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TECHNICAL BRIEFS

Measurements in the Transition Region of a Turbine Blade Profile Under Compressible Conditions

[+] Author and Article Information
E. J. Walsh, M. R. Davies

Stokes Research Institute, Department of Mechanical & Aeronautical Engineering,  University of Limerick, Plassey Technological Park, Limerick, Ireland

J. Fluids Eng 127(2), 400-403 (Nov 22, 2004) (4 pages) doi:10.1115/1.1881699 History: Received March 25, 2004; Revised November 22, 2004

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Copyright © 2005 by American Society of Mechanical Engineers
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Figures

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Figure 1

The transonic blow-down wind tunnel facility utilized in this investigation

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Figure 2

Measured hot film signals and skew distribution showing the transition region along the suction surface of the linear transonic cascade with an inlet Rec and exit Mach numbers of 283k and 0.61, respectively

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Figure 3

Comparisons between measured and predicted Mach number

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Figure 4

Method to determine the intermittency from the hot film measurements. Raw voltage was captured from 55% suction surface length of the linear transonic cascade with an inlet Rec and exit Mach numbers of 283k and 0.61, respectively; fulltime trace shown in Fig. 2.

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Figure 5

Measured transition region parameters: (top) Reθ at transition onset, (middle) acceleration parameter at transition onset and (bottom) spot formation rate.

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