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  5. <title>UTas ePrints - Flow visualisation of the external flow from a converging slot-hole film-cooling geometry</title>
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  13. <meta content="Sargison, Jane E." name="eprints.creators_name" />
  14. <meta content="Oldfield, Martin L.G." name="eprints.creators_name" />
  15. <meta content="Guo, S.M." name="eprints.creators_name" />
  16. <meta content="Lock, Gary D." name="eprints.creators_name" />
  17. <meta content="Rawlinson, Anton J." name="eprints.creators_name" />
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  27. <meta content="Flow visualisation of the external flow from a converging slot-hole film-cooling geometry" name="eprints.title" />
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  32. <meta content="The original publication is available at http://www.springerlink.com/content/100416/" name="eprints.note" />
  33. <meta content="This paper presents flow visualisation experiments
  34. for a novel film-cooling hole, the converging
  35. slot-hole or console for short. Previously published
  36. experimental results have demonstrated that the console
  37. improved both the heat transfer and the aerodynamic
  38. performance of turbine vane and rotor blade cooling
  39. systems. Flow visualisation data for a row of consoles
  40. were compared with that of cylindrical and fan-shaped
  41. holes and a slot at the same inclination angle of 35° to
  42. the surface, on a large-scale, flat-plate model at enginerepresentative
  43. Reynolds numbers in a low speed tunnel
  44. with ambient temperature mainstream flow. In the first
  45. set of experiments, the flow was visualised by using a fine
  46. nylon mesh covered with thermochromic liquid crystals,
  47. allowing the measurement of gas temperature contours
  48. in planes perpendicular to the flow. This data demonstrated
  49. that the console film was similar to a slot film,
  50. and remained thin and attached to the surface for the
  51. coolant-to-mainstream momentum flux ratios of 1.1 to
  52. 40 and for a case with no crossflow (infinite momentum
  53. flux ratio). A second set of flow visualisation experiments
  54. using water/dry-ice fog have confirmed these
  55. results and have shown that the flow through all coolant
  56. geometries is unsteady." name="eprints.abstract" />
  57. <meta content="2005-03" name="eprints.date" />
  58. <meta content="published" name="eprints.date_type" />
  59. <meta content="Experiments in Fluids" name="eprints.publication" />
  60. <meta content="38" name="eprints.volume" />
  61. <meta content="3" name="eprints.number" />
  62. <meta content="304-318" name="eprints.pagerange" />
  63. <meta content="10.1007/s00348-004-0892-1" name="eprints.id_number" />
  64. <meta content="TRUE" name="eprints.refereed" />
  65. <meta content="0723-4864" name="eprints.issn" />
  66. <meta content="http://dx.doi.org/10.1007/s00348-004-0892-1" name="eprints.official_url" />
  67. <meta content="Day CRB, Oldfield MLG, Lock GD (2000) Aerodynamic performance of an annular cascade of film cooled nozzle guide vanes under engine representative conditions. Exp Fluids 29:117–129
  68. Eckert ERG, Drake RM (1972) Analysis of heat and mass transfer. McGraw Hill, New York, pp 453–466
  69. Ekkad SV, Zapata D, Han JC (1997a) Heat transfer coefficient
  70. measurement over a flat surface with air and CO2 injection
  71. through compound angle holes using a transient liquid crystal method. J Turbomach 119:580–586
  72. Ekkad SV, Zapata D, Han JC (1997b) Film effectiveness measurement over a flat surface with air and CO2 injection through compound angle holes using a transient liquid crystal method. J Turbomach 119:587–592
  73. Farmer JP, Seager DJ, Liburdy JA (1997) The effect of shaping inclined slots on film cooling effectiveness and heat transfer coefficient. ASME Paper 97-GT-399
  74. Goldstein RJ, Eckert ERG, Ramsey JW (1968) Film cooling with
  75. injection through holes: adiabatic wall temperatures downstream of a circular hole. J Eng Power 90:384–395
