1997 Best Paper Award—Education Committee: A Three-Dimensional Turbine Engine Analysis Compressor Code (TEACC) for Steady-State Inlet Distortion

[+] Author and Article Information
A. Hale

Sverdrup Technology, Inc., AEDC Group, Arnold Engineering Development Center, Arnold Air Force Base, TN 37389-6001

W. O’Brien

Virginia Polytechnic Institute and State University, Blacksburg, VA 24061-0139

J. Turbomach 120(3), 422-430 (Jul 01, 1998) (9 pages) doi:10.1115/1.2841733 History: Received February 01, 1997; Online January 29, 2008


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.

Copyright © 1998 by The American Society of Mechanical Engineers
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