深冷组合循环发动机氦循环控制方式对稳态性能影响

郑尚喆; 贾琳渊; 高远; 田放; 王祎

doi:10.13224/j.cnki.jasp.20250207

深冷组合循环发动机氦循环控制方式对稳态性能影响

doi: 10.13224/j.cnki.jasp.20250207

郑尚喆^1,,
贾琳渊^{1, 2,*, ,},
高远³,
田放¹,
王祎¹

1.
西北工业大学动力与能源学院，西安 710072
2.
轻型涡轮动力全国重点实验室，西安 710072
3.
中国航发控制系统研究所，江苏无锡 214063

详细信息

作者简介:
郑尚喆（1993-），男，博士生，主要从事组合发动机总体设计研究。E-mail：zhengshangzhe@mail.nwpu.edu.cn

通讯作者:
贾琳渊（1989-），男，副教授，博士，主要从事涡轮发动机总体性能研究。E-mail：jialinyuan@nwpu.edu.cn

中图分类号: V236
计量
- 文章访问数: 628
- HTML浏览量: 353
- PDF量: 32
- 被引次数: 0
出版历程
- 收稿日期: 2025-04-28
- 网络出版日期: 2025-10-22

Effect of helium cycle control method on steady-state performance of deeply precooled combined cycle engine

ZHENG Shangzhe^1
,,
JIA Linyuan^{1, 2,*
, ,},
GAO Yuan³,
TIAN Fang¹,
WANG Yi¹

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine，Xi’an 710072，China
3.
Aero Engine Control System Institute，Aero Engine Corporation of China，Wuxi Jiangsu 214063，China

摘要

摘要:
闭式氦循环是影响深冷组合循环发动机性能的重要环节。针对深冷组合循环发动机，建立了基于部件法的发动机稳态性能计算模型，分析了在相同的稳态控制规律下，深冷组合循环发动机闭式氦循环的控制方式的改变对发动机性能的影响。在基准控制方式1的基础上，通过选择氦循环起点温度、起点压力、涡轮2可调导叶位置及氦质量4个变量中的任意两个作为调节自由度，但受限于系统约束，最终提出了3种可行的氦循环控制方式，开展氦循环控制方式对发动机最大状态与节流状态性能的影响分析。结果表明：发动机在最大状态工作时，控制方式4无法完成，若以推力最大为目标应选择控制方式2，若以节省氢燃料或降低氦循环系统复杂程度为目标，则选择控制方式3。在进行节流状态工作时，基准的控制方式1节流程度更深，控制方式2更远离喘振边界，控制方式3的耗油率最高。
- 深冷组合循环发动机 /
- 闭式氦循环 /
- 控制规律 /
- 控制方式 /
- 最大状态 /
- 节流状态 /
- 稳态性能
Abstract:
The closed helium cycle is a critical factor affecting engine performance in the deeply precooled combined cycle engine. A steady-state performance calculation model based on the component-based method for deeply precooled combined cycle engine was established, and the impact of modifying control method for the closed helium cycle under identical steady-state control schedule was analyzed. Using the baseline control mode 1 as a reference, any two of the four variables: initial helium cycle temperature, initial pressure, adjustable guide vane of turbine 2 and helium mass in regulation system were selected as the degrees of freedom for adjustment, but due to system constraints, three feasible helium cycle control methods were finally proposed. The analysis of these control methods on maximum and throttling states revealed that, when the engine operated in the maximum state, control method 4 cannot be completed. If the maximum thrust was the target, control method 2 should be selected. If the target was to save hydrogen fuel or reduce the complexity of the helium circulation system, control method 3 should be selected. When performing throttling state operation, control method 1 had a deeper throttling, control method 2 was farther away from the surge boundary, and control method 3 had the highest fuel consumption rate.
- deeply precooled combined cycle engine /
- closed helium cycle /
- control schedule /
- control method /
- maximum state /
- throttling state /
- steady-state performance

