Abstract
Shock waves are formed in the channels between blades in a compressor working in the transsonic state, and the positions of these vary periodically and produce strong vibrations in the blades. The effect is extremely complex and is dependent on a large number of parameters. Here we present a simplified model for the effect, which can be examined theoretically. It is assumed that the nonstationary pulsations in the flow and the amplitudes in the oscillations of the shock waves are small, and therefore one can employ a steady-state flow whose characteristics may be taken as given, including the mean position of the shock waves.
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S. Lane, “Supersonic flow past an oscillating cascade with supersonic leading-edge locus,” J. Aeronaut. Sci.,24, No. 1 (1957).
D. N. Gorelov, “A plate system in a supersonic nonstationary flow,” Izv. Akad. Nauk SSSR, Mekhan. Zhidk. i Gaza, No. 4 (1960).
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Translated from Zhurnal Prikladnoi Mekhaniki i Tekhnicheskoi Fiziki, No. 5, pp. 41–47, September–October, 1973.
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Gorelov, D.N., Meshman, V.A. Nonstationary gas flow with shock waves in a supersonic compressor. J Appl Mech Tech Phys 14, 636–641 (1973). https://doi.org/10.1007/BF00856873
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DOI: https://doi.org/10.1007/BF00856873