We use cookies to ensure that we give you the best experience on our website. By continuing to browse this repository, you give consent for essential cookies to be used. You can read more about our Privacy and Cookie Policy.

Durham Research Online
You are in:

Experimental study on linear compressor cascade with three-dimensional blade oscillation.

Yang, H. and He, L. (2004) 'Experimental study on linear compressor cascade with three-dimensional blade oscillation.', Journal of propulsion and power., 20 (1). pp. 180-188.


An experiment is carried out to enhance the understanding of three-dimensional blade aeroelastic mechanisms and to produce test data for validation of numerical methods. A compressor cascade test rig developed consists of seven prismatic controlled diffusion blades with the middle blade being oscillated in a three-dimensional bending/flapping mode. Steady and unsteady pressure measurements are performed at six spanwise sections for three reduced frequencies and two tip-clearance gaps. Off-board pressure transducers are utilized with a transfer-function method correcting tubing errors. The tuned cascade results are constructed by using the influence coefficient method. The results illustrate fully three-dimensional unsteady behaviour. The blades are aeroelastically destabilized as the tip gap is increased, and the destabilizing effect of the tip-clearance influences most of the span. The total aerodynamic damping at the least stable interblade phase angle is reduced by 27% when the tip gap is increased from nearly 0 to 2% span.

Item Type:Article
Keywords:Unsteady-flow, Tip clearance, Performance, Stability, Velocity, Passage, Stall.
Full text:Full text not available from this repository.
Publisher Web site:
Record Created:11 Mar 2009
Last Modified:08 Apr 2009 16:21

Social bookmarking: del.icio.usConnoteaBibSonomyCiteULikeFacebookTwitterExport: EndNote, Zotero | BibTex
Look up in GoogleScholar | Find in a UK Library