Low Reynolds Number Effects in Compressor Blade Design
Author:
Affiliation:
1. German Aerospace Center (DLR) Institute of Propulsion Technology
Publisher
Gas Turbine Society of Japan
Link
https://www.jstage.jst.go.jp/article/jgpp/15/4/15_vol15no4tp08/_pdf
Reference16 articles.
1. R. A. BERDANIER AND N. L. KEY, The Effects of Tip Leakage Flow on the Performance of Multistage Compressors Used in Small Core Engine Applications, ASME Journal of Engineering for Gas Turbines and Power, 138(5) (2016).
2. A. HERGT, W. HAGE, S. GRUND, W. STEINERT, M. TERHORST, F. SCHONGEN, AND Y. WILKE, Riblet application in compressors: Toward efficient blade design, ASME Journal of Turbomachinery, 137 (2015), p. 111006.
3. A. HERGT, J. KLINNER, S. GRUND, C. WILLERT, W. STEINERT, AND M. BEVERSDORFF, On the Importance of Transition Control at Transonic Compressor Blades, ASME Journal of Turbomachinery, 143 (2021), p. 031007.
4. A. HERGT, B. KLOSE, J. KLINNER, M. BERGMANN, E. J. M. LOPEZ, S. GRUND, AND C. MORSBACH, On the Shock Boundary Layer Interaction in Transonic Compressor Blading, in ASME Turbo Expo, GT-2023-103218, June 26-30, Boston, MA, USA, 2023.
5. A. HERGT, W. STEINERT, AND S. GRUND, Design and Experimental Investigation of a Compressor Cascade for Low Reynolds Number Conditions, no. ISABE-2013-1104 in 21st ISABE Conference, Busan, Korea, 9-13 September 2013.
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