The flow through gas turbine compressors is often characterized by unsteady, transonic, and viscous phenomena. Accurately predicting the behavior of these complex multi-blade-row flows with unsteady rotor–stator interacting Navier–Stokes analyses can require enormous computer resources. In this investigation, several methods for predicting the flow field, losses, and performance quantities associated with axial compressor stages are presented. The methods studied include: (1) the unsteady fully coupled blade row technique, (2) the steady coupled blade row method, (3) the steady single blade row technique, and (4) the loosely coupled blade row method. The analyses have been evaluated in terms of accuracy and efficiency.

1.
Adamczyk, J. J., 1985, “Model Equation for Simulating Flows in Multistage Turbomachinery,” ASME Paper No. 85-GT-226.
2.
Baldwin, B. S., and Lomax, H., 1978, “Thin-Layer Approximation and Algebraic Model for Separated Turbulent Flows,” AIAA Paper No. 78-257.
3.
Chakravarthy, S., and Osher, S., 1982, “Numerical Experiments With the Osher Upwind Scheme for the Euler Equations,” AIAA Paper No. 82-0975.
4.
Chen, J. P., Celestina, M. L., and Adamczyk, J. J., 1994, “A New Procedure for Simulating Unsteady Flows Through Turbomachinery Blade Rows,” ASME Paper No. 94-GT-151.
5.
Chima
R. V.
,
1987
, “
Explicit Multigrid Algorithm for Quasi-Three-Dimensional Viscous Flows in Turbomachinery
,”
AIAA Journal of Propulsion and Power
, Vol.
3
, No.
5
, pp.
397
405
.
6.
Crook, A. J., and Delaney, R. A., 1992, “Investigation of Advanced Counterrotation Blade Configuration Concepts for High Speed Turboprop Systems: Task IV—Advanced Fan Section Aerodynamic Analysis Final Report,” NASA CR-187128, Nov.
7.
Davis
R. L.
,
Hobbs
D. E.
, and
Weingold
H. D.
,
1988
, “
Prediction of Compressor Cascade Performance Using a Navier–Stokes Technique
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
110
, pp.
520
531
.
8.
Dawes
W. N.
,
1992
, “
Toward Improved Throughflow Capability: The Use of 3D Viscous Flow Solvers in a Multistage Environment
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
114
, pp.
8
17
.
9.
Denton, J. D., and Singh, U. K., 1979, “Time Marching Methods for Turbomachinery Flow Calculations,” VKI Lecture Series, 1979–.7.
10.
Denton, J. D., 1986, “The Use of a Distributed Body Force to Simulate Viscous Flow in 3D Flow Calculations,” ASME Paper No. 86-GT-144.
11.
Dorney
D. J.
, and
Verdon
J. M.
,
1994
, “
Numerical Simulations of Unsteady Cascade Flows
,”
ASME JOURNAL OF TURBOMACHINERY
, Vol.
116
, pp.
665
675
.
12.
Dorney, D. J., Davis, R. L., and Sharma, O. P., 1995, “Unsteady Multi-stage Analysis Using a Loosely-Coupled Blade Row Approach,” AIAA Paper No. 95-0179; to be published in the AIAA Journal of Propulsion and Power.
13.
Giles, M., 1991, “UNSFLO: A Numerical Method for the Calculation of Unsteady Flow in Turbomachinery,” MIT Gas Turbine Laboratory Report No. 205.
14.
LeJambre, C. J., Zacharias, R. M., Biederman, B. P., Gleixner, A. J., and Yetka, C. J., 1995, “Development and Application of a Multistage Navier–Stokes Solver—Part II: Application to a High Pressure Compressor Design,” ASME Paper No. 95-GT-343, to appear in the ASME JOURNAL OF TURBOMACHINERY.
15.
Rai
M. M.
,
1989
, “
Three-Dimensional Navier–Stokes Simulations of Turbine Rotor–Stator Interaction
,”
AIAA Journal of Propulsion and Power
, Vol.
5
, No.
3
, pp.
307
319
.
16.
Rao
K. V.
,
Delaney
R. A.
, and
Dunn
M. G.
,
1994
a, “
Vane-Blade Interaction in a Transonic Turbine: Part I—Aerodynamics
,”
AIAA Journal of Propulsion and Power
, Vol.
10
, No.
3
, pp.
305
311
.
17.
Rao
K. V.
,
Delaney
R. A.
, and
Dunn
M. G.
,
1994
b, “
Vane-Blade Interaction in a Transonic Turbine: Part II—Heat Transfer
,”
AIAA Journal of Propulsion and Power
, Vol.
10
, No.
3
, pp.
312
317
.
18.
Rhie, C. M., Gleixner, A. J., Spear, D. A., Fischberg, C. J., and Zacharias, R. M., 1995, “Development and Application of a Multistage Navier–Stokes Solver—Part I: Multistage Modeling Using Body Forces and Deterministic Stresses,” ASME Paper No. 95-GT-342; to appear in the ASME JOURNAL OF TURBOMACHINERY.
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