The direct approach of modeling the flow between all blade passages for each blade row in the compressor is too computationally intensive for practical design and analysis investigations with inlet distortion. Therefore a new simulation tool called the Turbine Engine Analysis Compressor Code (TEACC) has been developed. TEACC solves the compressible, time-dependent, three-dimensional Euler equations modified to include turbomachinery source terms, which represent the effect of the blades. The source terms are calculated for each blade row by the application of a streamline curvature code. TEACC was validated against experimental data from the transonic NASA rotor, Rotor 1B, for a clean inlet and for an inlet distortion produced by a 90-deg, one-per-revolution distortion screen. TEACC revealed that strong swirl produced by the rotor caused the compressor to increase in loading in the direction of rotor rotation through the distorted region and decrease in loading circumferentially away from the distorted region.

Issue Section:
Research Papers
Topics:
Compressors, Education, Gas turbines, Steady state, Blades, Rotors, Flow (Dynamics), Turbomachinery, Design, Modeling, NASA, Rotation, Simulation
1.
Billet
G.
,
Huard
J.
,
Chevalier
P.
, and
Laval
P.
,
1988
, “
Experimental and Numerical Study of the Response of an Axial Compressor to Distorted Inlet Flow
,”
ASME Journal of Fluids Engineering
, Vol.
110
, pp.
355
–
360
.
2.
Cooper, G. K., and Sirbaugh, J. R., 1989, “PARC Code: Theory and Usage,” AEDC-TR-89-15, Dec.
3.
Greitzer, E. M., and Strand, T., 1978, “Asymmetric Swirling Flows in Turbomachine Annuli,” ASME Paper No. 78-GT-109.
4.
Hale, A. A., Davis, M. W., Jr., and Kneile, K. R., 1994, “Turbine Engine Analysis Compressor Code: TEACC, Part I: Technical Approach and Steady Results,” AIAA Paper No. 94-0148.
5.
Hearsey, R. M., 1970, “HT0300—A Computer Program for the Design and Analysis of Axial Turbomachinery,” Cambridge, MA, Mar.
6.
Jameson, A., Schmidt, W., and Turkel, E., 1981, “Numerical Solutions of the Euler Equations by Finite Volume Methods Using Runge–Kutta Time-Stepping Schemes,” AIAA Paper No. 81-1259.
7.
Kimzey, W. F., 1977, “An Analysis of the Influence of Some External Disturbances on the Aerodynamic Stability of Turbine Engine Axial Flow Fans and Compressors,” AEDC-TR-77-80, Aug.
8.
Longley, J. P., and Greitzer, E. M., 1992, “Inlet Distortion Effects in Aircraft Propulsion System Integration,” AGARD-LS-183. Advisory Group for Aerospace Research & Development Lecture Series, May.
9.
Mazzawy
R. S.
,
1977
, “
Multiple Segment Parallel Compressor Model for Circumferential Flow Distortion
,”
ASME Journal of Engineering for Power
, Vol.
99
, pp.
288
–
296
.
10.
Pulliam
T. H.
, and
Steger
J. L.
,
1980
, “
Implicit Finite-Difference Simulations of Three Dimensional Compressible Flow
,”
AIAA Journal
, Vol.
18
, No.
2
, pp.
159
–
167
.
11.
Seyler, D. R., and Gostelow, J. P., 1967, “Single Stage Experimental Evaluation of High Mach Number Compressor Rotor Blading: Part 2—Performance of Rotor IB,” NASA-CR-54582, Sept.
12.
Shahrokhi, K. A., 1995, “Application of Modified Dynamic Compression System Model to a Low-Aspect Ratio Fan: Effects of Inlet Distortion,” MS Thesis, Mechanical Engineering, Vanderbilt University, Nashville, TN.
13.
Steenken, W. G., 1983, “Modeling Compression Component Stability Characteristics—Effects of Inlet Distortion and Fan Bypass Duct Disturbances,” AGARD-CP-324, Advisory Group for Aerospace Research & Development Conference Proceedings, Feb.
This content is only available via PDF.
Copyright © 1998
 by The American Society of Mechanical Engineers
You do not currently have access to this content.