旋转爆轰反压与轴流压气机相互作用数值模拟

聂嘉仪; 武郁文; 翁春生; 夏益青

doi:10.13224/j.cnki.jasp.20230620

旋转爆轰反压与轴流压气机相互作用数值模拟

doi: 10.13224/j.cnki.jasp.20230620

南京理工大学瞬态物理国家重点实验室，南京 210094

基金项目: 国家自然科学基金面上项目（12172177）

详细信息

作者简介:
聂嘉仪（2000-），女，硕士生，主要从事组合推进技术研究

通讯作者:
武郁文（1987-），男，副研究员，博士，主要从事爆轰推进技术研究。E-mail：y.wu@njust.edu.cn

中图分类号: V231.1
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- 被引次数: 0
出版历程
- 收稿日期: 2023-09-27
- 网络出版日期: 2025-02-11

Numerical study on interaction between rotating detonation backpressure and axial compressor

National Key Laboratory of Transient Physics，Nanjing University of Science and Technology，Nanjing 210094，China

摘要

摘要:
建立了旋转爆轰燃烧与跨声速轴流式压气机Stage 37耦合计算模型，分析旋转爆轰反压形成的前传压力波对压气机内部流场的影响，并探究反压传播速度对压气机工作性能的影响机制。结果表明：压力波传播的过程中相继与静转子的叶片相互作用，产生一系列激波，最终导致动叶前缘的附体激波在旋转爆轰反压作用下略微向上游推移。此外，旋转爆轰反压对静子通道的流场结构影响更为明显，相应地静子对前传压力波的抑制作用相对更强。相比于稳态设计点工况，当压气机出口存在以CJ速度（CJ为Chapman-Jouguet理论的爆轰波传播速度）传播的旋转爆轰反压时，压气机的效率可以提升1%，并且工作范围更宽广。
- 旋转爆轰反压 /
- 跨声速轴流压气机 /
- 压气机流场 /
- 压气机效率 /
- 附体激波
Abstract:
A coupled computational model of a transonic axial compressor and a rotating detonation combustor Stage 37 was constructed to investigate the impact of forward-propagating pressure waves generated by rotating backpressure on the internal flow field of the compressor. Furthermore, the effect of backpressure velocity on the compressor's performance was analyzed. It was observed that the forward-propagating wave interacted with both the stator and rotor blades, resulting in a slight upstream shift in the attached shockwave at the leading edge of the rotor blades due to the influence of the rotating backpressure. Moreover, the flow field structure of the stator was more significantly affected by rotational backpressure, and correspondingly, the forward pressure wave was relatively more strongly suppressed by the stator. In comparison with the peak efficiency point, the compressor’s performance was found that CJ velocity backpressure (CJ was the detonation propagation velocity in the Chapman-Jouguet theory) had a positive effect on the compressor’s efficiency, with an increase of 1% and wider operating range.
- rotating detonation backpressure /
- transonic axial compressor /
- compressor flow filed /
- compressor efficiency /
- attached shock wave

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图 1 Stage 37几何模型

Figure 1. Geometry of Stage 37

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图 2 计算域

Figure 2. Computational domain

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图 3 计算网格

Figure 3. Computational gird

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图 4 旋转爆轰反压时程曲线

Figure 4. Time history of rotating detonation backpressure

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图 5 50%叶高截面监测点分布

Figure 5. Monitor positions at 50% span

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图 6 Stage 37稳态性能曲线

Figure 6. Steady performance of NASA Stage 37

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图 7 不同叶高截面的相对马赫数云图

Figure 7. Contours of relative Mach number at different spans

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图 8 不同叶高截面的叶片表面静压曲线

Figure 8. Static pressure distribution of blade at different spans

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图 9 50%叶高截面压力前传期间的静压云图

Figure 9. Contours of static pressure at 50% span during forward propagation

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图 10 爆轰循环周期内监测点静压时程图

Figure 10. Time histories of static pressure at monitors in time cycle

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图 11 瞬态压比-流量比波动

Figure 11. Fluctuations of transient pressure ratio-flow rate

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表 1 Stage 37主要参数

Table 1. Stage 37 main parameters

参数	数值或说明
设计总压比	2.05
转子叶片数	36
静子叶片数	46
动叶展弦比	1.19
静叶展弦比	1.26
叶型	多圆弧叶型
设计转速/（r/min）	17811
设计质量流量/（kg/s）	20.188
设计等熵效率	0.84
轮毂比	0.7