HTML

图 1 深冷组合循环发动机方案

Figure 1. Scheme of deeply precooled combined cycle engine

下载: 全尺寸图片幻灯片

图 2 预冷器模块结构图

Figure 2. Precooler module structure diagram

下载: 全尺寸图片幻灯片

图 3 预冷器轴向结构视图

Figure 3. Precooler axial structure view

下载: 全尺寸图片幻灯片

图 4 闭式氦循环系统组成

Figure 4. Compositions of closed helium cycle system

下载: 全尺寸图片幻灯片

图 5 控制规律分区示意图

Figure 5. Control schedule partition diagram

下载: 全尺寸图片幻灯片

图 6 飞行轨迹

Figure 6. Flight trajectory

下载: 全尺寸图片幻灯片

图 7 不同调节方式下的发动机状态参数对比

Figure 7. Comparison of engine state parameters under different control methods

下载: 全尺寸图片幻灯片

图 8 不同调节方式下的发动机性能参数对比

Figure 8. Comparison of engine parameters under different control methods

下载: 全尺寸图片幻灯片

图 9 发动机推力对比

Figure 9. Comparison of engine thrust

下载: 全尺寸图片幻灯片

图 10 节流状态压气机工作线

Figure 10. Operating lines of compressor under throttling

下载: 全尺寸图片幻灯片

图 11 节流状态性能

Figure 11. Throttling performance

下载: 全尺寸图片幻灯片

表 1 发动机变量与平衡方程

Table 1. Engine variables and equilibrium equation

部件	变量	平衡方程
压气机	n₁, n₂, Z_c1, Z_c2	L_c1=L_t1, L_c2=L_t2
氢泵	n₃, p₃₂	L_p=L_t3
涡轮	W_t1,cor, W_t2,cor,	W_c2=W_t1, W_p=W_t2,
	W_t3,cor, C_tff2	W_p=W_t3
换热器	T₂₄
氦循环	T₂₁, p₂₁, m_rs	T₂₁=$T'_{21} $, p₂₁=$p'_{21} $
		m_He,tot=m_He,tot,des
尾喷管		W₃₆+W₁₃=W₁₈

下载: 导出CSV

表 2 闭式氦循环基准控制方式

Table 2. Closed helium cycle control method

T₂₁	p₂₁	C_tff2	m_rs
固定	固定	可调	有

下载: 导出CSV

表 3 发动机设计点参数

Table 3. Engine design point parameters

参数	数值
高度H/km	25.61
飞行马赫数Ma	5.0
空气流量W_a/（kg/s）	100.0
氦气流量W_He/（kg/s）	20.89
氢气流量$W_{{\mathrm{H}}_2} $/（kg/s）	8.08
空气压气机压比π_c1	30.00
氦气压气机压比π_c2	6.13
氦循环起始温度T₂₁/K	50.00
氦循环起始压力p₂₁/MPa	3.00
预冷器出口温度T₂₃/K	1050
氦涡轮前温度T₂₄/K	1300
空气压气机百分比转速n₁/%	83
氦气压气机百分比转速n₂/%	100
氢泵百分比转速n₃/%	100
空气压气机换算转速n_1,cor	0.7
氦气压气机换算转速n_2,cor	1.0

下载: 导出CSV

表 4 发动机设计点性能

Table 4. Engine design point performance

参数	数值
推力F_n/kN	130.86
单位推力F_s/（kN/（kg/s））	1.308
耗油率S_fc/（kg/（N·h））	0.223
比冲I_sp/s	1650

下载: 导出CSV

表 5 氦循环控制方式对比

Table 5. Comparison of helium cycle control method

方式	T₂₁	p₂₁	C_tff2	m_rs
1	固定	固定	可调	有
2	不固定	固定	不可调	有
3	固定	不固定	可调	无
4	不固定	固定	可调	无

下载: 导出CSV

参考文献(30)

