Part 1 of this paper describes the design and optimization of two high turning subsonic compressor cascades operating as an outlet guide vane (OGV) behind a single stage low pressure turbine at low Reynolds number condition (Re = 1.3×105). In the numerical optimization algorithm, the design point and off-design performance has been considered in an objective function to achieve a wide low loss incidence range. The objective of the present paper is to examine some of the characteristics describing the new airfoils as well as to prove the reliability of the design process and the applied flow solver. Some aerodynamic characteristics for the two new airfoils and a conventional controlled diffusion airfoil (CDA), have been extensively investigated in the cascade wind tunnel of DLR Cologne. For an inlet Mach number of 0.6 the effect of Reynolds number and incidence angle on each airfoil performance is discussed, based on experimental and numerical results. For an interpretation of the airfoil boundary layer behavior, results of some boundary layer calculations are compared to oil flow visualization pictures. The design goal of an increased low loss incidence range at low Reynolds number condition could be confirmed without having a negative effect on the high Reynolds number region.
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ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference
June 16–19, 2003
Atlanta, Georgia, USA
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-3689-4
PROCEEDINGS PAPER
Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition: Part 2 — Experimental and Numerical Analysis
Heinz-Adolf Schreiber,
Heinz-Adolf Schreiber
German Aerospace Center (DLR), Ko¨ln, Germany
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Wolfgang Steinert,
Wolfgang Steinert
German Aerospace Center (DLR), Ko¨ln, Germany
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Toyotaka Sonoda,
Toyotaka Sonoda
Honda R&D Company, Saitama, Japan
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Toshiyuki Arima
Toshiyuki Arima
Honda R&D Company, Saitama, Japan
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Heinz-Adolf Schreiber
German Aerospace Center (DLR), Ko¨ln, Germany
Wolfgang Steinert
German Aerospace Center (DLR), Ko¨ln, Germany
Toyotaka Sonoda
Honda R&D Company, Saitama, Japan
Toshiyuki Arima
Honda R&D Company, Saitama, Japan
Paper No:
GT2003-38477, pp. 451-463; 13 pages
Published Online:
February 4, 2009
Citation
Schreiber, H, Steinert, W, Sonoda, T, & Arima, T. "Advanced High Turning Compressor Airfoils for Low Reynolds Number Condition: Part 2 — Experimental and Numerical Analysis." Proceedings of the ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference. Volume 6: Turbo Expo 2003, Parts A and B. Atlanta, Georgia, USA. June 16–19, 2003. pp. 451-463. ASME. https://doi.org/10.1115/GT2003-38477
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