Abstract: Continuous multifront detonation of kerosene with air heated to 800 K was obtained and investigated in a flow-through annular combustor with a diameter of 503 mm with narrowing of the exit section and profiling of the channel (by installing cavities at the beginning or end of the combustor). The installation of cavities was shown to increase the frequency of transverse waves. The region of existence of detonation was determined in the coordinates of the specific air flow rate and the equivalence ratio. The existence of continuous multifront detonation was found to be due to collisions of transverse shock waves generating transverse detonation waves which degenerate into shock waves before collisions. The maximum fuel-based specific impulse of 2040 s was obtained when a cavity was installed at the end of the annular cylindrical combustor. The minimum combustor length needed to obtain continuous multifront detonation is in the range from 530 to 670 mm. Measurements of pressure oscillations in the settling chamber and at the combustor exit using high-frequency sensors show that they are sound oscillations. This is important for the practical application of detonation combustion.

Cite: Bykovskii F.A. , Zhdan S.A. , Samsonov A.N. , Vedernikov E.F.
Influence of Combustor Geometry on the Continuous Detonation of a Kerosene–Heated Air Mixture
Combustion, Explosion and Shock Waves. 2025. V.61. N4. P.567-580. DOI: 10.1134/S0010508225700546

Original: Быковский Ф.А. , Ждан С.А. , Самсонов А.Н. , Ведерников Е.Ф.
ВЛИЯНИЕ ГЕОМЕТРИИ КАМЕРЫ СГОРАНИЯ НА РЕЖИМЫ НЕПРЕРЫВНОЙ ДЕТОНАЦИИ СМЕСИ КЕРОСИН — НАГРЕТЫЙ ВОЗДУХ
Физика горения и взрыва. 2025. Т.61. №4. С.79-94. DOI: 10.15372/FGV2024.9441 РИНЦ OpenAlex

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