Williams, Richard and Gregory-Smith, David and Ingram, Grant (2009) 'Large tip clearances and highly skewed inlet conditions.', in 8th European Conference on Turbomachinery : fluid dynamics and thermodynamics (EUROTURBO 8), 23-27 March 2009, Graz, Austria ; proceedings. Graz, Austria: Verlag der TU Graz, pp. 355-366.
Multi stage and end-wall effects result in a highly skewed inlet boundary layer to high pressure axial compressor rotor rows, this paper investigates the influence of these skewed boundary layers on tip clearance flows. The particular focus is on compressor stages where the tip clearance values are relatively large and the tip clearance flow accounts for a large proportion of the row loss. Experimental measurements have been undertaken upon a linear cascade of a typical high pressure compressor geometry with upstream tangential injection implemented to create a realistic inlet boundary layer skew. Results are presented for two inlet boundary conditions: large skew (realistic inlet conditions) and low skew (less realistic inlet conditions) with tip clearances from 0 to 12%. This paper reports that although the loss is reduced with increased tip clearance a penalty is paid in terms of reduced flow turning, for example a tip clearance of 12% of span halves the turning through the cascade. This paper shows that the results are consistent whether or not inlet skew is applied.
|Item Type:||Book chapter|
|Additional Information:||Conference programme: http://ttm.tugraz.at/pdfs/ETC_09_Final_Program.pdf|
|Full text:||Full text not available from this repository.|
|Publisher Web site:||http://www.ub.tugraz.at/Verlag/|
|Record Created:||25 Oct 2011 15:05|
|Last Modified:||26 Oct 2011 10:06|
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