火箭推进2026，Vol.52Issue(4)：92-101,149,11.DOI:10.3969/j.issn.1672-9374.2026.04.009
基于盘式结构的非预混气态煤油旋转爆轰燃烧性能探索
Exploration of combustion performance of non-premixed gaseous kerosene rotating detonation based on a disk-type structure
摘要
Abstract
To investigate the characteristics of a disk-shaped rotating detonation combustor under non-premixed conditions,a detonation combustor model featuring an"inward inflow and outward outflow"configuration with both inlet and outlet oriented axially was adopted.Gaseous kerosene was used as fuel,and oxygen-enriched air served as the oxidizer.Numerical simulations were conducted to study the effects of different inlet Mach numbers on the combustion characteristics within the disk-shaped detonation combustor.The results indicate that the detonation reaction zone in this configuration is primarily concentrated near the turning region close to the outlet,and the right-angle bend structure at the inlet weakens the back-pressure characteristics of the detonation wave.A stable single detonation wave propagation mode was maintained in the combustor under all tested inlet Mach number conditions.As the inflow Mach number increased,the post-wave high-temperature region gradually shrunk.Due to non-premixed inflow,the post-wave region exhibited an interleaved distribution of high-temperature and high-pressure zones.The cold-flow total pressure recovery coefficient decreased with increasing inlet Mach number,whereas under reactive hot conditions,the total pressure recovery coefficient showed an increasing trend with higher Mach numbers.A relative pressure gain effect was achieved in the combustor at an inlet Mach number of 0.8.The combustion efficiency generally decreased as the inlet Mach number increased.关键词
旋转爆轰发动机/数值模拟/传播特性/发动机性能Key words
rotating detonation engine/numerical simulation/propagation characteristics/engine per-formance分类
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闫煌彪,朱志祥,曲鸿昂,丁国玉,黄亚坤..基于盘式结构的非预混气态煤油旋转爆轰燃烧性能探索[J].火箭推进,2026,52(4):92-101,149,11.基金项目
国家自然科学基金(12402433) （12402433）
