The present paper investigates the effects of a fan-shaped hole endwall cooling geometry on the aero-thermal performance of a nozzle vane cascade. Two endwall cooling geometries with four rows of holes were tested, for different mass flow rate ratios: the first configuration is made of cylindrical holes, whereas the second one features conical expanded exits and a reduced number of holes. The experimental analysis is mainly focused on the variations of secondary flow phenomena related to different injection rates, as they have a strong relationship with the film cooling effectiveness. Secondary flow assessment was performed through downstream 3D aerodynamic measurements, by means of a miniaturized 5-hole probe. The results show that at high injection rates, the passage vortex and the 3D effects tend to become weaker, leading to a strong reduction of the endwall cross flow and to a more uniform flow in spanwise direction. This is of course obtained at the expense of a significant increase of losses. The thermal behavior was then investigated through the analysis of adiabatic effectiveness distributions on the two endwall configurations. The wide-banded thermochromic liquid crystals (TLC) technique was used to determine the adiabatic wall temperature. Using the measured distributions of film-cooling adiabatic effectiveness, the interaction between the secondary flow vortices and the cooling jets can be followed in good detail all over the endwall surface. Fan-shaped holes have been shown to perform better than cylindrical ones: at low injection rates, the cooling performance is increased only in the front part of the vane passage. A larger improvement of cooling coverage all over the endwall is attained with a larger mass flow rate, about 1.5% of core flow, without a substantial increase of the aerodynamic losses.
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e-mail: giovanna.barigozzi@unibg.it
e-mail: antonio.perdichizzi@unibg.it
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January 2006
Technical Papers
Fan-Shaped Hole Effects on the Aero-Thermal Performance of a Film-Cooled Endwall
Giovanna Barigozzi,
Giovanna Barigozzi
Dipartimento di Ingegneria Industriale,
e-mail: giovanna.barigozzi@unibg.it
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
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Giuseppe Benzoni,
Giuseppe Benzoni
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
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Giuseppe Franchini,
Giuseppe Franchini
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
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Antonio Perdichizzi
Antonio Perdichizzi
Dipartimento di Ingegneria Industriale,
e-mail: antonio.perdichizzi@unibg.it
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
Search for other works by this author on:
Giovanna Barigozzi
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italye-mail: giovanna.barigozzi@unibg.it
Giuseppe Benzoni
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
Giuseppe Franchini
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italy
Antonio Perdichizzi
Dipartimento di Ingegneria Industriale,
Università degli Studi di Bergamo
, Viale Marconi 24044, Dalmine (BG), Italye-mail: antonio.perdichizzi@unibg.it
J. Turbomach. Jan 2006, 128(1): 43-52 (10 pages)
Published Online: February 1, 2005
Article history
Received:
October 1, 2004
Revised:
February 1, 2005
Citation
Barigozzi, G., Benzoni, G., Franchini, G., and Perdichizzi, A. (February 1, 2005). "Fan-Shaped Hole Effects on the Aero-Thermal Performance of a Film-Cooled Endwall." ASME. J. Turbomach. January 2006; 128(1): 43–52. https://doi.org/10.1115/1.2098788
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