Nowadays, modern axial compressors have already reached a very high level of development. The current study is focused on the question, if the application of riblets on the surfaces of a highly efficient modern compressor blade can be a further step toward more efficient blade design. Therefore, a highly loaded compressor cascade has been designed and optimized specifically for low Reynolds number (LRN) conditions, as encountered at high altitudes and under consideration of the application of riblets. The optimization was performed at a Mach number of 0.6 and a Reynolds number of 1.5 × 105. Two objective functions were used. The aim of the first objective function was to minimize the cascade losses at the design point and at incidence angles of +5 and −5 deg. The intention of the second objective function was to achieve a smooth distribution of the skin friction coefficient on the suction side of the blade by influencing the blade curvature in order to apply riblets. The MISES flow solver as well as the DLR optimizer “AutoOpti” was used for the optimization process. The developed compressor cascade was investigated in the transonic cascade wind tunnel of DLR in Cologne, where the Reynolds number was varied in the range of 1.5 × 105–9.0 × 105. Furthermore, the measurements were carried out at a low turbulence level of 0.8% and at a high turbulence level of 4%, representative for high pressure compressor stages. The measurement program was divided into two parts. The first part consisted of the investigation of the reference cascade. In the second part of the study, riblets were applied on suction and pressure side of the cascade blades; two different manufacturing techniques, a rolling and a coating techniques, were applied. The rolling technique provides riblets with a width of 70 μm and the coated riblets (CRs) have a width of 50 μm. The wake measurements were performed using a three-hole probe at midspan of the cascade in order to determine the resulting losses of the reference blade and the blades with applied riblets. The detailed analysis of the measurements shows that the riblets have only a slight influence on the viscous losses in the case of the compressor application in this study. Finally, these results are discussed and assessed against the background of feasibility and effort of riblet applications within the industrial design and manufacturing process.
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November 2015
Research-Article
Riblet Application in Compressors: Toward Efficient Blade Design
Alexander Hergt,
Alexander Hergt
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
e-mail: alexander.hergt@dlr.de
Institute of Propulsion Technology,
Cologne 51147, Germany
e-mail: alexander.hergt@dlr.de
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W. Hage,
W. Hage
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
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S. Grund,
S. Grund
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
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W. Steinert,
W. Steinert
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
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M. Terhorst,
M. Terhorst
Laboratory for Machine Tools and
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
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F. Schongen,
F. Schongen
Laboratory for Machine Tools and
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
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Y. Wilke
Y. Wilke
Fraunhofer Institute for Manufacturing,
Technology and Advanced Materials IFAM,
Bremen 28359, Germany
Technology and Advanced Materials IFAM,
Bremen 28359, Germany
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Alexander Hergt
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
e-mail: alexander.hergt@dlr.de
Institute of Propulsion Technology,
Cologne 51147, Germany
e-mail: alexander.hergt@dlr.de
W. Hage
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
S. Grund
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
W. Steinert
German Aerospace Center (DLR),
Institute of Propulsion Technology,
Cologne 51147, Germany
Institute of Propulsion Technology,
Cologne 51147, Germany
M. Terhorst
Laboratory for Machine Tools and
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
F. Schongen
Laboratory for Machine Tools and
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
Production Engineering,
RWTH Aachen University,
Aachen 52074, Germany
Y. Wilke
Fraunhofer Institute for Manufacturing,
Technology and Advanced Materials IFAM,
Bremen 28359, Germany
Technology and Advanced Materials IFAM,
Bremen 28359, Germany
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received May 25, 2015; final manuscript received June 12, 2015; published online September 16, 2015. Assoc. Editor: Michael Hathaway.
J. Turbomach. Nov 2015, 137(11): 111006 (12 pages)
Published Online: September 16, 2015
Article history
Received:
May 25, 2015
Revision Received:
June 12, 2015
Citation
Hergt, A., Hage, W., Grund, S., Steinert, W., Terhorst, M., Schongen, F., and Wilke, Y. (September 16, 2015). "Riblet Application in Compressors: Toward Efficient Blade Design." ASME. J. Turbomach. November 2015; 137(11): 111006. https://doi.org/10.1115/1.4031090
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