火焰筒内环向多孔径向射流的流场研究  

Flow-Field Study of Multi-Hole Radial Jet in Combustor Liner

作　　者：程勇[1] 汪军[1] 

机构地区：[1]上海理工大学动力工程学院,上海200093

出　　处：《热力透平》2005年第2期78-81,104,共5页Thermal Turbine

摘　　要：环向径向射流对燃烧室火焰筒内的流场有着重要的影响。本文采用三维标准kε湍流模型详细模拟了燃烧室火焰筒内外的等温流场,给出了火焰筒不同截面位置的轴向速度和径向速度分布。并对数值模拟结果与实验数据进行了比较,结果符合较好,同时还分析了数值模拟结果与实验数据的差异。研究了火焰筒内多孔径向射流的流场特性,并比较了不同环向径向射流流量对火焰筒内流场的影响。研究结果表明:在射流孔附近,火焰筒内轴向速度和径向速度沿径向的梯度增大;而在火焰筒外,轴向速度沿径向的梯度变化不大,径向速度变化较大,但随着流体的流动,火焰筒外径向速度很快趋于均匀。当射流流量增加时,火焰筒内射流孔中心截面的两对称旋涡逐渐增大。The annular multi-hole radial jets have important effect on combustor liner. The three dimensional k-ε model are employed in the present paper. The isothermal flow-field of liner is numerically simulated in detail, and the axial and radial velocity distributions are given in liner different position. The results of calculation are compared with the experiment measurements, and good agreements are obtained between the calculated and measured axial and radial velocities. The flow characteristics of the liner are also studied, and differences between numerical simulation and experimental results have been analyzed. At the same time, the effect of different annular multi-hole radial jet flow velocity on combustor liner flow-field ais also studied and compared. The result of study shows that the gradient of axial and radial velocity increase near radial jet hole along radius, but in outer of liner, the gradient of axial velocity along radius changes a little, the radial velocity changes greater, and the radial velocity quickly reached the same. When jets flow increased, the two axisymmetric vortexes increased gradually in liner jets hole of cross-section.

关 键 词：火焰筒 环向 多孔 轴向速度 实验数据 模拟结果 射流流量 径向速度 等温流场 湍流模型 速度分布 流场特性 研究结果 梯度变化 速度变化 燃烧室 射流孔 内流场 截面 数值 增大 

分 类 号：TQ051.302[化学工程] V235.113[航空宇航科学与技术—航空宇航推进理论与工程]