Abstract:A mathematical model is proposed, which allows calculating the amplitude of forced pressure oscillations in the combustor of a liquid-propellant rocket engine, caused by periodic changes in the nozzle throat area, with allowance for acoustic properties of the combustion zone. Results calculated for some particular cases are given.The development of highly forced combustors is associated with ensuring stability of the operation process. As the combustion zone is capable of sustaining self-induced high-intensity… Show more
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