Abstract: In order to understand how the gap between sleeve and baffle affecting the property of combustor exit temperature distribution，an experimental investigation has been carried out to test an annular combustor exit temperature distribution at different gap height，viz. 0.1mm，0.15mm and 0.2mm. The mechanism of gap effect is also analyzed by numerical simulation method. Numerical simulation results revealed that swirl flow direction，primary zone flow structure and mass fraction distribution of kerosene were strongly affected by annular jet from the gap between sleeve and baffle. The experimental and computational results show that combustor exit temperature distribution property is deteriorated while the gap height exceeds the design value. The overall temperature distribution factor (OTDF) increases by 29% and the high temperature point on the radial temperature distribution curve migrates inward more than 10% guide vane height with the increase of gap height.

Key words: Aerospace propulsion system；Gas turbine engine；Combustor；Exit temperature distribution

摘要： 为了研究燃烧室头部涡流器套筒与冷却片配合间隙对燃烧室出口温度场品质的影响规律，分别针对0.1mm，0.15mm及0.2mm三种不同间隙宽度情况进行了燃烧室性能试验研究，并采用数值模拟方法对其影响机理进行了分析。结果表明，通过间隙的环状射流对涡流器旋转射流方向、燃烧室主燃区流场结构以及燃油质量分布均有较大影响。随着间隙宽度增加，燃烧室出口温度分布系数增加了29%，径向温度分布曲线的高温点向叶根方向的移动距离超过10%叶片高度，燃烧室出口温度场品质急剧恶化。

关键词: 航空航天推进系统；燃气涡轮发动机；燃烧室；出口温度场