The present work is part of a detailed aerothermal investigation in a model of a rotating internal cooling channel performed in a novel facility setup which allows test conditions at high rotation numbers (). The test section is mounted on a rotating frame with all the required instrumentation, resulting in a high spatial resolution and accuracy. The channel has a cross section with an aspect ratio of 0.9 and a ribbed wall with eight ribs perpendicular to the main flow direction. The blockage of the ribs is 10% of the channel cross section, whereas the rib pitch-to-height ratio is 10. In this first part of the paper, the flow over the wall region between the sixth and seventh ribs in the symmetry plane is investigated by means of two-dimensional particle image velocimetry (PIV). Tests were carried out at a Reynolds number () of 15,000 in static and rotating conditions, with a maximum of 0.77. Results are in good agreement with the data present in literature at the same Reynolds number and with rotation numbers of 0 (static conditions) and 0.38 in a channel with the same geometry as in the present work. When is increased from 0.38 to 0.77, the main velocity and turbulence fields show important changes. At a rotation number of 0.77, although the extension of the recirculation bubble after the sixth rib on the trailing side does not vary significantly, it covers the full inter-rib area on the leading side in the streamwise direction. The turbulence intensity on the leading side shows a low value with respect to the static case but roughly at the same level as in the lower case. On the trailing side, the maximum value of the turbulence intensity slightly decreases from = 0.38 to = 0.77, the wall shear layer is restabilized along the second half of the pitch due to the high rotation, and the secondary flows are redistributed causing spanwise vortex compression. The observed result is the rapid decay of turbulent fluctuations in the second half of the inter-rib area.
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October 2016
Research-Article
Aerothermal Characterization of a Rotating Ribbed Channel at Engine Representative Conditions—Part I: High-Resolution Particle Image Velocimetry Measurements
Ignacio Mayo,
Ignacio Mayo
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
e-mail: ignacio.mayo.yague@vki.ac.be
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
e-mail: ignacio.mayo.yague@vki.ac.be
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Gian Luca Gori,
Gian Luca Gori
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
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Aude Lahalle,
Aude Lahalle
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
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Tony Arts
Tony Arts
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
Search for other works by this author on:
Ignacio Mayo
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
e-mail: ignacio.mayo.yague@vki.ac.be
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
e-mail: ignacio.mayo.yague@vki.ac.be
Gian Luca Gori
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
Aude Lahalle
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
Tony Arts
Turbomachinery and Propulsion Department,
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
von Karman Institute for Fluid Mechanics,
Rhode-Saint-Genèse B-1640, Belgium
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received February 5, 2016; final manuscript received February 26, 2016; published online April 26, 2016. Editor: Kenneth C. Hall.
J. Turbomach. Oct 2016, 138(10): 101008 (9 pages)
Published Online: April 26, 2016
Article history
Received:
February 5, 2016
Revised:
February 26, 2016
Connected Content
A companion article has been published:
Aerothermal Characterization of a Rotating Ribbed Channel at Engine Representative Conditions—Part II: Detailed Liquid Crystal Thermography Measurements
Citation
Mayo, I., Luca Gori, G., Lahalle, A., and Arts, T. (April 26, 2016). "Aerothermal Characterization of a Rotating Ribbed Channel at Engine Representative Conditions—Part I: High-Resolution Particle Image Velocimetry Measurements." ASME. J. Turbomach. October 2016; 138(10): 101008. https://doi.org/10.1115/1.4032926
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