Direct Numerical Simulations of Wake-Perturbed Separated Boundary Layers

A wake-perturbed flat plate boundary layer with a streamwise pressure distribution similar to those encountered on the suction side of typical low-pressure turbine blades is investigated by direct numerical simulation. The laminar boundary layer separates due to a strong adverse pressure gradient in...

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Veröffentlicht in:	Journal of turbomachinery 2012-11, Vol.134 (6)
Hauptverfasser:	Gungor, Ayse G., Simens, Mark P., Jiménez, Javier
Format:	Artikel
Sprache:	eng
Schlagworte:	Applied sciences Continuous cycle engines: steam and gas turbines, jet engines Drops and bubbles Engines and turbines Exact sciences and technology Fluid dynamics Fundamental areas of phenomenology (including applications) Mechanical engineering. Machine design Nonhomogeneous flows Physics
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Zusammenfassung:	A wake-perturbed flat plate boundary layer with a streamwise pressure distribution similar to those encountered on the suction side of typical low-pressure turbine blades is investigated by direct numerical simulation. The laminar boundary layer separates due to a strong adverse pressure gradient induced by suction along the upper simulation boundary, transitions, and reattaches while still subject to the adverse pressure gradient. Various simulations are performed with different wake passing frequencies, corresponding to the Strouhal number 0.0043< fθb/ΔU
ISSN:	0889-504X 1528-8900
DOI:	10.1115/1.4004882