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表 2 网格参数

Table 2. Parameter of grids

参数	数值
转子网格数/10⁶	1.7
静子网格数/10⁶	1.5
整体网格数/10⁶	3.2
第1层边界层厚度/mm	0.001

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表 3 网格无关性

Table 3. Grid independence

网格数量/10⁶	总压比	效率
2.5	1.989	0.841
3.2	1.990	0.843
3.9	1.991	0.845

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表 4 监测点最大压升

Table 4. Maximum pressure rise at monitors MPa

监测点	$ {p}_{i,\mathrm{s}\mathrm{t}\mathrm{e}\mathrm{a}\mathrm{d}\mathrm{y}} $	$ {p}_{i,\mathrm{m}\mathrm{a}\mathrm{x}} $	$ \Delta {p}_{i,\mathrm{m}\mathrm{a}\mathrm{x}} $
5	0.0748	0.0713	0.0035
7	0.1344	0.1513	0.0169
9	0.1365	0.1601	0.0236
10	0.1319	0.1428	0.0109
11	0.1490	0.1683	0.0193
13	0.1543	0.1754	0.0211
15	0.1500	0.2300	0.0800
17	0.1637	0.1963	0.0326
20	0.1009	0.1078	0.0069

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表 5 不同反压传播速度下压气机的工作性能

Table 5. Performance of compressor at different back pressure velocities

反压速度$ {V}_{\mathrm{r}\mathrm{d}\mathrm{e}} $	出口流量$ {\dot{m}}_{\mathrm{o}\mathrm{u}\mathrm{t}} $/（kg/s）	总压比$ \pi $	效率$ \eta $/%
稳态设计点	21.04	1.970	84.39
稳态近失速点	20.98	2.005	84.01
0.5CJ	21.03	1.992	84.73
0.75CJ	21.01	1.999	84.85
1CJ	20.96	2.007	85.38

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参考文献(41)