[1]	王亚飞, 安永旺, 杨继何. 临近空间飞行器的现状及发展趋势[J]. 国防技术基础, 2010(1): 33-37. WANG Yafei, AN Yongwang, YANG Jihe. Present situation and development trend of near-space vehicles[J]. Technology Foundation of National Defence, 2010(1): 33-37. (in Chinese WANG Yafei, AN Yongwang, YANG Jihe. Present situation and development trend of near-space vehicles[J]. Technology Foundation of National Defence, 2010(1): 33-37. (in Chinese)
[2]	赵海洋, 刘书雷, 吴集, 等. 国外高超声速临近空间飞行器技术进展[J]. 飞航导弹, 2013(9): 8-13. ZHAO Haiyang, LIU Shulei, WU Ji, et al. Technical progress of hypersonic near-space vehicles abroad[J]. Aerodynamic Missile Journal, 2013(9): 8-13. (in Chinese ZHAO Haiyang, LIU Shulei, WU Ji, et al. Technical progress of hypersonic near-space vehicles abroad[J]. Aerodynamic Missile Journal, 2013(9): 8-13. (in Chinese)
[3]	张海林, 周林, 马骁, 等. 临近空间飞行器发展现状及军事应用研究[J]. 飞航导弹, 2014(7): 3-7. ZHANG Hailin, ZHOU Lin, MA Xiao, et al. Research on development status and military application of near space vehicles[J]. Aerodynamic Missile Journal, 2014(7): 3-7. (in Chinese ZHANG Hailin, ZHOU Lin, MA Xiao, et al. Research on development status and military application of near space vehicles[J]. Aerodynamic Missile Journal, 2014(7): 3-7. (in Chinese)
[4]	HEMPSELL M, BOND A. SKYLON: an example of commercial launch system development[J]. Journal of the British Interplanetary Society, 2014, 67(11/12): 434-439.
[5]	HEMPSELL M, BOND A, BOND R, et al. Progress on the SKYLON and SABRE development programme[C]//62nd International Astronautical Congress. Cape Town, South Africa: International Astronautical Federation, 2011: 7519-7525.
[6]	MURRAY J J, HEMPSELL C M, BOND A. An experimental precooler for airbreathing rocket engines[J]. Journal of the British Interplanetary Society, 2001, 54(5/6): 199-209.
[7]	谭米, 马薏文, 苗辉. 反应发动机公司破产: SABRE发动机发展停滞[J]. 航空动力, 2024(6): 25-27. TAN Mi, MA Yiwen, MIAO Hui. REL goes into bankruptcy: taking the SABRE with it[J]. Aerospace Power, 2024(6): 25-27. (in Chinese TAN Mi, MA Yiwen, MIAO Hui. REL goes into bankruptcy: taking the SABRE with it[J]. Aerospace Power, 2024(6): 25-27. (in Chinese)
[8]	陈操斌, 郑日恒, 马同玲, 等. 带有闭式布雷顿循环的预冷发动机特性研究[J]. 推进技术, 2021, 42(8): 1749-1760. CHEN Caobin, ZHENG Riheng, MA Tongling, et al. Study on characteristics of precooling engine with closed Brayton cycle[J]. Journal of Propulsion Technology, 2021, 42(8): 1749-1760. (in Chinese CHEN Caobin, ZHENG Riheng, MA Tongling, et al. Study on characteristics of precooling engine with closed Brayton cycle[J]. Journal of Propulsion Technology, 2021, 42(8): 1749-1760. (in Chinese)
[9]	李帅, 马同玲, 刘洪涛, 等. SABRE预冷器结构参数对其性能影响的数值分析[J]. 推进技术, 2022, 43(4): 200818. LI Shuai, MA Tongling, LIU Hongtao, et al. Numerical analysis of effects of pre-cooler structure parameter on its performance in SABRE[J]. Journal of Propulsion Technology, 2022, 43(4): 200818. (in Chinese LI Shuai, MA Tongling, LIU Hongtao, et al. Numerical analysis of effects of pre-cooler structure parameter on its performance in SABRE[J]. Journal of Propulsion Technology, 2022, 43(4): 200818. (in Chinese)
[10]	YU Xuanfei, YU Wenli, WANG Cong, et al. Thermodynamic analysis of the influential mechanism of fuel properties on the performance of an indirect precooled hypersonic airbreathing engine and vehicle[J]. Energy Conversion and Management, 2019, 196: 1138-1152. doi: 10.1016/j.enconman.2019.06.049
[11]	YU Xuanfei, WANG Cong, YU Daren. Minimization of entropy generation of a closed Brayton cycle based precooling-compression system for advanced hypersonic airbreathing engine[J]. Energy Conversion and Management, 2020, 209: 112548. doi: 10.1016/j.enconman.2020.112548
