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 (RANS) computations were used to perform detailed analysis of the Stage 67 configuration experimentally tested at NASA's Glenn Research Center in 2004. Time varying predictions of the stage plus recirculation and injection flowpath were executed utilizing the nonlinear harmonic (NLH) 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 influence of tip injection, resulting in experimentally and numerically demonstrated stall suppression.
High Resolution RANS Nonlinear Harmonic Study of Stage 67 Tip Injection Physics
Contributed by the International Gas Turbine Institute (IGTI) Division of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 29, 2014; final manuscript received August 17, 2014; published online November 18, 2014. Editor: Ronald Bunker.
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Grosvenor, A. D., Rixon, G. S., Sailer, L. M., Matheson, M. A., Gutzwiller, D. P., Demeulenaere, A., Gontier, M., and Strazisar, A. J. (May 1, 2015). "High Resolution RANS Nonlinear Harmonic Study of Stage 67 Tip Injection Physics." ASME. J. Turbomach. May 2015; 137(5): 051005. https://doi.org/10.1115/1.4028550
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