摘要
四通道环形进气先进旋涡燃烧室(AVC)上下两个通道具有冷却燃烧壁面、中间两通道的靠近燃烧室轴线的通道面积小,在贫油燃烧时,一定程度上可充当值班火焰通道的作用。以导流片到前钝体上端面的距离与燃烧室进气通道高度之比a/E、导流片伸入凹腔的长度与前钝体高度之比b/H、导流片到前钝体后端面的距离与凹腔长度之比c/L为研究对象进行数值模拟,并分析导流片结构参数a/E、b/H、c/L不同时燃烧室的流场分布、涡结构、总压损失、燃烧效率。结果表明:随着a/E增大,燃烧效率不断提高,但总压损失系数也增大;b/H、c/L对AVC性能的影响较小;当a/E=0.3、b/H=0.4及c/L=0.2时,燃烧室性能达到最佳;引入导流片后,凹腔内形成稳定的双旋涡结构,凹腔稳焰及燃气掺混有所增强,总压损失较小的同时燃烧效率大幅度提高。
The four-duct-annular advanced vortex combustor(AVC)has small duct area near the combustor axis of cooling burn wall and middle two-duct,which can be served as duty fire duct under poor oil burning.The numerical simulation is carried out by considering the ratio of the distance between the flow guide vanes to the upper end face of the front bluff body and the height of the inlet passage a/E,the ratio of the length of the flow guide vanes extending into the cavity and the height of the front bluff body b/H,and the ratio of the distance between the flow guide vanes and the rear end face of the front bluff body and the length of the cavity c/L as the research object,The effects of different structure parameters a/E、b/H、c/L of the flow guide vanes on flow fields,structure of vortices,the total pressure loss,and combustion efficiency are analyzed.The results show that,with the increasing value of a/E,the combustion efficiency is increased significantly,and the total pressure loss coefficient also increases simultaneously.The structure parameters of b/H and c/L are of low influence on AVC performance.When a/E=0.3,b/H=0.4,c/L=0.2,the combustor can achieve the best performance.The stable dual vortices structure is formed in the cavity after k dtroducing the flow guide vanes,the stability of flame and the mixing of gas in the cavity are enhanced,the acceptable pressure loss is lesser and the combustion efficiency is greatly increased.
作者
张长天
刘景源
ZHANG Changtian;LIU Jingyuan(Jiangxi Key Laboratory of Micro Aeroengine,Nanchang Hangkong University,Nanchang 330063,China)
出处
《航空工程进展》
CSCD
2021年第4期138-146,共9页
Advances in Aeronautical Science and Engineering
基金
国家自然科学基金(11562012)
江西省微小航空发动机重点实验室开放基金(Ef202006072)。
关键词
先进旋涡燃烧室
导流片
双旋涡
燃烧效率
总压损失系数
数值模拟
advanced vortex combustor
flow guide vane
dual vortices
combustion efficiency
total pressure loss coefficient
numerical simulation