[12]	YU X, WANG C, QIN J, et al. Thermodynamic analysis of precooled airbreathing engine[J]. Journal of Engineering Thermophysics, 2018, 39: 31-37.
[13]	YU Xuanfei, WANG Cong, YU Daren. Thermodynamic design and optimization of the multi-branch closed Brayton cycle based precooling-compression system for a novel hypersonic aeroengine[J]. Energy Conversion and Management, 2020, 205: 112412. doi: 10.1016/j.enconman.2019.112412
[14]	高远, 陈玉春, 史新兴. 深冷组合发动机吸气模态最大状态控制规律研究[J]. 推进技术, 2020, 41(12): 2659-2669. GAO Yuan, CHEN Yuchun, SHI Xinxing. Maximum state control schedule research on deeply precooled combined cycle engine in airbreathing mode[J]. Journal of Propulsion Technology, 2020, 41(12): 2659-2669. (in Chinese GAO Yuan, CHEN Yuchun, SHI Xinxing. Maximum state control schedule research on deeply precooled combined cycle engine in airbreathing mode[J]. Journal of Propulsion Technology, 2020, 41(12): 2659-2669. (in Chinese)
[15]	郑尚喆, 陈玉春, 王治华, 等. SABRE4氦循环分流比对设计点氢流量影响分析[J]. 航空动力学报, 2024, 39(11): 20220774. ZHENG Shangzhe, CHEN Yuchun, WANG Zhihua, et al. Influence of helium cycle flow ratio on SABRE4 design point hydrogen flow rate[J]. Journal of Aerospace Power, 2024, 39(11): 20220774. (in Chinese ZHENG Shangzhe, CHEN Yuchun, WANG Zhihua, et al. Influence of helium cycle flow ratio on SABRE4 design point hydrogen flow rate[J]. Journal of Aerospace Power, 2024, 39(11): 20220774. (in Chinese)
[16]	邹正平, 王一帆, 姚李超, 等. 超临界二氧化碳闭式布莱顿循环系统研究进展[J]. 北京航空航天大学学报, 2022, 48(9): 1643-1677. ZOU Zhengping, WANG Yifan, YAO Lichao, et al. Progress in research of closed supercritical carbon dioxide Brayton cycle system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(9): 1643-1677. (in Chinese ZOU Zhengping, WANG Yifan, YAO Lichao, et al. Progress in research of closed supercritical carbon dioxide Brayton cycle system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2022, 48(9): 1643-1677. (in Chinese)
[17]	邹正平, 王一帆, 额日其太, 等. 高超声速强预冷航空发动机技术研究进展[J]. 航空发动机, 2021, 47(4): 8-21. ZOU Zhengping, WANG Yifan, ERIQITAI, et al. Research progress on hypersonic precooled airbreathing engine technology[J]. Aeroengine, 2021, 47(4): 8-21. (in Chinese ZOU Zhengping, WANG Yifan, ERIQITAI, et al. Research progress on hypersonic precooled airbreathing engine technology[J]. Aeroengine, 2021, 47(4): 8-21. (in Chinese)
[18]	邹正平, 王一帆, 杜鹏程, 等. 强预冷发动机新型热力循环布局及性能分析[J]. 火箭推进, 2021, 47(6): 62-75. ZOU Zhengping, WANG Yifan, DU Pengcheng, et al. Thermodynamic performance analysis of anovel precooled airbreathing engine layout[J]. Journal of Rocket Propulsion, 2021, 47(6): 62-75. (in Chinese ZOU Zhengping, WANG Yifan, DU Pengcheng, et al. Thermodynamic performance analysis of anovel precooled airbreathing engine layout[J]. Journal of Rocket Propulsion, 2021, 47(6): 62-75. (in Chinese)
[19]	ZOU Zhengping, WANG Yifan, DU Pengcheng, et al. A novel simplified precooled airbreathing engine cycle: thermodynamic performance and control law[J]. Energy Conversion and Management, 2022, 258: 115472. doi: 10.1016/j.enconman.2022.115472
[20]	马文友, 张文胜, 马元, 等. 基于控制规律的PATR发动机典型工况点速度与高度特性分析[J]. 火箭推进, 2022, 48(6): 35-43. MA Wenyou, ZHANG Wensheng, MA Yuan, et al. Analysis of velocity and altitude characteristics at typical operating conditions based on control law of PATR engine[J]. Journal of Rocket Propulsion, 2022, 48(6): 35-43. (in Chinese MA Wenyou, ZHANG Wensheng, MA Yuan, et al. Analysis of velocity and altitude characteristics at typical operating conditions based on control law of PATR engine[J]. Journal of Rocket Propulsion, 2022, 48(6): 35-43. (in Chinese)
