甲烷预冷器三维换热特性数值研究

罗佳茂; 游进; 焦思; 杨顺华; 薄泽民; 肖云雷

doi:10.13224/j.cnki.jasp.20220603

甲烷预冷器三维换热特性数值研究

doi: 10.13224/j.cnki.jasp.20220603

罗佳茂^1,,
游进^1,*, ,,
焦思¹,
杨顺华²,
薄泽民¹,
肖云雷¹

1.
北京流体动力科学研究中心，北京 100011
2.
中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室，四川绵阳 621000

基金项目: 国家自然科学基金（11902337，52207179）

详细信息

作者简介:
罗佳茂（1994-），男，助理研究员，硕士，主要从事组合发动机技术研究。E-mail：luojiamao@cardc.cn

通讯作者:
游进（1981-），男，副研究员，博士，主要从事组合发动机技术研究。E-mail：youjin_nudt@163.com

中图分类号: V231.1
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- 文章访问数: 30
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- 被引次数: 0
出版历程
- 收稿日期: 2022-08-19
- 网络出版日期: 2024-01-09

Numerical study on heat exchange performance for three-dimensional methane pre-cooler

LUO Jiamao^1
,,
YOU Jin^{1,*
, ,},
JIAO Si¹,
YANG Shunhua²,
BO Zemin¹,
XIAO Yunlei¹

1.
Beijing Aerohydrodynamic Research Center，Beijing 100011，China
2.
Science and Technology on Scramjet Laboratory，China Aerodynamics Research and Development Center，Mianyang Sichuan 621000，China

摘要

摘要:
采用三维数值仿真方法对轴向管束式甲烷预冷器的热交换性能进行了评估，获得了预冷器在不同冷却剂当量比和飞行工况下的流场分布，并在此基础上提出了冷却剂流量控制策略。计算结果表明：该型甲烷预冷器在3倍当量比冷却剂条件下最高能将来流空气冷却131 K，能将传统涡轮发动机工作速域拓展至马赫数为3.0以上；预冷器出口空气流场受管束排列方式影响无法实现完全均匀，总温畸变为13.3%；甲烷最高温升为395 K；冷却管内外壁面平均温差约为15 K，管内甲烷横截面内温差约为10 K；预冷器总压恢复系数为0.715～0.88，换热有效度为0.63～0.9，最大功质比为395 kW/kg。在发动机预冷需求和冷却剂消耗限制条件下规划了冷却剂流量控制策略，建议马赫数为2.5以下保持不高于1.5倍当量比冷却剂，马赫数为3.0以上保持3倍当量比冷却剂。
- 预冷器 /
- 甲烷 /
- 预冷发动机 /
- 热交换 /
- 冷却管
Abstract:
A three-dimensional simulation method was established to assess the heat exchange performance with methane as coolant for an axial tube-bundled pre-cooler. The flow field of the pre-cooler was obtained at different coolant equivalent ratios and flight conditions, and the control strategy of coolant massflow was proposed from the simulation results. The assessed results indicated that the incoming air could be cooled 131 K at maximum under the condition of three times the equivalent ratio by methane pre-cooler, extending the working velocity spectrum to Ma=3.0 at least for conventional turbine engine. The air field could not completely well-distributed because of the influence of the tube arrangement which led to a maximum temperature distortion of 13.3%. The methane got a maximum temperature rise of 395 K. The temperature difference between the outside and inside tube surfaces was about 15 K, and the methane temperature range at cross section of the tube was about 10 K. The total pressure recovery coefficient of the pre-cooler was 0.715—0.88, the heat transfer efficiency was 0.63—0.9, and the maximum power-weight ratio was 395 kW/kg. The control strategy for coolant was proposed under the condition of engine pre-cooling requirement and coolant consumption limitation. It is recommended that the consumption of coolant should be restricted to 1.5 times the equivalent ratio as flight velocity was lower than Ma=2.5, and 3.0 times the equivalent ratio as flight velocity was higher than Ma=3.0.
- pre-cooler /
- methane /
- pre-cooled engine /
- heat exchange /
- cooling tube

