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Large tip clearance flows in two compressor cascades

Williams, R; Ingram, G; Gregory-Smith, D


R Williams

D Gregory-Smith


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.


Williams, R., Ingram, G., & 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 (391-402).

Conference Name ASME Turbo Expo 2010: Power for Land, Sea and Air GT2010.
Conference Location Glasgow, UK (Scottish Exhibition & Conference Centre)
Publication Date Jun 1, 2010
Deposit Date Sep 6, 2010
Publisher American Society of Mechanical Engineers
Volume 7
Pages 391-402
Book Title ASME Turbo Expo 2010 : Power for land, sea and air, 14-18 June 2010, Glasgow ; proceedings.
Keywords Flow (Dynamics), Compressors , Clearances (Engineering).
Additional Information Conference dates: June 14-18, 2010.