[1]	ZHU Yiyuan,WANG Ke,WANG Zhicheng,et al. Study on the performance of a rotating detonation chamber with different aerospike nozzles[J]. Aerospace Science and Technology,2020,107: 106338. doi: 10.1016/j.ast.2020.106338
[2]	王超,刘卫东,刘世杰,等. 高总温来流下的连续旋转爆震验证试验[J]. 推进技术,2016,37(3): 578-584. WANG Chao,LIU Weidong,LIU Shijie,et al. Validating experiment of continuous rotating detonation under high total temperature air[J]. Journal of Propulsion Technology,2016,37(3): 578-584. (in Chinese WANG Chao, LIU Weidong, LIU Shijie, et al. Validating experiment of continuous rotating detonation under high total temperature air[J]. Journal of Propulsion Technology, 2016, 37(3): 578-584. (in Chinese)
[3]	WOLAŃSKI P. Detonative propulsion[J]. Proceedings of the Combustion Institute,2013,34(1): 125-158. doi: 10.1016/j.proci.2012.10.005
[4]	MA J Z,LUAN Mingyi,XIA Zhijie,et al. Recent progress,development trends,and consideration of continuous detonation engines[J]. AIAA Journal,2020,58(12): 4976-5035. doi: 10.2514/1.J058157
[5]	WANG Guangyu,LIU Weidong,LIU Shijie,et al. Experimental verification of cylindrical air-breathing continuous rotating detonation engine fueled by non-premixed ethylene[J]. Acta Astronautica,2021,189: 722-732. doi: 10.1016/j.actaastro.2021.09.009
[6]	王健平,周蕊,武丹. 连续旋转爆轰发动机的研究进展[J]. 实验流体力学,2015,29(4): 12-25. WANG Jianping,ZHOU Rui,WU Dan. Progress of continuously rotating detonation engine research[J]. Journal of Experiments in Fluid Mechanics,2015,29(4): 12-25. (in Chinese doi: 10.11729/syltlx20150048 WANG Jianping, ZHOU Rui, WU Dan. Progress of continuously rotating detonation engine research[J]. Journal of Experiments in Fluid Mechanics, 2015, 29(4): 12-25. (in Chinese) doi: 10.11729/syltlx20150048
[7]	BYKOVSKII F A,ZHDAN S A,VEDERNIKOV E F. Continuous spin detonations[J]. Journal of Propulsion and Power,2006,22(6): 1204-1216. doi: 10.2514/1.17656
[8]	FROLOV S M,DUBROVSKII A V,IVANOV V S. Three-dimensional numerical simulation of a continuously rotating detonation in the annular combustion chamber with a wide gap and separate delivery of fuel and oxidizer[J]. Progress in Propulsion Physics,2016,8: 375-388.
[9]	SOUSA J,PANIAGUA G,COLLADO MORATA E. Thermodynamic analysis of a gas turbine engine with a rotating detonation combustor[J]. Applied Energy,2017,195: 247-256. doi: 10.1016/j.apenergy.2017.03.045
[10]	MIZENER A R,LU F K. Low-order parametric analysis of a rotating detonation engine in rocket mode[J]. Journal of Propulsion and Power,2017,33(6): 1543-1554. doi: 10.2514/1.B36432
[11]	JI Zifei,ZHANG Huiqiang,WANG Bing. Performance analysis of dual-duct rotating detonation aero-turbine engine[J]. Aerospace Science and Technology,2019,92: 806-819. doi: 10.1016/j.ast.2019.07.011
[12]	WOLAŃSKI P. Application of the continuous rotating detonation to gas turbine[J]. Applied Mechanics and Materials,2015,782: 3-12. doi: 10.4028/www.scientific.net/AMM.782.3
[13]	ISHIYAMA C,MIYAZAKI K,NAKAGAMI S,et al. Experimental study of research of centrifugal-compressor-radial-turbine type rotating detonation engine[R]. AIAA-2016-5103,2016.
[14]	HIGASHI J,NAKAGAMI S,MATSUOKA K,et al. Experimental study of the disk-shaped rotating detonation turbine engine[R]. AIAA-2017-1286,2017.
[15]	RHEE H,ISHIYAMA C,HIGASHI J,et al. Experimental study on a rotating detonation turbine engine with an axial turbine[R]. Boston,US: 26th International Colloquium on the Dynamics of Explosions and Reactive Systems,2017.
[16]	ZHOU Shengbing,MA Hu,LI Shuai,et al. Effects of a turbine guide vane on hydrogen-air rotating detonation wave propagation characteristics[J]. International Journal of Hydrogen Energy,2017,42(31): 20297-20305. doi: 10.1016/j.ijhydene.2017.06.115
[17]	ZHOU Shengbing,MA Hu,YANG Yuchen,et al. Investigation on propagation characteristics of rotating detonation wave in a radial-flow turbine engine combustor model[J]. Acta Astronautica,2019,160: 15-24. doi: 10.1016/j.actaastro.2019.04.022
[18]	BAKHTIARI F,SCHIFFER H P. Numerical approach to the modelling of transient interaction of prospective combustor concepts and conventional high pressure turbines[J]. Propulsion and Power Research,2019,8(1): 1-12. doi: 10.1016/j.jppr.2019.01.008
[19]	LIU Zhe,BRAUN J,PANIAGUA G. Three dimensional optimization for subsonic axial turbines operating at high unsteady inlet Mach number[R]. AIAA-2018-4480,2018.
[20]	LIU Z,BRAUN J,PANIAGUA G. Characterization of a supersonic turbine downstream of a rotating detonation combustor[J]. Journal of Engineering for Gas Turbines and Power,2019,141(3): 031501. doi: 10.1115/1.4040815
