摘要
近年来,炮弹增程技术发展迅速。与其它吸气式发动机相比,固体燃料冲压发动机(SFRJ)由于其高比冲(8000~11000N·s/kg)、低成本、结构简单和高可靠性等优点而备受关注。然而,由于燃烧和湍流的相互耦合,固体燃料冲压发动机的内流场非常复杂,为该类发动机的研究难点之一。
针对设计马赫数Ma=3的固体燃料冲压炮弹,对其二维轴对称定常内流场进行了数值模拟,从而为初步设计提供理论依据。本文研究内容主要分为两部分:
第一部分,对进气道初始设计模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明初始进气道的性能不能令人满意;针对初始模型的不足之处,作出了改进,并对改进后的进气道模型进行了数值模拟,分析了流场结构、节流特性以及流场品质,结果表明改进后进气道的性能满足要求;在确定了进气道方案之后,给出其稳定工作范围。
第二部分,在改进后进气道模型基础上,基于标准k—ε湍流模型、简单化学反应机制和涡耗散模型,建立了固体燃料冲压炮弹统一内流场的计算模型,并完成了统一内流场的数值模拟,分析了燃烧室内的流场结构、再附点位置、温度分布、化学组分分布以及总压恢复系数,研究了补燃室长度与空燃比对燃烧效率和发动机性能参数的影响。
本文的研究成果对固体燃料冲压增程炮弹的研制具有一定的参考价值。
Nowadays, the assisted-range technology of projectile develops rapidly. Compared to other air breathing engines, solid fuel ramjet (SFRJ) has become a very attractive propulsion system for its high specific impulse (8000~11000N·s/kg), low cost, structure simplicity and high reliability. However, due to the coupling of combustion and turbulent flow, the internal flow field of SFRJ is very complicated, and it is one of the puzzling problems of SFRJ.
The present paper focuses on the SFRJ assisted range projectile which the design Mach number is 3, the two-dimensional axisymmetric steady internal flow field in SFRJ is numerically simulated, thus provide theory basis for the primary design stage. The research of this paper can be divided into two parts:
In the first part, the original intake model is numerically simulated, then its flow structure, throttle character and flow field character are analyzed, and the results show that the performance of the original intake model is unsatisfactory. Aim at the shortcomings of the original intake model, the improved intake model is obtained, and also its numerical simulation is achieved, then its flow structure, throttle character and flow field character are analyzed, the results show that the performance of intake can meet the request. After the intake model is confirmed, the stable operation range of intake is obtained.
In the second part, on the basis of the improved intake model, the compute model in internal flow field of SFRJ assisted-range projectile is established, which based on the k -εturbulent model, simple react flow and Eddy Dissipation model, and also the numerical simulation of the whole internal flow field are achieved. The flow field structure, reattachment point position, temperature distribution, chemical species distribution and total pressure recovery in the combustion chamber are analyzed. The influence of aft combustion chamber and air-fuel ratio on the combustion efficiency and other performance parameters are also analyzed, respectively.
The conclusions of this paper have reference value for the research and manufacture of SFRJ assisted range projectile.
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