This paper considers the measurement and prediction of the additional total pressure losses of subsonic steady air flow in sharp-cornered bends, similar to those present in the secondary air cooling systems of gas turbine engines. The bends examined ranged between 30 to 150 in 30 deg increments and were circular in cross section. Experimental results covering a wide speed range up to choking are presented for five different bend geometries. An analytical flow model provided results in fairly good agreement with the measurements obtained and equally compared favourably with the experimental findings of other researchers at low Mach numbers. The highest attainable upstream Mach number (MU) of the average upstream flow was 0.57 for the 30 deg bend. The maximum possible values of MU represent a limiting condition dictated by downstream choking of the flow. The compressible flow coefficients, caused by the presence of the bends, can be expected to be between 10 to 20 percent higher than those for incompressible flow.
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December 1995
Research Papers
Prediction of Compressible Flow Pressure Losses in 30–150 Deg Sharp-Cornered Bends
Nia Haidar
Nia Haidar
Department of Mechanical & Manufacturing Engineering, University of Brighton, Cockcroft Building, Lewes Road, Brighton BN2 4GJ, England
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Nia Haidar
Department of Mechanical & Manufacturing Engineering, University of Brighton, Cockcroft Building, Lewes Road, Brighton BN2 4GJ, England
J. Fluids Eng. Dec 1995, 117(4): 589-592 (4 pages)
Published Online: December 1, 1995
Article history
Received:
May 13, 1994
Revised:
February 17, 1995
Online:
December 4, 2007
Citation
Haidar, N. (December 1, 1995). "Prediction of Compressible Flow Pressure Losses in 30–150 Deg Sharp-Cornered Bends." ASME. J. Fluids Eng. December 1995; 117(4): 589–592. https://doi.org/10.1115/1.2817306
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