[21]	高远, 陈玉春, 王治华, 等. 深冷组合循环发动机吸气模态循环分析与设计可行域研究[J]. 推进技术, 2020, 41(6): 1217-1226. GAO Yuan, CHEN Yuchun, WANG Zhihua, et al. Cycle analysis and design feasible region research of deeply precooled combined cycle engine in airbreathing mode[J]. Journal of Propulsion Technology, 2020, 41(6): 1217-1226. (in Chinese GAO Yuan, CHEN Yuchun, WANG Zhihua, et al. Cycle analysis and design feasible region research of deeply precooled combined cycle engine in airbreathing mode[J]. Journal of Propulsion Technology, 2020, 41(6): 1217-1226. (in Chinese)
[22]	SELLER J F, DANIELE C J. DYNGEN: a program for calculating steady-state and transient performance of turbojet and turbofan engines[M]. Washington DC: National Aeronautics and Space Administration, 1975.
[23]	高远, 陈玉春, 史新兴. SABRE预冷器计算模型及其在整机模型中的应用[J]. 推进技术, 2021, 42(11): 2485-2493. GAO Yuan, CHEN Yuchun, SHI Xinxing. SABRE precooler calculation model and its application in engine model[J]. Journal of Propulsion Technology, 2021, 42(11): 2485-2493. (in Chinese GAO Yuan, CHEN Yuchun, SHI Xinxing. SABRE precooler calculation model and its application in engine model[J]. Journal of Propulsion Technology, 2021, 42(11): 2485-2493. (in Chinese)
[24]	杨世铭, 陶文铨. 传热学[M]. 4版. 北京: 高等教育出版社, 2006. YANG Shiming, TAO Wenquan. Heat transfer[M]. 4th ed. Beijing: Higher Education Press, 2006. (in Chinese YANG Shiming, TAO Wenquan. Heat transfer[M]. 4th ed. Beijing: Higher Education Press, 2006. (in Chinese)
[25]	关醒凡. 现代泵理论与设计[M]. 北京: 中国宇航出版社, 2011. GUAN Xingfan. Modern pumps theory and design[M]. Beijing: China Astronautic Publishing House, 2011. (in Chinese GUAN Xingfan. Modern pumps theory and design[M]. Beijing: China Astronautic Publishing House, 2011. (in Chinese)
[26]	黄兴. 超燃冲压发动机特性计算与一体化设计技术研究[D]. 西安: 西北工业大学, 2014. HUANG Xing. The characteristic simulation of scramjet and the integration design research[D]. Xi’an: Northwestern Polytechnical University, 2014. (in Chinese HUANG Xing. The characteristic simulation of scramjet and the integration design research[D]. Xi’an: Northwestern Polytechnical University, 2014. (in Chinese)
[27]	严传俊, 范玮. 燃烧学[M]. 西安: 西北工业大学出版社, 2005. YAN Chuanjun, FAN Wei. Combustion science[M]. Xi’an: Northwestern Polytechnical University Press, 2005. (in Chinese YAN Chuanjun, FAN Wei. Combustion science[M]. Xi’an: Northwestern Polytechnical University Press, 2005. (in Chinese)
[28]	杨立军, 富庆飞. 液体火箭发动机推力室设计[M]. 北京: 北京航空航天大学出版社, 2013. YANG Lijun, FU Qingfei. Design of thrust chamber of liquid rocket engine[M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2013. (in Chinese YANG Lijun, FU Qingfei. Design of thrust chamber of liquid rocket engine[M]. Beijing: Beijing University of Aeronautics and Astronautics Press, 2013. (in Chinese)
[29]	高远. 深冷组合循环发动机总体性能与控制规律研究[D]. 西安: 西北工业大学, 2022. GAO Yuan. Performance simulation and control schedule design of deeply precooled combined cycle engine[D]. Xi’an: Northwestern Polytechnical University, 2022. (in Chinese GAO Yuan. Performance simulation and control schedule design of deeply precooled combined cycle engine[D]. Xi’an: Northwestern Polytechnical University, 2022. (in Chinese)
[30]	LEMMON E W, HUBER M L, MCLINDEN M O. NIST standard reference database 23: reference fluid thermodynamic and transport properties REFPROP Version 9.11[R]. Gaithersburg, US: National Insitute of Standards and Technology, 2013.