A microscale, high-speed compressor impeller (12 mm diameter, 800,000 rpm) was tested for feasibility in regard to aerodynamic performance. The compressor was designed for application in a first-sized gas turbine generator. To survive high stresses at such high temperatures, the rotor was manufactured as a single turbine/compressor/shaft unit in silicon nitride, by the Mold SDM process. Performance testing was conducted in a cold-flow rig at reduced speed of 420,000 rpm. Results from a CFD code compared favorably to measured data at this speed. Extrapolation from test conditions to full design speed was accomplished by application of CFD applied at both speeds.
Microscale Radial-Flow Compressor Impeller Made of Silicon Nitride: Manufacturing and Performance
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Atlanta, GA, June 16–19; 2003, Paper No. 2003-GT-38933. Manuscript received by IGTI, October 2002, final revision, March 2003. Associate Editor: H. R. Simmons.
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Kang, S., Johnston, J. P., Arima , T., Matsunaga , M., Tsuru, H., and Printz, F. B. (June 7, 2004). "Microscale Radial-Flow Compressor Impeller Made of Silicon Nitride: Manufacturing and Performance ." ASME. J. Eng. Gas Turbines Power. April 2004; 126(2): 358–365. https://doi.org/10.1115/1.1739246
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