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Extra info for Advanced Gas Turbine Systems Research [qtly prog rpt]
5% at flow rates of interest. cf Measurement: A number of researchers ha ve struggled with the complexities of making drag measurements over rough surfaces. Two common methods relying solely on velocity measurements are a boundary layer momentum balance and log-region curve fitting. For a zero streamwise pressure gradient flow, the change in boundary layer momentum thickness (θ) can be related directly to cf by cf = 2dθ/dx. This is the momentum balance method. It requires a minimum of two velocity profiles separated by a streamwise distance (dx) over the rough surface.
Since operational data was not supplied by the manufacturers, estimates of these parameters were made as follows. For all cases, the blade Reynolds number, Re c, was approximated at 2x106 . This is in the range of values cons idered typical for high pressure turbine vanes/blades as reported by other researchers [4,13]. 097δ from a power- law boundary layer profile]. Admittedly, this estimate is an oversimplification. Turbine blade boundary layers are not turbulent from the leading edge and they are subject to pressure gradients, transonic Mach numbers, freestream turbulence, and (of course) roughness.
K. Hodge. An Instructional Computer Program for Computing the Steady, Compressible Turbulent Flow of an Arbitrary Fluid Near a Smooth Wall. Department of Mechanical Engineering, Mississippi State University, Second printing, 1990. Hodge, B. , J. Bons, R. Sondergaard, and R. Rivir. ” Janna, W. S. Introduction to Fluid Mechanics. Boston: PWS Kent. Second edition. 1994. Lindsey, W. F. ” NACA TR 619, 1938. -31- Morris, H. M. Applied Hydraulics in Engineering. New York: The Ronald Press Company. Second edition.
Advanced Gas Turbine Systems Research [qtly prog rpt]