摘要
为了改善RBCC发动机超燃模态的性能,设计了轴对称结构燃烧室结合小支板组进行燃料喷注的发动机构型。通过煤油的3步简化动力学模型,对不同燃料喷注方式下的发动机性能进行计算分析。结果表明,基于本设计的发动机,让支板火箭工作于小流量富燃状态,可实现超燃模态的可靠点火和稳定燃烧;采用一级支板结合二级壁喷的燃料喷注方式,可获得相对最优的性能;随着燃料当量比的增加,燃烧室压强和推力增加,但燃烧效率降低,比冲也随之下降;在低马赫数条件下,发动机可实现正常工作,但燃烧效率将有所下降。计算结果可为未来RBCC发动机的结构设计和燃烧组织提供参考数据。
In order to improve the performance of scramjet mode of RBCC, the axisymmetric combustor combined with pylon was developed. The scramjet performance in different injection mode was analyzed by three-step reduced chemical kinetic model. It is indicated that robust ignition and combustion were achieved when strut-rocket was operated in fuel-rich condition;the best engine performance can be achieved by pylon injection in front combustor with wall injection in rear;pressure and thrust were enhanced as well as combustion efficiency and impulse were reduced with increase of equivalence ratio of fuel ; successful combustion can be achieved whereas combustion efficiency was lower in low Mach number. The result can be used to design RBCC engine.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第6期728-733,共6页
Journal of Solid Rocket Technology
