid
Prototyping Methods”, Journal of Spacecraft and Rockets, 35,
No.6
[14] Teekaram, A.J.H., Forth, C.J.P., and Jones, T.V., 1989,
“The Use of Foreign Gas to Simulate the Effects of Density
Ratios in Film Cooling”, ASME Journal of Turbomachinery,
111 pp. 57-62
[15] Guo, S.M., Lai, C.C., Jeong, J.H., Jones, T.V., and
Oldfield, M.L.G., 1997, “Use of Liquid Crystal Techniques to
Measure Film Cooling Heat Transfer and Effectiveness”, 90th
Symposium of the Propulsion and Energetics Panel, AGARD
[16] Ireland, P.T., Wang, Z.W. and Jones T.V., 1993, “Liquid
Crystal Heat Transfer Measurements”, von Karman Institute for
Fluid Dynamics 1992-1993 Lecture Series.
[17] Ireland, P.T. and Jones, T.V., 1987, “The Response Time of
a Surface Thermometer Employing Encapsulated
Thermochromic Liquid Crystals”, Journal of Physics E, 20, pp
1195-1199
[18] Sargison, J.E., Guo, S.M., Oldfield, M.L.G., Lock G.D.
and Rawlinson, A.J, 2000, “Use of Liquid Crystal Techniques
for a Gas Turbine Film Cooling Study in a Transonic Tunnel”,
Proceedings of 9th International Symposium on Flow
Visualisation, Heriot-Watt University, Edinburgh, 2000.
[19] Gonzalez, R.C. and Woods, R.E., 1993, “Digital Image
Processing”, Addison-Wesley
[20] 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
[21] 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
[22] Kays, W.M. and Crawford, M.E., 1993, Convective Heat
and Mass Transfer, McGraw-Hill, New York
[23] Schultz, D.L. and Jones, T.V., 1973, “Heat Transfer
Measurements in Short-Duration Hypersonic Facilities”,
AGARD AG-165
[24] Guo, S.M., Lai, C.C., Jones, T.V., Oldfield, M.L.G., Lock
G.D., and Rawlinson, A.J., 1998, “The Application of Thin-
Film Technology to Measure Turbine-Vane Heat Transfer and
Effectiveness in a Film-Cooled, Engine-Simulated
Environment”, International Journal of Heat and Fluid Flow,
19, pp. 564-600
[25] Doorly, J.E. and Oldfield, M.L.G., 1987, “The Theory of
Advanced Multi-layer Thin Film Heat Transfer Gauges”,
International Journal of Heat and Mass Transfer, 30, No.6, pp.
1159-1168
[26] Ainsworth, R.W., Allen, J.L., Davies, M.R.D., Doorly,
J.E., Forth, C.J.P., Hilditch, M.A., Oldfield, M.L.G. and Sheard,
A.G., 1989, “Developments in Instrumentation and Processing
for Transient Heat Transfer Measurements in a Full Stage
Model Turbine”, ASME Journal of Turbomachinery, 111, pp.
20-27
[27] Ireland, P.T. and Jones, T.V., 2000, “Liquid Crystal
Measurement of Heat Transfer and Shear Stress”, Measurement
Science Technology 2000, 11, pp.969 - 986.
[28] Lai, C.C., 1999, “Fully Film Cooled Nozzle Guide Vane
Heat Transfer Measurement and Prediction”, DPhil Thesis,
University of Oxford
[29] Rowbury, D.A., Oldfield, M.L.G., and Lock, G.D., 1997,
“Engine-Representative Discharge Coefficients Measured in an
Annular Nozzle Guide Vane Cascade”, ASME Paper No. 97-
GT-99
[30] Sen, B., Schmidt, D.L. and Bogard D.G. 1994 Film
Cooling with Compound Angle Holes: Heat Transfer ASME
Paper 94-GT-311
[31] Main A.J., 1994, “Annular Turbine Cascade
Aerodynamics”, DPhil Thesis, University of Oxford
[32] Main, A.J., Day, C.R.B., Lock, G.D., and Oldfield,
M.L.G., 1996, “Calibration of a four-hole pyramid probe and
area traverse measurements in a short-duration transonic
turbine cascade tunnel”, Experiments in Fluids, 21, pp. 302-311
[33] Day, C.R.B., Oldfield, M.L.G., Lock, G.D., 1999, “The
Influence of Film Cooling on the Efficiency of an Annular
Nozzle Guide Vane Cascade”, ASME Journal of
Turbomachinery, 121, No.1, pp.145-151 (Also ASME Paper
97-GT-521)
[34] 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 2, pp. 117-129
[35] Dzung, L.S., 1971, “Konsistente Mittelwerte in der
Theorie der Turbomaschinen fur Kompressible Medien”, BBCMitt.,
58, pp. 485-492" name="eprints.referencetext" />
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<meta content="290501 Mechanical Engineering" name="DC.subject" />
<meta content="This paper presents the first experimental measurements on
an engine representative nozzle guide vane, of a new film
cooling hole geometry, a Converging Slot-Hole or Console.