HTML

图 1 甲烷预冷膨胀循环ATR发动机原理

Figure 1. Schematic of methane pre-cooled expander cycle ATR engine

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图 2 预冷器总体结构

Figure 2. Overall structure of the pre-cooler

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图 3 预冷器轴向截面

Figure 3. Axial section of the pre-cooler

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图 4 预冷器管束分布

Figure 4. Distribution of the pre-cooler tubes

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图 5 预冷器三维计算域

Figure 5. Three-dimensional computed field of the pre-cooler

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图 6 预冷器网格划分

Figure 6. Grid partition for the pre-cooler

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图 7 不同网格仿真结果对比

Figure 7. Comparison of simulation results using different grids

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图 8 不同冷却介质预冷器内总温和压力场分布

Figure 8. Temperature and pressure distribution in pre-cooler with different coolants

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图 9 Ma₀=3.0、φ=3.0条件下空气总温、总压和速度云图

Figure 9. Air contour of total temperature, total pressure and velocity at Ma₀=3.0 with φ=3.0

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图 10 预冷器横截面总温云图（Ma₀=3.0，φ=3.0）

Figure 10. Contour of total temperature at the pre-cooler cross section （Ma₀=3.0，φ=3.0）

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图 11 Ma₀=3.0、φ=3.0条件下预冷器管束壁内及壁面温度

Figure 11. Temperature inside and on wall of pre-cooler tube bundle at Ma₀=3.0 with φ=3.0

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图 12 Ma₀=3.0、φ=3.0条件下甲烷总温、总压和速度云图

Figure 12. Methane contour of total temperature, total pressure and velocity at Ma₀=3.0 with φ=3.0

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图 13 Ma₀=2.8条件下不同冷却剂当量比的总温云图

Figure 13. Contour of total temperature with different equivalent ratio at Ma₀=2.8

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图 14 不同当量比下冷却管出口总温云图

Figure 14. Contour of total temperature at a tube exit with different equivalent ratio

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图 15 冷却剂当量比φ=3.0下不同来流速度空气总温和速度云图

Figure 15. Contour of total temperature and velocity at air outlet at different incoming velocity with φ=3.0

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图 16 空气和甲烷温度变化

Figure 16. Variation of total temperature for air and methane

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图 17 不同飞行工况下预冷器内总压恢复系数变化云图

Figure 17. Contour of total pressure recovery coefficient with different flight condition

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图 18 预冷器空气总压恢复系数与预入口空气流速分布

Figure 18. Distribution of total pressure recovery coefficient of air and the air velocity at pre-cooler entrance

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图 19 预冷器热交换效率

Figure 19. Heat exchange efficiency of the pre-cooler

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图 20 预冷器功质比变化

Figure 20. Power to weight ratio of the pre-cooler

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图 21 不同飞行速度下冷却剂质量流控制策略

Figure 21. Control line of coolant massflow with different flight velocity

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表 1 预冷器仿真计算边界条件

Table 1. Boundary conditions for pre-cooler simulation

边界条件	Ma₀=2.0	Ma₀=2.5	Ma₀=2.8	Ma₀=3.0	Ma₀=3.1
空气流量/（kg/s）	0.4641	0.3372	0.3952	0.4556	0.4556
空气入口静压/kPa	198	213	290	445	445
空气来流总温/K	388	480	550	601	628
空气出口背压/kPa	138	180	246	386	386
冷却剂当量比	1.0/2.0	1.0/2.0/3.0	1.0/2.0/3.0	2.0/3.0	3.0
冷却剂入口静压/kPa	785/1174	717/1029/1346	803/1211/1610	1404/1 885	1 920
冷却剂入口总温/K	117	117	117	117	117
冷却剂出口背压/kPa	500	500	500	500	500

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表 2 试验与仿真结果对比

Table 2. Comparison of test and simulation results

冷却剂种类	参数	文献[25]实验数据	仿真结果	相对误差/%
氮	空气入口温度/K	283	283.8	0.28
	空气出口温度/K	248	247.4	0.24
	空气入口压力/kPa	101.9	103.0	1.08
	空气出口压力/kPa	93.9	93.9	0
氢	空气入口温度/K	279	279.6	0.2
	空气出口温度/K	188	185.1	1.54
	空气入口压力/kPa	101.8	102.6	0.79
	空气出口压力/kPa	96.4	96.4	0

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