涡轮叶片径向槽轴向长度对超紧凑燃烧室性能的影响  

Effects of Cavity Length of Turbine Radial Vane Cavity on Performance of Ultra-Compact Combustor

作　　者：王力军[1] 周辉[2] 江金涛 

机构地区：[1]沈阳航空航天大学能源与环境学院,沈阳110136 [2]沈阳航空航天大学航空航天工程学部(院),沈阳110136

出　　处：《航空发动机》2016年第6期55-60,共6页Aeroengine

基　　金：航空科学基金(2013ZB54009)资助

摘　　要：为探究涡轮叶片径向槽轴向长度对超紧凑燃烧室性能的影响,对3种不同轴向长度的径向槽分别在2种当量比条件下,用FLUENT软件对超紧凑燃烧室内流动及燃烧进行了数值模拟。结果表明:随着径向槽轴向长度的减小,燃烧环内未完全燃烧的微小燃油颗粒和燃气沿着槽的径向迁移量也减少,从而使燃油颗粒和燃油蒸气在燃烧环内的驻留时间增加;当叶片径向槽的轴向长度与燃烧环轴向长度之比等于0.75且燃烧环当量比为0.81时,燃烧室的燃烧性能较好。这对超紧凑燃烧室的优化设计有重要的参考价值。To investigate the effects of axial length of turbine radial vane cavity （RVC） on the performance of Ultra- Compact Combustor （ UCC） , FLUENT was used to simulate the flow and combustion in the UCC for three different axial length of RVC under the condition of two equivalence ratios. Results show that with the reduction of axial length of RVC, the radial migration of unburnt micro fuel particles and gas to RVC is reduced, the residence time of fuel particles and gas is reversely increased in the circumferential cavity. The combustion performance of UCC is better when the ratio of axial length of RVC to that of the circumferential cavity is 0.75 and the equivalence ratio is 0.81. It has important reference value for the optimization design of UCC.

关 键 词：超紧凑燃烧室 涡轮叶片 径向槽 燃烧性能 数值模拟 航空发动机 

分 类 号：V235.2[航空宇航科学与技术—航空宇航推进理论与工程]