TY - GEN
T1 - NUMERICAL INVESTIGATION OF THE INFLUENCE OF THE DEGREE OF REACTION IN AN AXIAL COMPRESSOR STAGE WITH TANDEM VANES
AU - Giannini, Samuele
AU - Luz, Guilherme M.
AU - von Jeinsen, Philipp
AU - Straccia, Mattia
AU - Gümmer, Volker
N1 - Publisher Copyright:
Copyright © 2023 by ASME.
PY - 2023
Y1 - 2023
N2 - Many investigations have defined Smith-type diagrams to guide the preliminary designs of conventional axial compressor stages on the choice of loading, flow coefficient, and degree of reaction. The recent development of unconventional axial compressor stages with tandem vanes has not been accompanied by similar works aimed at tailoring existing correlations to the new type of vanes. While it is clear that axial compressor stages with tandem vanes operate in higher working ranges than conventional stages, it is less clear how the choice of reaction affects the aerodynamic behavior of such setups. Recent works have shown that higher work coefficients would require higher degrees of reaction thanks to the centrifugal effects’ beneficial influence on the rotor’s boundary layer. However, the interaction of tandem vanes with such phenomena is still not fully understood. For this purpose, this paper numerically investigates a low-speed axial compressor stage developed at the Technical University of Munich with different degrees of reaction for increasing loading levels. The metal angles of the unshrouded rotor and the shrouded stator are modified to ensure that the other design parameters of the stage, namely the work and flow coefficients, are kept constant and that the influence of the degree of reaction is isolated. The investigation starts with Q2D simulations of the reference midspan aerofoils, and it is then extended to a 3D configuration by maintaining the radial distribution of the aerofoil parameters together with the lean and bow distributions of the reference 3D vanes. New correlations are presented, aiming to show how the performance of the stage in terms of efficiency, total pressure losses, and loading coefficients of the vanes are influenced by the different degrees of reaction investigated. This paper therefore provides insight into the preliminary choices of parameters for the design of axial compressor stages with tandem vanes.
AB - Many investigations have defined Smith-type diagrams to guide the preliminary designs of conventional axial compressor stages on the choice of loading, flow coefficient, and degree of reaction. The recent development of unconventional axial compressor stages with tandem vanes has not been accompanied by similar works aimed at tailoring existing correlations to the new type of vanes. While it is clear that axial compressor stages with tandem vanes operate in higher working ranges than conventional stages, it is less clear how the choice of reaction affects the aerodynamic behavior of such setups. Recent works have shown that higher work coefficients would require higher degrees of reaction thanks to the centrifugal effects’ beneficial influence on the rotor’s boundary layer. However, the interaction of tandem vanes with such phenomena is still not fully understood. For this purpose, this paper numerically investigates a low-speed axial compressor stage developed at the Technical University of Munich with different degrees of reaction for increasing loading levels. The metal angles of the unshrouded rotor and the shrouded stator are modified to ensure that the other design parameters of the stage, namely the work and flow coefficients, are kept constant and that the influence of the degree of reaction is isolated. The investigation starts with Q2D simulations of the reference midspan aerofoils, and it is then extended to a 3D configuration by maintaining the radial distribution of the aerofoil parameters together with the lean and bow distributions of the reference 3D vanes. New correlations are presented, aiming to show how the performance of the stage in terms of efficiency, total pressure losses, and loading coefficients of the vanes are influenced by the different degrees of reaction investigated. This paper therefore provides insight into the preliminary choices of parameters for the design of axial compressor stages with tandem vanes.
UR - http://www.scopus.com/inward/record.url?scp=85177213684&partnerID=8YFLogxK
U2 - 10.1115/GT2023-100986
DO - 10.1115/GT2023-100986
M3 - Conference contribution
AN - SCOPUS:85177213684
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 2023: Turbomachinery Technical Conference and Exposition, GT 2023
Y2 - 26 June 2023 through 30 June 2023
ER -