Impingement cooling through jet holes is a very attractive cooling system for heat rejection at high heat loaded areas as the leading edge of turbine vanes. Although some correlations and tools are available to dimension such systems, the variety and complexity of the flow features present in those systems still require experimental validation of real engine designs. Among the experimental techniques possible to be used, transient liquid crystal method offers good resolution as well as sufficient accuracy. Under this investigation, an impingement cooling system for the leading edge of a contrarotating power turbine (PT) representative of a small turboshaft engine was investigated experimentally. The PT vane features a very thin leading edge with high curvature and side channels rapidly turning backward. Constraints on cooling flow consumption and distribution led to a leading edge configuration with two rows of staggered jets. This particular configuration was experimentally investigated for three different Reynolds numbers around the design point by using a transient liquid crystal technique, which allows the measurement of surface distribution of heat transfer coefficient at the area of interest. Heat transfer results are presented in terms of surface distributions, impingement rows stagnation line local distributions, streamwise distributions along planes over the impingement stagnation points, span averaged streamwise local distributions, and surface averaged values. These results are then compared with available correlations from existing literature showing good matching for both maximum and averaged values. The results are also used as baseline data to discuss some of the flow features that can have effect on the heat transfer on this particular configuration.
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e-mail: pedro.delacalzada@itp.es
e-mail: josejavier.alvarez@itp.es
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December 2010
This article was originally published in
Journal of Heat Transfer
Research Papers
Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes
Pedro de la Calzada,
e-mail: pedro.delacalzada@itp.es
Pedro de la Calzada
ITP, Industria de Turbopropulsores S.A.
, Avda Castilla 2, San Fernando de Henares, 28830 Madrid, Spain
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Jose Javier Alvarez
e-mail: josejavier.alvarez@itp.es
Jose Javier Alvarez
ITP, Industria de Turbopropulsores S.A.
, Avda Castilla 2, San Fernando de Henares, 28830 Madrid, Spain
Search for other works by this author on:
Pedro de la Calzada
ITP, Industria de Turbopropulsores S.A.
, Avda Castilla 2, San Fernando de Henares, 28830 Madrid, Spaine-mail: pedro.delacalzada@itp.es
Jose Javier Alvarez
ITP, Industria de Turbopropulsores S.A.
, Avda Castilla 2, San Fernando de Henares, 28830 Madrid, Spaine-mail: josejavier.alvarez@itp.es
J. Heat Transfer. Dec 2010, 132(12): 122202 (8 pages)
Published Online: September 21, 2010
Article history
Received:
April 23, 2010
Revised:
July 2, 2010
Online:
September 21, 2010
Published:
September 21, 2010
Citation
de la Calzada, P., and Alvarez, J. J. (September 21, 2010). "Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes." ASME. J. Heat Transfer. December 2010; 132(12): 122202. https://doi.org/10.1115/1.4002206
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