The patented console geometry is designed to improve the heat
transfer and aerodynamic performance of turbine vane and
rotor blade cooling systems. These experiments follow the
successful validation of the console design in low-speed flatplate
tests described in Part 1 of this paper (Sargison et al [1]).
Stereolithography was used to manufacture a resin model
of a transonic, engine representative nozzle guide vane in
which 7 rows of previously tested fan-shaped film-cooling
holes were replaced by 4 rows of consoles. This vane was
mounted in the annular vane ring of the Oxford Cold Heat
Transfer Tunnel for testing at engine Reynolds numbers, Mach
numbers and coolant to mainstream momentum flux ratios
using a heavy gas to simulate the correct coolant to mainstream
density ratio.
Heat transfer data were measured using wide band
thermochromic liquid crystals and a modified analysis
technique. Both surface heat transfer coefficient and the
adiabatic cooling effectiveness were derived from computervideo
records of hue changes during the transient tunnel run.
The cooling performance, quantified by the heat flux at engine
temperature levels, of the console vane compares favourably
with that of the previously tested vane with fan-shaped holes.
The new console film cooling hole geometry offers
advantages to the engine designer due to a superior
aerodynamic efficiency over the fan-shaped hole geometry.
These efficiency measurements are demonstrated by results
from mid span traverses of a four hole pyramid probe
downstream of the nozzle guide vane." name="DC.description" />
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    <h1 class="ep_tm_pagetitle">A converging slot-hole film-cooling geometry - Part 2: Transonic nozzle guide vane 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 2: Transonic nozzle guide vane 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/2310/1/2001-GT-0127.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/2310/1/2001-GT-0127.pdf"><span class="ep_document_citation">PDF</span></a> - Full text restricted - Requires a PDF viewer<br />943Kb</td><td><form method="get" accept-charset="utf-8" action="http://eprints.utas.edu.au/cgi/request_doc"><input accept-charset="utf-8" value="2960" 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 the first experimental measurements on&#13;
an engine representative nozzle guide vane, of a new film&#13;
cooling hole geometry, a Converging Slot-Hole or Console.&#13;
The patented console geometry is designed to improve the heat&#13;
transfer and aerodynamic performance of turbine vane and&#13;
rotor blade cooling systems. These experiments follow the&#13;
successful validation of the console design in low-speed flatplate&#13;
tests described in Part 1 of this paper (Sargison et al [1]).&#13;
Stereolithography was used to manufacture a resin model&#13;
of a transonic, engine representative nozzle guide vane in&#13;
which 7 rows of previously tested fan-shaped film-cooling&#13;
holes were replaced by 4 rows of consoles. This vane was&#13;
mounted in the annular vane ring of the Oxford Cold Heat&#13;
Transfer Tunnel for testing at engine Reynolds numbers, Mach&#13;
numbers and coolant to mainstream momentum flux ratios&#13;
using a heavy gas to simulate the correct coolant to mainstream&#13;
density ratio.&#13;
Heat transfer data were measured using wide band&#13;
thermochromic liquid crystals and a modified analysis&#13;
technique. Both surface heat transfer coefficient and the&#13;
adiabatic cooling effectiveness were derived from computervideo&#13;
records of hue changes during the transient tunnel run.&#13;
The cooling performance, quantified by the heat flux at engine&#13;
temperature levels, of the console vane compares favourably&#13;
with that of the previously tested vane with fan-shaped holes.&#13;
The new console film cooling hole geometry offers&#13;
advantages to the engine designer due to a superior&#13;
aerodynamic efficiency over the fan-shaped hole geometry.&#13;
These efficiency measurements are demonstrated by results&#13;
from mid span traverses of a four hole pyramid probe&#13;
downstream of the nozzle guide vane.</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">2310</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 08:54</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=2310;">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=2310">item control page</a></p>
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