TY - GEN
T1 - High resolution RANS NLH study of stage 67 tip injection physics
AU - Grosvenor, Allan D.
AU - Rixon, Gregory S.
AU - Sailer, Logan M.
AU - Matheson, Michael A.
AU - Gutzwiller, David P.
AU - Demeulenaere, Alain
AU - Gontier, Mathieu
AU - Strazisar, Anthony J.
N1 - Publisher Copyright:
Copyright © 2014 by ASME.
PY - 2014
Y1 - 2014
N2 - Numerical prediction of the Stage 67 transonic fan stage employing wall jet tip injection fow 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 confguration experimentally tested at NASA's Glenn Research Center in 2004. Time varying predictions of the stage plus recirculation and injection fowpath were executed utilizing the Nonlinear Harmonic approach. Signifcantly 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 infuence of tip injection, resulting in experimentally and numerically demonstrated stall suppression.
AB - Numerical prediction of the Stage 67 transonic fan stage employing wall jet tip injection fow 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 confguration experimentally tested at NASA's Glenn Research Center in 2004. Time varying predictions of the stage plus recirculation and injection fowpath were executed utilizing the Nonlinear Harmonic approach. Signifcantly 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 infuence of tip injection, resulting in experimentally and numerically demonstrated stall suppression.
UR - http://www.scopus.com/inward/record.url?scp=84961361641&partnerID=8YFLogxK
U2 - 10.1115/GT2014-27219
DO - 10.1115/GT2014-27219
M3 - Conference contribution
AN - SCOPUS:84961361641
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014
Y2 - 16 June 2014 through 20 June 2014
ER -