Modern methods for axial compressor design are capable of shaping the blade surfaces in a three-dimensional way. Linking these methods with automated optimization techniques provides a major benefit to the design process. The application of nonaxisymmetric contoured endwalls is considered to be very successful in turbine rotors and vanes. Concerning axial compressors, nonaxisymmetric endwalls are still a field of research. This two-part paper presents the recent development of a novel endwall design. A vortex created by a nonaxisymmetric endwall groove acts as an aerodynamic separator, preventing the passage vortex from interacting with the suction side boundary layer. This major impact on the secondary flow results in a significant loss reduction by means of load redistribution, reduction in recirculation areas, and suppressed corner separation. Part I of this paper deals with the endwall design and its compressor application. The resulting flow phenomena and physics are described and analyzed in detail. The second paper presents the detailed experimental and numerical investigation of the developed endwall groove. The measurements carried out at the transonic cascade wind tunnel of DLR in Cologne, demonstrated a considerable influence on the cascade performance. A loss reduction and redistribution of the cascade loading were achieved at the aerodynamic design point, as well as near the stall condition of the cascade. This behavior is well predicted by the numerical simulation. The combined analysis of experimental and numerical flow patterns allows a detailed interpretation and description of the resulting flow phenomena. In this context, high fidelity 3D-Reynolds-averaged Navier–Stokes flow simulations are required to analyze the complex blade and endwall boundary layer interaction.
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e-mail: alexander.hergt@dlr.de
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April 2011
Research Papers
Advanced Nonaxisymmetric Endwall Contouring for Axial Compressors by Generating an Aerodynamic Separator—Part II: Experimental and Numerical Cascade Investigation
Alexander Hergt,
e-mail: alexander.hergt@dlr.de
Alexander Hergt
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
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Christian Dorfner,
Christian Dorfner
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
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Wolfgang Steinert,
Wolfgang Steinert
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
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Eberhard Nicke,
Eberhard Nicke
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
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Heinz-Adolf Schreiber
Heinz-Adolf Schreiber
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
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Alexander Hergt
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germanye-mail: alexander.hergt@dlr.de
Christian Dorfner
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
Wolfgang Steinert
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
Eberhard Nicke
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, Germany
Heinz-Adolf Schreiber
German Aerospace Center (DLR)
, Institute of Propulsion Technology, 51147 Cologne, GermanyJ. Turbomach. Apr 2011, 133(2): 021027 (8 pages)
Published Online: October 27, 2010
Article history
Received:
August 5, 2009
Revised:
September 3, 2009
Online:
October 27, 2010
Published:
October 27, 2010
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Citation
Hergt, A., Dorfner, C., Steinert, W., Nicke, E., and Schreiber, H. (October 27, 2010). "Advanced Nonaxisymmetric Endwall Contouring for Axial Compressors by Generating an Aerodynamic Separator—Part II: Experimental and Numerical Cascade Investigation." ASME. J. Turbomach. April 2011; 133(2): 021027. https://doi.org/10.1115/1.4001224
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