Prediction of Compressible Flow Pressure Losses in 30–150 Deg Sharp-Cornered Bends

[+] Author and Article Information
Nia Haidar

Department of Mechanical & Manufacturing Engineering, University of Brighton, Cockcroft Building, Lewes Road, Brighton BN2 4GJ, England

J. Fluids Eng 117(4), 589-592 (Dec 01, 1995) (4 pages) doi:10.1115/1.2817306 History: Received May 13, 1994; Revised February 17, 1995; Online December 04, 2007


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.

Copyright © 1995 by The American Society of Mechanical Engineers
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