During the last few decades extremely powerful Quasi-three-dimensional (3D) codes and fully 3D Navier-Stokes solvers have been developed and successfully utilized in the design process and optimization of multistage axial-flow compressors. However, most of these methods proved to be difficult in handling and extremely time consuming. Due to these disadvantages, the primary stage design and stage matching as well as the off-design analysis is nowadays still based on fast 2D methods incorporating loss-, deviation- and end wall modeling. Only the detailed 3D optimization is normally performed by means of advanced 3D methods. In this paper a fast and efficient 2D calculation method is presented, which already in the initial design phase of multistage axial flow compressors, considers the influence of hub leakage flows, tip clearance effects, and other end wall flow phenomena. The method is generally based on the fundamental approach by Howard and Gallimore (1992). In order to allow a more accurate prediction of skewed and nondeveloped boundary layers in turbomachines, an improved theoretical approach was implemented. Particularly the splitting of the boundary layers into an axial and tangential component proved to be necessary in order to account for the change between rotating and stationary end walls. Additionally, a new approach is used for the prediction of the viscous end wall zones including hub leakage effects and strongly skewed boundary layers. As a result, empirical correlations for secondary flow effects are no longer required. The results of the improved method are compared with conventional 2D results including 3D loss- and deviation-models, with experimental data of a three-stage research compressor of the Institute for Jet Propulsion and Turbomachinery of the Technical University of Aachen and with 3D Navier-Stokes solutions of the V84.3A compressor and of a multistage Siemens research compressor. The results obtained using the new method show a remarkable improvement in comparison with conventional 2D methods. Due to the high quality and the extremely short computation time, the new method allows an overall viscous design of multistage compressors for heavy duty gas turbines and aeroengine applications.

1.
Adkins, G. G., and Smith, L. H., “Spanwise Mixing in Axial-Flow Turbomachines,” ASME-Paper 81-GT-57.
2.
Gallimore
,
S. J.
,
1986
, “
Spanwise Mixing in Multistage Axial Flow Compressors: Part II—Throughflow Calculations Including Mixing
,”
ASME J. Turbomach.
,
108
, No.
1
, pp.
10
16
.
3.
Howard, M. A., and Gallimore S. J., 1992, “Viscous Throughflow Modelling for Multi-stage Compressor Design,” ASME-Paper 92-GT-302, Cologne, Germany.
4.
Edited by Johnsen, I. A., and Bullock, R. O., “Aerodynamic Design of Axial Flow Compressors”, NASA Report SP-36, 1965.
5.
Schlichting, H., 1997, “Grenzschicht-Theorie,” 9th Ed. Springer-Verlag.
6.
Hoynacki, A., 1999, “Einfluß von instationa¨rer Stro¨mung und Turbulenz auf die Grenzschichten und auf die Druckverteilungen von Beschaufelungen moderner mehrstufiger Axialverdichter,” Forschungsvereinigung Verbrennungskraftmaschinen (FVV) Abschlußbericht, Heft 679.
7.
Roberts
,
W. B.
,
Serovy
,
G. K.
, and
Sandercock
,
D. M.
,
1988
, “
Design Point Variation of Three-Dimensional Loss and Deviation for Axial Compressor Middle Stage
,”
ASME J. Turbomach.
,
110
, pp.
426
433
.
8.
Hobbs
,
D. E.
, and
Weingold
,
H. D.
,
1984
, “
Development of Controlled Diffusion Airfoils for Multistage Compressor Application
,”
ASME J. Eng. Gas Turbines Power
,
106
, pp.
271
278
.
9.
Janssen, M., Zimmermann, H., Kopper, F., and Richardson, J., 1995, “Application of Aero-Engine Technology to Heavy Duty Gas Turbines,” ASME-Paper 95-GT-133, Houston, Texas.
10.
Elmendorf, W., Mildner, F., Ro¨per, R., Kru¨ger, U., and Kluck, M., 1998, “Three-Dimensional Analysis of a Multistage Compressor Flow Field,” ASME-Paper 98-GT-249, Stockholm, Sweden.
11.
Tascflow 3D Documentation, 1995–1997, Advanced Scientific Computing Ltd., Waterloo, Ontario, Canada.
12.
Ko¨ller, U., Mo¨nig, R., Schreiber, H. A., and Ku¨sters, B., 1999, “Development of Advanced Compressor Airfoils for HeavyDuty Gas Turbines; Part I: Design and Optimization,” ASME-Paper 99-GT-95, Indianapolis.
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