Williams, R. and Ingram, G. and Gregory-Smith, D. (2010) 'Large tip clearance flows in two compressor cascades.', in ASME Turbo Expo 2010 : Power for land, sea and air, 14-18 June 2010, Glasgow ; proceedings. New York: American Society of Mechanical Engineers, GT2010-22952.
Large tip clearances in the region of six percent span exist in the high pressure stages of compressors of industrial gas turbines. The over tip clearance ﬂow causes signiﬁcant block-age and accounts for the largest proportion of loss in the high pressure compressor. This paper examines large tip clearances in two different compressor cascades. The ﬁrst was a cascade of controlled-diffusion blades and the second cascade had geome¬try more representative of modern engine practise. The second cascade also featured realistic inlet boundary layer conditions delivered by an upstream injection system. Increasing the understanding of such ﬂows will allow for improvements in the design of such compressors. The key conclusions of this paper are: a) At large tip clearances the tip clearance is the primary variable inﬂuencing the ﬂow pattern, blade geometry is a secondary consideration; b) The blade geometry has a signiﬁcant inﬂuence on loss gener¬ation through the cascade; c) With increasing tip clearance the loss generation through the cascade can diminish but the ﬂow turning is much reduced; and d) The blade loading at the tip can increase at large tip clearances.
|Item Type:||Book chapter|
|Additional Information:||Volume 7: Turbomachinery, Parts A, B, and C.|
|Full text:||Full text not available from this repository.|
|Publisher Web site:||http://www.asmedl.org/dbt/dbt.jsp?KEY=ASMECP&Volume=2010&Issue=44021|
|Record Created:||21 Oct 2011 14:50|
|Last Modified:||26 Oct 2011 14:50|
|Social bookmarking:||Export: EndNote, Zotero | BibTex|
|Usage statistics||Look up in GoogleScholar | Find in a UK Library|