An experimental survey on a state of the art leading edge cooling scheme was performed to evaluate heat transfer coefficients (HTC) on a large scale test facility simulating a high pressure turbine airfoil leading edge cavity. The test section includes a trapezoidal supply channel with three large racetrack impingement holes. On the internal surface of the leading edge, four big fins are placed in order to confine impingement jets. The coolant flow impacts the leading edge internal surface, and it is extracted from the leading edge cavity through 24 showerhead holes and 24 film cooling holes. The aim of the present study is to investigate the combined effects of jet impingement and mass flow extraction on the internal heat transfer of the leading edge. A nonuniform mass flow extraction was also imposed to reproduce the effects of the pressure side and suction side external pressure. Measurements were performed by means of a transient technique using narrow band thermochromic liquid crystals (TLCs). Jet Reynolds number and crossflow conditions into the supply channel were varied in order to cover the typical engine conditions of these cooling systems (). Experiments were compared with a numerical analysis on the same test case in order to better understand flow interaction inside the cavity. Results are reported in terms of detailed 2D maps, radial-wise, and span-wise averaged values of Nusselt number.
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Research-Article
Heat Transfer Measurements in a Leading Edge Geometry With Racetrack Holes and Film Cooling Extraction
Francesco Maiuolo,
Francesco Maiuolo
1
1Corresponding author.
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Lorenzo Tarchi,
Lorenzo Tarchi
“S. Stecco” Energy Engineering Department,
University of Florence
,Via S. Marta, 3, 50139 Florence
, Italy
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Stefano Zecchi
e-mail: stefano.zecchi@aviogroup.com
Stefano Zecchi
Engineering, Research & Development
,AVIO S.p.A.
, Via Primo Maggio 56
,Rivalta di Torino
,Turin 10040
, Italy
e-mail: stefano.zecchi@aviogroup.com
Search for other works by this author on:
Francesco Maiuolo
Lorenzo Tarchi
“S. Stecco” Energy Engineering Department,
University of Florence
,Via S. Marta, 3, 50139 Florence
, Italy
Stefano Zecchi
Engineering, Research & Development
,AVIO S.p.A.
, Via Primo Maggio 56
,Rivalta di Torino
,Turin 10040
, Italy
e-mail: stefano.zecchi@aviogroup.com
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received June 29, 2012; final manuscript received August 6, 2012; published online March 25, 2013. Editor: David Wisler.
J. Turbomach. May 2013, 135(3): 031020 (9 pages)
Published Online: March 25, 2013
Article history
Received:
June 29, 2012
Revision Received:
August 6, 2012
Citation
Andrei, L., Carcasci, C., Da Soghe, R., Facchini, B., Maiuolo, F., Tarchi, L., and Zecchi, S. (March 25, 2013). "Heat Transfer Measurements in a Leading Edge Geometry With Racetrack Holes and Film Cooling Extraction." ASME. J. Turbomach. May 2013; 135(3): 031020. https://doi.org/10.1115/1.4007527
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