  76. Gritsch M, Schulz A, Wittig S (1997) Discharge coefficient measurements of film cooling holes with expanded exits. ASME Paper 97-GT-165
  77. Gritsch M, Schulz A, Wittig S (1998) Adiabatic wall effectiveness measurements of film cooling holes with expanded exits. J Turbomach 120:549–556
  78. Ligrani P, Ciriello S, Bishop DT (1992) Heat transfer, adiabatic effectiveness and injectant distributions downstream of a single row and two staggered rows of compound angle film-cooling holes. J Turbomach 114:687–700
  79. Mann C (2002) Flow visualisation of turbine blade film cooling. Final year project report, Department of Engineering Science, University of Oxford
  80. Mee DJ, Ireland PT, Bather S (1999) Measurement of the temperature field downstream of simulated leading-edge filmcooling holes. Exp Fluids 27:273–283
  81. Oldfield MLG, Lock GD (1998) Coolant passages for gas turbine components, UK patent application no. 9821639.3 (1998) for the new Console converging slot hole turbine film cooling hole geometry, University of Oxford, Oxford, UK
  82. Sargison JE, Guo SM, Oldfield MLG, Lock GD, Rawlinson AJ
  83. (2002a) A converging slot–hole film-cooling geometry. Part 1: low speed flat-plate heat transfer and loss. J Turbomach
  84. 124:453–460
  85. Sargison JE, Guo SM, Oldfield MLG, Lock GD, Rawlinson AJ
  86. (2002b) A converging slot–hole film-cooling geometry. Part 2: transonic guide vane heat transfer and loss. J Turbomach
  87. 124:461–471
  88. Sargison JE, Guo SM, Oldfield MLG, Lock GD, Rawlinson AJ
  89. (2002c) Flow visualisation of a converging slot–hole film-cooling geometry, ASME Paper GT-2002–30177
  90. Schlichting H (1979) Boundary-layer theory, 7th edn. McGraw-
  91. Hill, New York
  92. Schmidt DL, Sen B, Bogard DG (1994) Film cooling with compound angle holes: adiabatic effectiveness. ASME Paper 94-
  93. GT-312
  94. Seban RA (1960) Heat transfer and effectiveness for a turbulent boundary layer with tangential fluid injection. J Heat Transfer 82:303–312
  95. Sen B, Schmidt DL, Bogard DG (1996) Film cooling with compound angle holes: heat transfer. J Turbomach 118:800–806
  96. Thole K, Gritsch M, Schulz A, Wittig S (1996) Flowfield measurements for film-cooling holes with expanded exits. J Turbomach
  97. 118:327–336
  98. Wang Z, Ireland PT, Kohler ST (1996) Gas temperature measurement in internal cooling passages. ASME Paper 96-GT-534
  99. Weighardt K (1943) Hot air discharge for de-icing (in German). ATI 24536 (original in Dt Luftfahrtforsch Forschungsber)" name="eprints.referencetext" />
  100. <meta content="Sargison, Jane E. and Oldfield, Martin L.G. and Guo, S.M. and Lock, Gary D. and Rawlinson, Anton J. (2005) Flow visualisation of the external flow from a converging slot-hole film-cooling geometry. Experiments in Fluids, 38 (3). pp. 304-318. ISSN 0723-4864" name="eprints.citation" />
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  104. <meta content="Sargison, Jane E." name="DC.creator" />
  105. <meta content="Oldfield, Martin L.G." name="DC.creator" />
  106. <meta content="Guo, S.M." name="DC.creator" />
  107. <meta content="Lock, Gary D." name="DC.creator" />
  108. <meta content="Rawlinson, Anton J." name="DC.creator" />
  109. <meta content="290501 Mechanical Engineering" name="DC.subject" />
  110. <meta content="290201 Aerodynamics" name="DC.subject" />
  111. <meta content="This paper presents flow visualisation experiments
  112. for a novel film-cooling hole, the converging
  113. slot-hole or console for short. Previously published
  114. experimental results have demonstrated that the console
  115. improved both the heat transfer and the aerodynamic
  116. performance of turbine vane and rotor blade cooling
  117. systems. Flow visualisation data for a row of consoles
  118. were compared with that of cylindrical and fan-shaped
  119. holes and a slot at the same inclination angle of 35° to
  120. the surface, on a large-scale, flat-plate model at enginerepresentative
  121. Reynolds numbers in a low speed tunnel
  122. with ambient temperature mainstream flow. In the first
  123. set of experiments, the flow was visualised by using a fine
  124. nylon mesh covered with thermochromic liquid crystals,
