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

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Porter, JS and Sargison, JE and Walker, GJ and Henderson, AD (2008) A comparative investigation of round and fan-shaped cooling hole near flow fields. Journal of Turbomachinery, 130 (4). pp. 1-8. ISSN 0889-504X

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Abstract

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 points to reasons for improvements in cooling performance noted by previous studies. Two different computational fluid dynamics 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: Article
Keywords: Round Fan Cooling Hole Flow Field
Journal or Publication Title: Journal of Turbomachinery
Page Range: pp. 1-8
ISSN: 0889-504X
Identification Number - DOI: 10.1115/1.2812952
Additional Information: ©2008 American Society of Mechanical Engineers
Date Deposited: 06 Jan 2009 02:33
Last Modified: 18 Nov 2014 03:54
URI: http://eprints.utas.edu.au/id/eprint/8178
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