In this paper, the development of a model 17-stage axial compressor (pressure ratio 14.7) for a medium-size gas turbine is described. The aerodynamic and mechanical design features of the compressor are presented. In advance of the full 17-stage test, the first three and nine stages were tested. Measured results confirm the design performance in the first stages of the 17-stage compressor. The details of the construction of the facilities, instrumentation and data acquisition system for the full 17-stage test are described. Test results for the 17-stage compressor are presented. The measured results are in good agreement with the predicted values.
Development of a High-Pressure-Ratio Axial Flow Compressor for a Medium-Size Gas Turbine
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Kashiwabara, Y., Matsuura, Y., Katoh, Y., Hagiwara, N., Hattori, T., and Tokunaga, K. (October 1, 1986). "Development of a High-Pressure-Ratio Axial Flow Compressor for a Medium-Size Gas Turbine." ASME. J. Turbomach. October 1986; 108(2): 233–239. https://doi.org/10.1115/1.3262042
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