二次燃烧反应对空水两用涡轮机性能影响

张安静; 秦侃; 王瀚伟; 王谦; 罗凯

doi:10.13224/j.cnki.jasp.20220671

二次燃烧反应对空水两用涡轮机性能影响

doi: 10.13224/j.cnki.jasp.20220671

西北工业大学航海学院，西安 710072

基金项目: 国家自然科学基金（51805435）

详细信息

作者简介:
张安静（1997-），女，硕士生，主要从事空水两用涡轮机研究。E-mail：2020260798@mail.nwpu.edu.cn

通讯作者:
秦侃（1988-），男，副教授、硕士生导师，博士，主要从事水下动力推进研究。E-mail：kan.qin@nwpu.edu.cn

中图分类号: V239；TJ630.1
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出版历程
- 收稿日期: 2022-09-07
- 网络出版日期: 2023-11-10

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

School of Marine Science and Technology，Northwestern Polytechnical University，Xi’an 710072，China

摘要

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、H₂和CH₄，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、H₂和CH₄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2 185 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。
- 空水两用涡轮机 /
- 三维仿真 /
- 组分输运 /
- 二次燃烧 /
- 推进
Abstract:
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, H₂ and CH₄, 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, H₂ and CH₄ 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 2 185 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.
- air-underwater dual-mode turbines /
- three-dimensional simulation /
- species transport /
- secondary combustion /
- propulsion

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图 1 跨介质航行器动力系统示意图

Figure 1. Sketch of the trans-media vehicle power system

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图 2 用于数值验证的计算域和网格

Figure 2. Calculation domain and mesh for numerical validation

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图 3 混合燃烧试验系统组成

Figure 3. Mixed combustion test system composition

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图 4 混合燃烧系统实物装置

Figure 4. Mixed combustion system physical device

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图 5 两股燃气混合燃烧时的试验温度

Figure 5. Test temperature when two gas streams are mixed and burned

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图 6 二次反应室网格划分

Figure 6. Secondary reaction chamber meshing

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图 7 二次燃烧温度云图

Figure 7. Secondary combustion temperature contours

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图 8 计算流场的网格划分

Figure 8. Meshing of computational flow fields

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图 9 流场速度分布云图

Figure 9. Flow field velocity contours

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图 10 流场温度云图

Figure 10. Flow field temperature contours

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图 11 叶栅流场温度分布

Figure 11. Temperature distribution in the cascade flow field

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图 12 各组分质量分数云图对比

Figure 12. Comparison of mass fraction contours of each component

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表 1 Kiely涡轮机设计参数

Table 1. Turbine design parameters from Kiely

参数	数值
涡轮中径/mm	25.76
喷管喉部直径/mm	0.56
喷管出口直径/mm	1.27
叶片高度/mm	1.524
叶片弦长/mm	1.88
叶片边缘厚度/mm	0.076
喷管数目	5
叶片数	75
喷管斜切角/（°）	15
叶片安装角/（°）	25

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表 2 涡轮机边界条件设置

Table 2. Turbine boundary conditions

边界条件	数值
喷管入口总压/MPa	2.0684
喷管入口总温/K	1225
喷管出口总压/MPa	0.0345
转速/（r/min）	435000

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表 3 仿真结果与试验结果对比

Table 3. Comparison of simulation results and test results

参数	网格数/10⁴
参数	150	180	200
输出功率/kW	1.993	1.997	1.996
仿真效率/%	62.43	62.58	62.55
试验效率/%	63

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表 4 燃气入口组分及质量分数

Table 4. Species and mass fraction of inlet %

边界	质量分数
边界	CO₂	H₂O	O₂	CO	H₂	CH₄	N₂
煤油燃气入口	13.8	5.5	7.4				73.4
鱼推3燃气入口	8.1	8.3		62.0	3.0	5.6	13.0
出口	20.6	8.0	2.1				69.7

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表 5 涡轮机的主要设计参数

Table 5. Main design parameters of the turbine

参数	数值
水下喷管数目	1
空中喷管数目	30
水下喷管喉部宽度/mm	1.26
空中喷管喉部高度/mm	12.5
水下喷管喉部高度/mm	12.5
空中喷管标称出口宽/mm	3
水下喷管中心线倾角/（°）	15
空中喷管中心线倾角/（°）	13
转子个数	75
叶片高度/mm	15
叶顶间隙/mm	0.53
尾喷管入口半径/mm	96.03
尾喷管出口半径/mm	30.7
尾喷管收缩锥角/（°）	20
尾喷管收缩段长度/mm	179.5
空腔半径/mm	300.7
空腔长度/mm	541.2
尾喷管圆柱段长度/mm	100

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表 6 燃气入口组分及质量分数

Table 6. Species and mass fraction of inlet

边界	质量分数
边界	H₂	N₂	H₂O	CO₂	CO	CH₄	O₂
水下喷管	0.03	0.13	0.08	0.08	0.62	0.06
空中喷管		0.75	0.022	0.056			0.169

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表 7 无/含二次燃烧结果对比

Table 7. Comparison of results without/with secondary combustion

参数	含二次燃烧	无二次燃烧
尾喷管出口平均速度/（m/s）	927.31	582.79
尾喷管出口温度/K	2185	712
推力/N	1 067.33	819.51
功率/kW	178.11	236.06
效率/%	26.4	29.0
温度理论计算值/K	2 330

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