Shroud leakage flow undergoes little change in the tangential velocity as it passes over the shroud. Mixing due to the difference in tangential velocity between the main stream flow and the leakage flow creates a significant proportion of the total loss associated with shroud leakage flow. The unturned leakage flow also causes negative incidence and intensifies the secondary flows in the downstream blade row. This paper describes the experimental results of a concept to turn the rotor shroud leakage flow in the direction of the main blade passage flow in order to reduce the aerodynamic mixing losses. A three-stage air model turbine with low aspect ratio blading was used in this study. A series of different stationary turning vane geometries placed into the rotor shroud exit cavity downstream of each rotor blade row was tested. A significant improvement in flow angle and loss in the downstream stator blade rows was measured together with an increase in turbine brake efficiency of 0.4 %.
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April 2008
Research Papers
Control of Shroud Leakage Loss by Reducing Circumferential Mixing
John D. Denton
John D. Denton
Whittle Laboratory,
Cambridge University
, Cambridge, CB30DY, UK
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Budimir Rosic
John D. Denton
Whittle Laboratory,
Cambridge University
, Cambridge, CB30DY, UKJ. Turbomach. Apr 2008, 130(2): 021010 (7 pages)
Published Online: March 21, 2008
Article history
Revised:
July 14, 2006
Received:
July 14, 2006
Published:
March 21, 2008
Citation
Rosic, B., and Denton, J. D. (March 21, 2008). "Control of Shroud Leakage Loss by Reducing Circumferential Mixing." ASME. J. Turbomach. April 2008; 130(2): 021010. https://doi.org/10.1115/1.2750682
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