摘要
针对煤油-空气旋转爆震发动机(RDE)点火困难问题,提出一种采用等压预燃的爆震循环模式。通过零维的热效率理论分析方法,建立了一种针对于带预燃的爆震热循环效率模型。结果表明,预燃爆震循环的热效率高于理想Brayton循环,低于理想爆震循环。预燃空气比例是热效率的重要影响因素,循环温比为2,预燃空气比例为0时,预燃爆震循环比理想Brayton循环热效率高26.4%,而当预燃空气量逐渐增加,预燃循环效率提升的比例逐渐变小。采用预燃方式有利于液态煤油的点火起爆,在低温比,低预燃空气比例条件下优势明显。试验中应当在保证煤油能够起爆的前提下采用尽可能少的预燃空气。
A isobaric pre-combustion rotating detonation engine(RDE)cycle was proposed to solve the ignition conundrum of kerosene and air.Thermal efficiency model of the isobaric pre-combustion detonation cycle was built by zero dimensional method.The results show that the thermal efficiency of isobaric pre-combustion detonation cycle is higher than that of ideal Brayton cycle and lower than that of ideal detonation cycle.The air ratio of isobaric pre-combustion effects on thermal efficiency greatly.When the cycle temperature ratio is 2 and the pre-combustion air ratio is 0,the thermal efficiency of pre-combustion detonation cycle is 26.4%higher than that of the ideal Brayton cycle.The thermal efficiency rising percentage of pre-combustion detonation cycle declines with air ratio increasing.Pre-combustion is conducive to liquid kerosene detonation ignition.Also precombustion have obvious advantages in low temperature ratio and low pre-combustion air ratio condition.As little as possible air should be used under the successful ignition premise in the experiment.
作者
王丹
陈宏玉
严宇
洪流
WANG Dan;CHEN Hong-yu;YAN Yu;HONG Liu(Science and Technology on Liquid Rocket Engine Laboratory,Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2019年第5期970-977,共8页
Journal of Propulsion Technology
关键词
两级燃烧
旋转爆震发动机
热效率
预燃
性能分析
Two stage combustion
Rotating detonation engine
Thermal efficiency
Pre-combustion
Performance analysis
