论文部分内容阅读
在来流马赫数2.5,总温为285K的条件下,对于带亚燃预燃和流向涡掺混的超声速双燃烧室的亚燃室,进行了计算流体力学正问题设计研究以及实验验证研究。结果表明,亚燃室通过采用内压式三波系进气道、前部集中式主燃孔的火焰筒、增大了的亚燃室体积和火炬流喷口截面积、增设的V型火焰稳定器,使亚燃室内流场组织合理,解决了进气道的热态失速问题,得到了稳定的亚燃室燃烧和达到设计状态的火炬流喷射。
Under the Mach number of 2.5 and the total temperature of 285K, the positive and negative computational fluid mechanics (CFD) combustor subspace with the supersonic dual combustor with the pre-combusting and the vortex-eddy mixing was designed and verified. The results show that the sub-combustion chamber adopts the internal pressure type three-wave air inlet, the front centralized centralized combustion hole flame tube, the enlarged sub-combustion chamber volume and the cross-sectional area of the torch flow nozzle. The additional V-shaped flame stabilizer , So that the flow field in the sub-combustion chamber is reasonable, which solves the problem of thermal stall in the intake passage, and achieves stable combustion in sub-combustion chamber and torch flow injection to design state.