【摘要】 基于自研的微观燃烧状态参数与宏观性能参数结合的燃烧边界判定方法，确定了二冲程航空活塞发动机的燃烧边界，研究了在环境温度范围从0℃到-25℃，环境压力范围从95 kPa到70 kPa条件下燃烧边界的变化规律，并量化评价了环境温度和压力对燃烧边界的影响权重及等量关系．结果表明，环境温度和压力的降低均会使稀混合气方向的失火边界和稳定燃烧边界的过量空气系数减小，使浓混合气方向的失火边界和稳定燃烧边界的过量空气系数增大，导致稳定燃烧区域的面积减小，从而增加失火的风险．环境温度对燃烧边界影响权重明显小于环境压力，二者对稳定燃烧边界的等量作用关系可表示为T=(1.45～1.6℃/k Pa)Δp.更多还原

【Abstract】 Based on a self-developed methodology that integrates in-cylinder and out-of-cylinder parameters,the combustion boundaries of a two-stroke aviation piston engine have been established. The study has investigated the variation of combustion boundaries under the environmental temperatures ranging from 0℃ t o-25℃ and t he environmental pressures ranging from 95 k Pa to 70 k Pa. Additionally,it has quantitatively evaluated the influence weights and equivalence relationships of environmental temperature and pressure on the combustion boundaries. The decrease in both environmental temperature and pressure leads to a reduction in the excess air coefficient at the misfire boundary and the stable combustion boundary in the lean mixture direction,and causes an increase in the equivalence ratio at the misfire boundary and the stable combustion boundary in the rich mixture direction. The reduction in the area of the stable combustion region may increase the risk of misfire. The impact weight of environmental temperature on the combustion boundaries is found to be significantly smaller than that of environmental pressure,with their equivalence relationship represented as T=(1.45—1.6 ℃/k Pa)Δp.更多还原