This paper considers the effect of small variations in leading edge geometry, leading edge roughness, leading edge fillet, and blade fillet geometry on the three-dimensional separations found in compressor blade rows. The detrimental effects of these separations have historically been predicted by correlations based on global flow parameters, such as blade loading, inlet boundary layer skew, etc., and thus ignoring small deviations such as those highlighted above. In this paper it is shown that this may not be the case and that certain, engine representative geometry deviations can have an effect equivalent to an increase in blade loading of 10%. Experiments were performed at the stator hub of a low-speed, single-stage compressor. The results show that any deviation which causes suction surface transition to move to the leading edge over the first 30% of span will cause a large growth in the size of the hub separation, doubling its impact on loss. The geometry deviations that caused this, and are thus of greatest concern to a designer, are changes in leading edge quality and roughness around the leading edge, which are characteristic of an eroded blade.
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March 2012
Research Papers
The Impact of Real Geometries on Three-Dimensional Separations in Compressors
Robert J. Miller
Robert J. Miller
Whittle Laboratory,
University of Cambridge
, Cambridge CB3 0DY, UK
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Martin N. Goodhand
Robert J. Miller
Whittle Laboratory,
University of Cambridge
, Cambridge CB3 0DY, UKJ. Turbomach. Mar 2012, 134(2): 021007 (8 pages)
Published Online: June 22, 2011
Article history
Received:
June 28, 2010
Revised:
July 12, 2010
Online:
June 22, 2011
Published:
June 22, 2011
Citation
Goodhand, M. N., and Miller, R. J. (June 22, 2011). "The Impact of Real Geometries on Three-Dimensional Separations in Compressors." ASME. J. Turbomach. March 2012; 134(2): 021007. https://doi.org/10.1115/1.4002990
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