COMPUTATIONAL COMPRESSOR PERFORMANCE IMPROVEMENTS UTILIZING SELF-RECIRCULATION THROUGH INLET GUIDE VANES

Abstract

Compressor stall is a performance limit on aircraft engines. Increasing compressor stall range broadens the safe operating range of the aircraft. Research into compressor casing treatment designs is needed to accomplish an increase in compressor stability range, while not completely sacrificing efficiency. Flow recirculation over the compressor rotors has been demonstrated to improve both efficiency and stall range in transonic compressors; however, a single general method has not been developed. A different approach to extend the stability range of transonic compressors is flow recirculation through the inlet guide vanes, which was explored in this study. Computational fluid dynamics (CFD) was used to predict performance improvements in the demonstration transonic compressor at the Naval Postgraduate School's Turbo Propulsion Lab. This study demonstrated that pressure side axial flow-recirculation provided a 7.89% stability range increase, a 2.96% stall margin increase, and a 0.23% efficiency increase.Distribution Statement A. Approved for public release: Distribution is unlimited.Ensign, United States NavyONR 35, Arlington V