  125. allowing the measurement of gas temperature contours
  126. in planes perpendicular to the flow. This data demonstrated
  127. that the console film was similar to a slot film,
  128. and remained thin and attached to the surface for the
  129. coolant-to-mainstream momentum flux ratios of 1.1 to
  130. 40 and for a case with no crossflow (infinite momentum
  131. flux ratio). A second set of flow visualisation experiments
  132. using water/dry-ice fog have confirmed these
  133. results and have shown that the flow through all coolant
  134. geometries is unsteady." name="DC.description" />
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  246. <h1 class="ep_tm_pagetitle">Flow visualisation of the external flow from a converging slot-hole film-cooling geometry</h1>
  247. <p style="margin-bottom: 1em" class="not_ep_block"><span class="person_name">Sargison, Jane E.</span> and <span class="person_name">Oldfield, Martin L.G.</span> and <span class="person_name">Guo, S.M.</span> and <span class="person_name">Lock, Gary D.</span> and <span class="person_name">Rawlinson, Anton J.</span> (2005) <xhtml:em>Flow visualisation of the external flow from a converging slot-hole film-cooling geometry.</xhtml:em> Experiments in Fluids, 38 (3). pp. 304-318. ISSN 0723-4864</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/2259/1/final_Exp_Fluids_2005.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/2259/1/final_Exp_Fluids_2005.pdf"><span class="ep_document_citation">PDF</span></a> - Full text restricted - Requires a PDF viewer<br />1399Kb</td><td><form method="get" accept-charset="utf-8" action="http://eprints.utas.edu.au/cgi/request_doc"><input accept-charset="utf-8" value="2844" 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://dx.doi.org/10.1007/s00348-004-0892-1">http://dx.doi.org/10.1007/s00348-004-0892-1</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 flow visualisation experiments&#13;
  248. for a novel film-cooling hole, the converging&#13;
  249. slot-hole or console for short. Previously published&#13;
  250. experimental results have demonstrated that the console&#13;
  251. improved both the heat transfer and the aerodynamic&#13;
  252. performance of turbine vane and rotor blade cooling&#13;
  253. systems. Flow visualisation data for a row of consoles&#13;
  254. were compared with that of cylindrical and fan-shaped&#13;
  255. holes and a slot at the same inclination angle of 35° to&#13;
  256. the surface, on a large-scale, flat-plate model at enginerepresentative&#13;
  257. Reynolds numbers in a low speed tunnel&#13;
  258. with ambient temperature mainstream flow. In the first&#13;
  259. set of experiments, the flow was visualised by using a fine&#13;
  260. nylon mesh covered with thermochromic liquid crystals,&#13;
  261. allowing the measurement of gas temperature contours&#13;
  262. in planes perpendicular to the flow. This data demonstrated&#13;
  263. that the console film was similar to a slot film,&#13;
  264. and remained thin and attached to the surface for the&#13;
  265. coolant-to-mainstream momentum flux ratios of 1.1 to&#13;
  266. 40 and for a case with no crossflow (infinite momentum&#13;
  267. flux ratio). A second set of flow visualisation experiments&#13;
  268. using water/dry-ice fog have confirmed these&#13;
  269. results and have shown that the flow through all coolant&#13;
  270. geometries is unsteady.</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">Additional Information:</th><td valign="top" class="ep_row">The original publication is available at http://www.springerlink.com/content/100416/</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><br /><a href="http://eprints.utas.edu.au/view/subjects/290201.html">290000 Engineering and Technology &gt; 290200 Aerospace Engineering &gt; 290201 Aerodynamics</a></td></tr><tr><th valign="top" class="ep_row">ID Code:</th><td valign="top" class="ep_row">2259</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">22 Oct 2007 23:22</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=2259;">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=2259">item control page</a></p>
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