An experimental development program is proposed to design, fabricate, and performance test a compact two stage centrifligal compressor. The design is based on the extensive experience of the Principal Investigator and other team members with over 125 years of collective demonstrated turbomachinery knowledge. Specifically, anention has been focused on the aerodynamic design that eliminates use of complex cross-over ducting with turning vanes and will feature high specific speed mixed-flow first-stage and a moderately low specific speed centriftigal second stage with efficient diffbsion. Compactness will be achieved by reducing the diameter ratio, OD/Impeller Tip Diameter, while maintaining an equal level of performance. The Phase I investigation will provide aerodynamic and mechanical designs together with preliminary layout drawings and a Phase II demonstration plan. Cost estirnates will be obtained for components using the layout drawings in order to establish realistic assessment of the costs for the Phase II effort. State-of-the-art, demonstrated codes will be used to assist in the design process together with the hands-on experience of the proposed team. The proposed effort has the potential to improve performance of small turbomachinery such as auxiliary power units, main propulsion engines, and natural gas compressors for both military and commercial applications. Platforms would consist of small aircraft, helicopters, UAV's, missiles, turbojets, turboprops, turbofans, and combinations thereof.
Keywords: COMPRESSOR GAS TURBINE CENTRIFUGAL HIGH PRESSURE RATIO TURBOMACHINERY DIFFUSERS
