航空涡轮发动机燃烧室内流场的PIV测量  

PIV measurement for inner flowfield in aero turbine engine combustor

作　　者：张俊[1] 陈柳君[2,3] 胥頔 吴运刚[1] 张龙[1] 

机构地区：[1]中国空气动力研究与发展中心设备设计及测试技术研究所,四川绵阳621000 [2]西北工业大学动力与能源学院,西安710072 [3]中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《航空动力学报》2017年第6期1289-1295,共7页Journal of Aerospace Power

摘　　要：设计了一种基于旋风分离原理的高压粒子发生器,并成功应用于高压状态下的航空涡轮发动机燃烧室内流场的PIV(粒子图像测速法)测量.在氢氧燃烧加热来流温度为813K、燃烧室压力为2.78MPa条件下,应用PIV技术开展了航空涡轮发动机单头部燃烧室复杂内流场测量研究,实现了高温高压条件下强旋流、强扰流、宽速域流场的PIV测量,获得了接近燃烧室工作压力工况下的流场速度和流场精细结构.结果表明:该型燃烧室内流场存在多处旋涡结构,形成回流区;流场旋流作用强,横截面流场存在顺时针大涡;主燃孔射流和掺混孔射流作用明显,射流穿透深度较大,对流场结构影响显著;高温高压状态下,流场结构与常温中压状态类似.A high pressure particle generator based on cyclone separation principle was designed,and applied for PIV （particle image velocimetry） measurement of inner flowfield of high pressure aero turbine engine combustor successfully.With the combustion flow of hydrogen and oxygen,the research of measurement for complicated inner flowfield in the single sector combustor of aero turbine engine was carried out by PIV at 813 K and 2.78 MPa.The strong rotational and turbulent inner flowfield with wide velocity range was measured under conditions of high temperature and pressure,and the flowfield velocity and microscopic structure close to real work pressure of combustor were obtained.The results show that there are multiple vortices in the inner flowfield of the studied combustor,accompanied with relevant recirculation zones.The effect of swirler is strong,and there is big vortex clockwise in cross section.The jet effect of main combustion holes and dilution holes is obvious,the jet flows have deep penetration,and have distinct effect on the flowfield structure.The flow field structure under high temperature and pressure condition is similar to that under normal temperature and moderate pressure.

关 键 词：燃烧室 3级旋流器 粒子发生器 粒子图像测速法 流场测量 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]