进气道结构对含硼固冲发动机二次燃烧性能影响分析

采用标准k-ε湍流模型,单步涡团耗散燃烧模型以及高速气流作用下KING硼粒子点火燃烧模型,开展了不同进气道结构下冲压发动机补燃室内含硼颗粒三维两相燃烧流动数值模拟;分析了在6种进气道结构对硼颗粒点火燃烧以及燃气燃烧效率的影响;研究结果表明：在相同的边界条件下,进气道结构形式对硼颗粒点火影响不大;燃气燃烧效率在双侧180°的进气结构下最高,双下侧90°进气结构的燃气燃烧效率最低;硼颗粒燃烧效率在双侧180°时燃烧效率最高,在中心进气结构下硼燃烧效率最低;补燃室内总燃烧效率在双侧180°进气道结构时最高,在中心进气结构下最低。

Analyzing the Performance of Boron-Based Propellant Ducted Engine with Different Air Inlet Structure

The numerical simulation of three-dimensional two-phase flow in the boron-based propellant ducted rocket motor with the different inlet structure are carried out by the standard k- ε turbulence model,one-step eddy-dissipation combustion model and the ignition and combustion of boron particles of KING in high-speed flow. The ignition and combustion of boron particles and the combustion efficiency of combustion gas in afterburning chamber of motor with six types of air-inlet structures are analyzed. Combustion efficiency of gas is the highest under the inlet structure of bilateral 180° and it is the lowest at the case of inlet structure of 90° on both down side. The combustion efficiency of boron particles is the highest at the case of inlet structure of bilateral 180° and it is the lowest under the center air intake structure. The total combustion efficiency in afterburning chamber is the highest when the inlet structure for bilateral 180° is adopted and it is the lowest under the structure of center air intake.