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.

Issue Section:
Research Papers
Keywords:
Boundary layer development, Computational fluid dynamics, Fan, Compressor stall, Surge, Turbine aerodynamic design, Compressor , Operability
Topics:
Blades, Boundary layers, Compressors, Ejectors, Flow (Dynamics), Pressure, Resolution (Optics), Rotors, Vortices, Shock (Mechanics), Reynolds-averaged Navier–Stokes equations, Physics, Computational fluid dynamics, Stators, Mach number

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