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Title: High Resolution RANS NLH Study of Stage 67 Tip Injection Physics

Numerical prediction of the Stage 67 transonic fan stage employing wall jet tip injection flow control and study of the physical mechanisms leading to stall suppression and stability enhancement afforded by endwall recirculation/injection is the focus of this paper. Reynolds averaged Navier-Stokes computations were used to perform detailed analysis of the Stage 67 configuration experimentally tested at NASA s Glenn Research Center in 2004. Time varying prediction of the stage plus recirculation and injection flowpath were performed utilizing the Nonlinear Harmonic approach. Significantly higher grid resolution per passage was achieved than what has been generally employed in prior reported numerical studies of spike stall phenomena in transonic compressors. This paper focuses on characterizing the physics of spike stall embryonic stage phenomena and the impact of tip injection, resulting in experimentally and numerically demonstrated stall suppression
  1. ORNL
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Conference: Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, D sseldorf, Germany, 20140616, 20140620
Research Org:
Oak Ridge National Lab. (ORNL), Oak Ridge, TN (United States). Oak Ridge Leadership Computing Facility (OLCF)
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Country of Publication:
United States
High Resolution RANS NLH Study of Stage 67 Tip Injection Physics