TY - GEN
T1 - Parametric study on a casing treatment of a transonic high-pressure compressor rotor
AU - Clemen, C.
AU - Gümmer, V.
AU - Müller, M. W.
N1 - Publisher Copyright:
Copyright © 2009 Local Organising Committee.
PY - 2009
Y1 - 2009
N2 - The design of compressors for aero engines is aiming for maximum efficiency at minimum weight and cost. This can be achieved for example by a reduction of the stage count. That causes increased stage pressure ratio and loading. To guarantee a stable operation of the compressor, the rotor tip leakage flow at the casing, which has a major influence on compressor stability, has to be influenced such, that the compressor surge margin is sufficient at all engine operating conditions. The leakage flow is dominated by the tip leakage vortex, which generates losses and passage blockage in the end wall region. Its trajectory gets steeper when the compressor is throttled towards stall. At a certain point the vortex can spill into the next blade passage or break down and cause rotor stall and compressor surge. To delay or eliminate this mechanism so-called casing treatments positioned in the rotor casing over the blade tip can be used. In the present paper a parametric study on an existing casing treatment (axial slots) applied to the transonic TU Darmstadt Rotor-1 high-pressure compressor stage is presented. The study was carried out using steady and unsteady 3D-CFD and has been validated with test data of different configurations. The aim of the study was to investigate the influence of different geometry parameters of the casing treatment on its effectiveness. Especially the dependence of geometry, surge margin and efficiency was of primary interest, aiming to find the optimum configuration. As a baseline the rotor has been analysed without casing treatment and with an existing casing treatment using unsteady CFD and comparing with test data to validate the CFD model. Different geometry parameters of the casing treatment (number and position) were varied and the effect on flow field, surge margin and efficiency were investigated, evaluating the interaction between casing treatment and main flow as well as the effectiveness of each configuration.
AB - The design of compressors for aero engines is aiming for maximum efficiency at minimum weight and cost. This can be achieved for example by a reduction of the stage count. That causes increased stage pressure ratio and loading. To guarantee a stable operation of the compressor, the rotor tip leakage flow at the casing, which has a major influence on compressor stability, has to be influenced such, that the compressor surge margin is sufficient at all engine operating conditions. The leakage flow is dominated by the tip leakage vortex, which generates losses and passage blockage in the end wall region. Its trajectory gets steeper when the compressor is throttled towards stall. At a certain point the vortex can spill into the next blade passage or break down and cause rotor stall and compressor surge. To delay or eliminate this mechanism so-called casing treatments positioned in the rotor casing over the blade tip can be used. In the present paper a parametric study on an existing casing treatment (axial slots) applied to the transonic TU Darmstadt Rotor-1 high-pressure compressor stage is presented. The study was carried out using steady and unsteady 3D-CFD and has been validated with test data of different configurations. The aim of the study was to investigate the influence of different geometry parameters of the casing treatment on its effectiveness. Especially the dependence of geometry, surge margin and efficiency was of primary interest, aiming to find the optimum configuration. As a baseline the rotor has been analysed without casing treatment and with an existing casing treatment using unsteady CFD and comparing with test data to validate the CFD model. Different geometry parameters of the casing treatment (number and position) were varied and the effect on flow field, surge margin and efficiency were investigated, evaluating the interaction between casing treatment and main flow as well as the effectiveness of each configuration.
UR - http://www.scopus.com/inward/record.url?scp=84924971790&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:84924971790
T3 - 8th European Conference on Turbomachinery: Fluid Dynamics and Thermodynamics, ETC 2009 - Conference Proceedings
SP - 329
EP - 339
BT - 8th European Conference on Turbomachinery
A2 - Heitmeir, F.
A2 - Martelli, F.
A2 - Manna, M.
PB - Verlag der Technischen Universitat Graz
T2 - 8th European Conference on Turbomachinery: Fluid Dynamics and Thermodynamics, ETC 2009
Y2 - 23 March 2009 through 27 March 2009
ER -