Please use this identifier to cite or link to this item: http://buratest.brunel.ac.uk/handle/2438/8353
Title: Direct numerical simulations of transition in a compressor cascade: The influence of free-stream turbulence
Authors: Zaki, TA
Wissink, JG
Rodi, W
Durbin, PA
Keywords: Boundary layers;Bypass transition;Compressor cascade;Pressure gradient
Issue Date: 2010
Publisher: Cambridge University Press
Citation: Journal of Fluid Mechanics, 665, 57 - 98, 2010
Abstract: The flow through a compressor passage without and with incoming free-stream grid turbulence is simulated. At moderate Reynolds number, laminar-to-turbulence transition can take place on both sides of the aerofoil, but proceeds in distinctly different manners. The direct numerical simulations (DNS) of this flow reveal the mechanics of breakdown to turbulence on both surfaces of the blade. The pressure surface boundary layer undergoes laminar separation in the absence of free-stream disturbances. When exposed to free-stream forcing, the boundary layer remains attached due to transition to turbulence upstream of the laminar separation point. Three types of breakdowns are observed; they combine characteristics of natural and bypass transition. In particular, instability waves, which trace back to discrete modes of the base flow, can be observed, but their development is not independent of the Klebanoff distortions that are caused by free-stream turbulent forcing. At a higher turbulence intensity, the transition mechanism shifts to a purely bypass scenario. Unlike the pressure side, the suction surface boundary layer separates independent of the free-stream condition, be it laminar or a moderate free-stream turbulence of intensity Tu ~ 3%. Upstream of the separation, the amplification of the Klebanoff distortions is suppressed in the favourable pressure gradient (FPG) region. This suppression is in agreement with simulations of constant pressure gradient boundary layers. FPG is normally stabilizing with respect to bypass transition to turbulence, but is, thereby, unfavourable with respect to separation. Downstream of the FPG section, a strong adverse pressure gradient (APG) on the suction surface of the blade causes the laminar boundary layer to separate. The separation surface is modulated in the instantaneous fields of the Klebanoff distortion inside the shear layer, which consists of forward and backward jet-like perturbations. Separation is followed by breakdown to turbulence and reattachment. As the free-stream turbulence intensity is increased, Tu ~ 6.5%, transitional turbulent patches are initiated, and interact with the downstream separated flow, causing local attachment. The calming effect, or delayed re-establishment of the boundary layer separation, is observed in the wake of the turbulent events.
Description: Copyright © Cambridge University Press 2010.
URI: http://journals.cambridge.org/action/displayAbstract?fromPage=online&aid=7930514
http://bura.brunel.ac.uk/handle/2438/8353
DOI: http://dx.doi.org/10.1017/S0022112010003873
ISSN: 0022-1120
Appears in Collections:Publications
Mechanical and Aerospace Engineering
Dept of Mechanical Aerospace and Civil Engineering Research Papers

Files in This Item:
File Description SizeFormat 
Fulltext.pdf7.89 MBAdobe PDFView/Open


Items in BURA are protected by copyright, with all rights reserved, unless otherwise indicated.