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A comparative investigation of round and fan-shaped cooling hole near flow fields


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Porter, JS, Sargison, JE, Walker, GJ and Henderson, AD 2007 , 'A comparative investigation of round and fan-shaped cooling hole near flow fields', paper presented at the ASME Turbo Expo 2007: Power for Land, Sea and Air, 14-17 May, 2007, Montreal, Canada.

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This study presents velocity and turbulence data
measured experimentally in the near field of a round and a
laterally expanded fan-shaped cooling hole. Both holes are
fed by a plenum inlet, and interact with a turbulent
mainstream boundary layer. Flow is Reynolds number
matched to engine conditions to preserve flow structure, and
two coolant to mainstream blowing momentum ratios are
investigated experimentally. Results clearly identify regions
of high shear for the round hole as the jet penetrates into the
mainstream. In contrast, the distinct lack of high shear
regions for the fan shaped hole point to reasons for
improvements in cooling performance noted by previous
studies. Two different CFD codes are used to predict the flow
within and downstream of the fan shaped hole, with
validation from the experimental measurements. One code is
the commercially available ANSYS CFX 10.0, and the other
is the density-based solver with low Mach number preconditioning,
HYDRA, developed in-house by Rolls-Royce
plc for high speed turbomachinery flows. Good agreement
between numerical and experimental data for the center-line
traverses was obtained for a steady state solution, and a
region of reversed flow within the expansion region of the
fan-shaped hole was identified.

Item Type: Conference or Workshop Item (Paper)
Authors/Creators:Porter, JS and Sargison, JE and Walker, GJ and Henderson, AD
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