An experimental investigation of the endwall flows in two high-turning turbine cascades was presented by Taremi et al. (2010, “Measurements of Endwall Flows in Transonic Linear Turbine Cascades: Part II—High Flow Turning,” ASME Conf. Proc., GT2010-22760, pp. 1343–1356). Endwall contouring was subsequently implemented in these cascades to control the secondary flows and reduce the total pressure losses. The current paper presents experimental results from these cascades to assess the effectiveness of endwall contouring in the transonic flow regime. The results include blade loadings, total pressure losses, streamwise vorticity and secondary kinetic energy distributions. In addition, surface flow visualization results are presented in order to interpret the endwall limiting streamlines within the blade passages. The flat-endwall and contoured-endwall cascades produce very similar midspan loading distributions and profile losses, but exhibit different secondary flows. The endwall surface flow visualization results indicate weaker interaction between the secondary flows and the blade suction surface boundary layers in the contoured cascades. Overall, the implementation of endwall contouring results in smaller and less intense vortical structures, and the reduction of the associated secondary kinetic energy (SKE) and exit flow angle variations. However, the mass-averaged losses at the main measurement plane, located 40% axial chord lengths downstream of the cascade (1.4CX), do not corroborate the numerically predicted improvements for the contoured cascades. This is in part attributed to slower mixing rates of the secondary flows in the compressible flow regime. The mass-averaged results at 2.0CX, on the other hand, show smaller losses for the contoured configurations associated with smaller SKE dissipation downstream of the cascades. Accordingly, the mixed-out row losses also show improvements for the contoured cascades.
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January 2013
Research-Article
Application of Endwall Contouring to Transonic Turbine Cascades: Experimental Measurements at Design Conditions
Farzad Taremi,
Farzad Taremi
1
e-mail: ftaremi@connect.carleton.ca
1Corresponding author.
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Steen A. Sjolander,
Steen A. Sjolander
Department of Mechanical and Aerospace Engineering,
Carleton University
,Ottawa, ON, K1S 5B6
, Canada
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Thomas J. Praisner
Thomas J. Praisner
Turbine Aerodynamics,
e-mail: thomas.praisner@pw.utc.com
United Technologies, Pratt and Whitney
,East Hartford, CT 06118
e-mail: thomas.praisner@pw.utc.com
Search for other works by this author on:
Farzad Taremi
e-mail: ftaremi@connect.carleton.ca
Steen A. Sjolander
Department of Mechanical and Aerospace Engineering,
Carleton University
,Ottawa, ON, K1S 5B6
, Canada
Thomas J. Praisner
Turbine Aerodynamics,
e-mail: thomas.praisner@pw.utc.com
United Technologies, Pratt and Whitney
,East Hartford, CT 06118
e-mail: thomas.praisner@pw.utc.com
1Corresponding author.
Contributed by International Gas Turbine Institute of ASME for Publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 9, 2011; final manuscript received September 26, 2011; published online October 30, 2012. Editor: David Wisler.
J. Turbomach. Jan 2013, 135(1): 011031 (12 pages)
Published Online: October 30, 2012
Article history
Received:
August 9, 2011
Revision Received:
October 4, 2011
Citation
Taremi, F., Sjolander, S. A., and Praisner, T. J. (October 30, 2012). "Application of Endwall Contouring to Transonic Turbine Cascades: Experimental Measurements at Design Conditions." ASME. J. Turbomach. January 2013; 135(1): 011031. https://doi.org/10.1115/1.4006565
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