Abstract: A kind of flow in an annular cylinder of high and low pressure turbine axis in aero engine was simplified as a flow model of two co axial annular cylinders rotating independent. The governing equations were non dimensionalized and a series of analogous criteria were driven. The rotating components of rig were designed and set up, and the flow laws were experimentally investigated.Experiment indicates that the drag coefficient will decrease in general with the increasing of cooling air Reynolds number. The influence of the rotating of inner or outer cylinder effects on flow is less than that of cooling air Reynolds number.

Key words: Turbojet engine;Two axis loop;Turbine;Axial flow;Drag coefficient

摘要： 某型发动机高、低压涡轮轴间环形气流通道内的流动可以简化为两个独立旋转同心双轴环道内的流动问题。对其控制方程以及边界条件进行无量纲化 ,得出了实验准则 ,设计并建立了实验台 ,以实验方法研究了具有轴向通流的独立旋转同心双轴环道内的流动规律。结果发现 ,随着冷气雷诺数增大 ,阻力系数总体趋势减小 ;冷气雷诺数的影响远大于内轴和外轴旋转对流动的影响。

关键词: 涡轮喷气发动机;双轴环道;涡轮;轴向流;阻力系数