Surface Shear Stress and Pressure Measurements in a Turbine Cascade

To further the understanding of secondary flow loss, a set of surface measurements is presented for a planar turbine cascade tested at low Mach number (maximum of 0.23) and at an inlet axial chord Reynolds number of 5.9×105. The endwall and airfoil surface measurements are of skin friction, limiting...

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Veröffentlicht in:	Journal of turbomachinery 2009-07, Vol.131 (3), p.8-8
Hauptverfasser:	Holley, Brian M, Langston, Lee S
Format:	Artikel
Sprache:	eng
Schlagworte:	Applied sciences Engines and turbines Exact sciences and technology Mechanical engineering. Machine design
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description	To further the understanding of secondary flow loss, a set of surface measurements is presented for a planar turbine cascade tested at low Mach number (maximum of 0.23) and at an inlet axial chord Reynolds number of 5.9×105. The endwall and airfoil surface measurements are of skin friction, limiting streamline direction, and static pressure. An oil film interferometry measurement technique applied to the endwall and airfoil surfaces (at some 2000 locations) provides an extensive passage surface map of skin friction values and limiting streamline topology. Measurements of pressures on the same passage surfaces are also presented, resulting in a complete picture of endwall and airfoil surface pressure and shear.
doi_str_mv	10.1115/1.2988168
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source	ASME Transactions Journals (Current)
subjects	Applied sciences Engines and turbines Exact sciences and technology Mechanical engineering. Machine design
title	Surface Shear Stress and Pressure Measurements in a Turbine Cascade
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