二次燃烧反应对空水两用涡轮机性能影响  

Influence of secondary combustion reaction on the performance of air-underwater dual-mode turbines

作　　者：张安静 秦侃[1] 王瀚伟 王谦[1] 罗凯[1] ZHANG Anjing;QIN Kan;WANG Hanwei;WANG Qian;LUO Kai(School of Marine Science and Technology,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航海学院,西安710072

出　　处：《航空动力学报》2024年第10期229-240,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51805435)。

摘　　要：为使跨介质航行器同时适应水下和空中介质航行,开展了新型双模涡轮机的二次燃烧反应过程研究。该涡轮机于空中工作时以煤油和空气为燃料,于水下工作时以鱼推3推进剂为燃料。而在涡轮机出水起飞阶段,煤油和鱼推3推进剂需同时燃烧,由于鱼推3推进剂的燃烧产物中含有大量的CO、H_(2)和CH_(4),会在与煤油燃烧剩余的空气混合后产生二次燃烧现象。为分析起飞工况时二次燃烧反应造成的影响,通过数值模拟研究了二次燃烧反应对空水两用涡轮机性能的影响。结果表明:两种燃气发生了化学反应,鱼推3燃气中的CO、H_(2)和CH_(4)几乎被完全燃烧;二次燃烧反应主要发生在尾喷管前段,燃烧段的最大温度从712 K增加到2185 K,提高了尾喷管的出口速度,使得推力大约增加了30.24%。该研究为空水两用涡轮机起飞工况时推力的增加提供思路。In order to make the trans medium vehicle adapt to underwater and air medium navigation at the same time,research on the secondary combustion reaction process of a new dual-mode turbine was carried out.The turbine used kerosene and air as fuels when it worked in the air,and used Yutui-3 propellant as fuel when it worked underwater.At the stage of turbine water take-off,kerosene and Yutui-3 propellant need to be burned at the same time.As the combustion products of Yutui-3 propellant contain a large amount of CO,H_(2) and CH_(4),it will produce secondary combustion after mixing with the residual air from kerosene combustion.In order to analyze the influence of secondary combustion reaction during takeoff,the influence of secondary combustion reaction on the performance of air-water dual-purpose turbine was studied by numerical simulation.The results showed that these two kinds of fuel gases had chemical reaction,and CO,H_(2) and CH_(4) in Yutui 3 fuel gas were almost completely burned;the secondary combustion reaction mainly occurred in the front section of the nozzle.The maximum temperature of the combustion section increased from 712 K to 2185 K,which increased the outlet velocity of the nozzle and made the thrust increase by about 30.24%.This study provides an idea for the increase of thrust of air water turbine during takeoff.

关 键 词：空水两用涡轮机 三维仿真 组分输运 二次燃烧 推进 

分 类 号：V239[航空宇航科学与技术—航空宇航推进理论与工程] TJ630.1[兵器科学与技术—武器系统与运用工程]