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.
|Keywords:||Unsteady-flow, Tip clearance, Performance, Stability, Velocity, Passage, Stall.|
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|Publisher Web site:||http://www.aiaa.org/content.cfm?pageid=318|
|Record Created:||11 Mar 2009|
|Last Modified:||08 Apr 2009 16:21|
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