Shock Dynamics and Associated Flow Physics at Near Stall Condition in a Transonic Axial Flow Compressor Stage
Author:
Affiliation:
1. Propulsion Division, National Aerospace Laboratories, Bangalore, India
2. Indian Institute of Technology, Bombay, Powai, Mumbai, India
Publisher
Gas Turbine Society of Japan
Link
https://www.jstage.jst.go.jp/article/jgpp/15/4/15_vol15no4tp05/_pdf
Reference18 articles.
1. Roberto Biollo and Ernesto Benini, 2011, " State-of-Art of Transonic Axial Compressors," Advances in Gas Turbine Technology, Chapter 2, DOI:10.5772/25257.
2. Jüngst, Maximilian, 2019, " The transonic compressor with non-uniform tip clearance: Effects on aerodynamics and aeroelasticity," Ph.D. Thesis,, Darmstadt, Technische Universität.
3. S. L. Puterbaugh and M. Brendel,1997, " Tip Clearance Flow-Shock Interaction in a Transonic Compressor Rotor," AIAA, Journal of Propulsion and Power, Vol. 13, pp. 24-30, DOI:10.2514/2.5146.
4. M. T. Schobeiri, 1998, " Shock-Loss Model for Transonic and Supersonic Axial Compressors with Curved Blades," AIAA, Journal of Propulsion and Power, Vol. 14, pp.470-478, DOI:10.2514/2.5324.
5. Hanru Liu, Yangang Wang, Songchuan Xian and Jun Zhang, 2017, " Numerical investigation on the shock-wave and flow structures in a transonic contra-rotating axial compressor," Advances in Mechanical Engineering, Vol. 9, No. 3, DOI:10.1177/1687814017697895.
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