TY - GEN
T1 - ENDWALL BOUNDARY LAYER DEVELOPMENT in A MULTISTAGE LOW-SPEED COMPRESSOR with TANDEM STATOR VANES
AU - Hopfinger, Michael
AU - Gümmer, Volker
N1 - Publisher Copyright:
© 2021 by ASME.
PY - 2021
Y1 - 2021
N2 - The development of viscous endwall flow is of major importance when considering highly-loaded compressor stages. Essentially, all losses occurring in a subsonic compressor are caused by viscous shear stresses building up boundary layers on individual aerofoils and endwall surfaces. These boundary layers cause significant aerodynamic blockage and cause a reduction in effective flow area, depending on the specifics of the stage design. The presented work describes the numerical investigation of blockage development in a 3.5-stage low-speed compressor with tandem stator vanes. The research is aimed at understanding the mechanism of blockage generation and growth in tandem vane rows and across the entire compressor. Therefore, the blockage generation is investigated as a function of the operating point, the rotational speed and the inlet boundary layer thickness.
AB - The development of viscous endwall flow is of major importance when considering highly-loaded compressor stages. Essentially, all losses occurring in a subsonic compressor are caused by viscous shear stresses building up boundary layers on individual aerofoils and endwall surfaces. These boundary layers cause significant aerodynamic blockage and cause a reduction in effective flow area, depending on the specifics of the stage design. The presented work describes the numerical investigation of blockage development in a 3.5-stage low-speed compressor with tandem stator vanes. The research is aimed at understanding the mechanism of blockage generation and growth in tandem vane rows and across the entire compressor. Therefore, the blockage generation is investigated as a function of the operating point, the rotational speed and the inlet boundary layer thickness.
UR - http://www.scopus.com/inward/record.url?scp=85115445079&partnerID=8YFLogxK
U2 - 10.1115/GT2021-58742
DO - 10.1115/GT2021-58742
M3 - Conference contribution
AN - SCOPUS:85115445079
T3 - Proceedings of the ASME Turbo Expo
BT - Turbomachinery - Axial Flow Fan and Compressor Aerodynamics
PB - American Society of Mechanical Engineers (ASME)
T2 - ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition, GT 2021
Y2 - 7 June 2021 through 11 June 2021
ER -