International Journal of Aeronautical and Space Sciences

  • 제7권2호
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  • Pages.33-41
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  • 2006
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  • 2093-274X(pISSN)
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  • 2093-2480(eISSN)
한국항공우주학회 (The Korean Society for Aeronautical and Space Sciences)
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Hybridal Method for the Prediction of Wave Instabilities Inherent in High Energy-Density Combustors (2): Cumulative Effects of Pressure Coupled Responses on Cavity Acoustics

  • 발행 : 2006.12.31
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초록

Theoretical-numerical approach of combustion instability in a specific rocket engine is conducted with parametric response functions. Fluctuating instantaneous burning rate is assumed to be functionally coupled with acoustic pressures and have a finite or time-varying amplitudes and phase lags. Only when the amplitudes and phases of combustion response function are sufficiently large and small respectively, the triggered unstable waves are amplified.

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참고문헌

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