Pressure oscillations in ramjet engines are studied.udwithin quasi one-dimensional linear acoustics. The flowudfield in the dump combustor is approximated by divisionudinto three parts: a flow of reactants, a region containing combustion products, and a recirculation zone, separated by a flame sheet and a dividing streamline. udThe three zones are matched by considering kinematicudand conservation relations. Acoustic fields in the inletudsection and in the combustion chamber are coupled toudprovide an analytical equation for the complex waveudnumber characterizing the linear stability. The calculated results are compared with the experimental data reported by the Naval Weapons Center. Reasonable agreements are obtained.
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