Turbine Engine Analysis Compressor Code - TEACC. II - Multi-stage compressors and inlet distortion

A technique to predict the effects of inlet distortion on a compression system is in high demand and numerical approaches using three-dimensional CFD are being investigated as possible solutions. The traditional CFD approach of simulating the flow through each blade of the compression system is still too computationally intense to be timely to the testing community. This paper reports on additional developments of a three-dimensional computational tool, TEACC, which uses approximate methods to simulate the effect of turbomachinery. TEACC has been extended to simulate a single-stage machine, Stage-3.5, a modem three-stage military fan, and a modern ninestage military high pressure compressor. The predicted results were compared to the available experimental data for clean inlet performance. In addition, a detailed investigation of a single rotor, Rotor 16, was investigated in the presence of a classical radial total pressure distortion.