[21]	WU Yuwen,WENG Chunsheng,ZHENG Quan,et al. Experimental research on the performance of a rotating detonation combustor with a turbine guide vane[J]. Energy,2021,218: 119580. doi: 10.1016/j.energy.2020.119580
[22]	李群,武郁文,翁春生,等. 旋转爆轰波与涡轮平面叶栅相互作用数值模拟[J]. 推进技术,2022,43(9): 210323. LI Qun,WU Yuwen,WENG Chunsheng,et al. Numerical simulation of interaction between rotating detonation wave and turbine plane cascade[J]. Journal of Propulsion Technology,2022,43(9): 210323. (in Chinese LI Qun, WU Yuwen, WENG Chunsheng, et al. Numerical simulation of interaction between rotating detonation wave and turbine plane cascade[J]. Journal of Propulsion Technology, 2022, 43(9): 210323. (in Chinese)
[23]	王凌羿,郑龙席,贾胜锡. 离心压气机与脉冲爆震燃烧室共同工作分析[J]. 航空动力学报,2020,35(4): 704-710. WANG Lingyi,ZHENG Longxi,JIA Shengxi. Analysis on interaction between centrifugal compressor and pulse detonation combustor[J]. Journal of Aerospace Power,2020,35(4): 704-710. (in Chinese WANG Lingyi, ZHENG Longxi, JIA Shengxi. Analysis on interaction between centrifugal compressor and pulse detonation combustor[J]. Journal of Aerospace Power, 2020, 35(4): 704-710. (in Chinese)
[24]	MARELLI S,CAPOBIANCO M,ZAMBONI G. Pulsating flow performance of a turbocharger compressor for automotive application[J]. International Journal of Heat and Fluid Flow,2014,45: 158-165. doi: 10.1016/j.ijheatfluidflow.2013.11.001
[25]	MARELLI S,CAPOBIANCO M. Experimental investigation under unsteady flow conditions on turbocharger compressors for automotive gasoline engines[M]//10th International Conference on Turbochargers and Turbocharging. Amsterdam,Netherlands: Elsevier,2012: 219-229.
[26]	BARRERA-MEDRANO M E,MARTINEZ-BOTAS R,TOMITA I,et al. On the effect of engine pulsations on the performance of a turbocharger centrifugal compressor[J]. Journal of Engineering for Gas Turbines and Power,2019,141(8): 081001. doi: 10.1115/1.4042609
[27]	BARRERA-MEDRANO M E,NEWTON P,MARTINEZ-BOTAS R,et al. Effect of exit pressure pulsation on the performance and stability limit of a turbocharger centrifugal compressor[J]. Journal of Engineering for Gas Turbines and Power,2017,139(5): 052601. doi: 10.1115/1.4034689
[28]	BENSON R S,WHITFIELD A. An experimental investigation of the non-steady flow characteristics of a centrifugal compressor[J]. Proceedings of the Institution of Mechanical Engineers,1965,180(1): 641-672. doi: 10.1243/PIME_PROC_1965_180_043_02
[29]	GALINDO J,CLIMENT H,GUARDIOLA C,et al. On the effect of pulsating flow on surge margin of small centrifugal compressors for automotive engines[J]. Experimental Thermal and Fluid Science,2009,33(8): 1163-1171. doi: 10.1016/j.expthermflusci.2009.07.006
[30]	SHU M Y,YANG M Y,ZHANG K Y,et al. Experimental study on centrifugal compressor performance at pulsating backpressure conditions[R]. Phoenix,US: ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition,2019.
[31]	舒梦影,杨名洋,王兴宸,等. 脉动背压离心压气机动态特性及稳定性[J]. 航空动力学报,2022,37(8): 1740-1748. SHU Mengying,YANG Mingyang,WANG Xingchen,et al. Compressor transient responses and stability at pulsating backpressure conditions[J]. Journal of Aerospace Power,2022,37(8): 1740-1748. (in Chinese SHU Mengying, YANG Mingyang, WANG Xingchen, et al. Compressor transient responses and stability at pulsating backpressure conditions[J]. Journal of Aerospace Power, 2022, 37(8): 1740-1748. (in Chinese)
[32]	WANG Zhiwu,YANG Yuxuan,HUANG Jingjing,et al. Effect of back-propagation pressure on axial flow compressor in a pulse detonation turbine engine[J]. Aerospace Science and Technology,2023,141: 108525. doi: 10.1016/j.ast.2023.108525
[33]	WANG Zhiwu,WANG Yafei,HUANG Jingjing,et al. Back-propagation suppression study based on intake configuration optimization for an air-breathing pulse detonation engine[J]. Aerospace Science and Technology,2021,118: 107042. doi: 10.1016/j.ast.2021.107042
[34]	SARACOGLU B H,PANIAGUA G. Compressor integration study for a pulse detonation engine[R]. AIAA-2016-0397,2016.
[35]	胡骏. 航空叶片机原理[M]. 2版. 北京: 国防工业出版社,2014.
[36]	VUONG T D,KIM K Y. Stability enhancement of a single-stage transonic axial compressor using inclined oblique slots[J]. Energies,2021,14(9): 2346. doi: 10.3390/en14092346
[37]	REID L,MOORE R D. Design and overall performance of four highly loaded,high speed inlet stages for an advanced high-pressure-ratio core compressor[R]. Washington,US: NASA Technical Reports Server,1978.
[38]	魏万里,郑权,鲁江涛,等. 中心锥对液态燃料旋转爆轰发动机工作过程与性能的影响[J]. 兵工学报,2021,42(6): 1185-1194. WEI Wanli,ZHENG Quan,LU Jiangtao,et al. Effect of central cone on working process and performance of liquid-fueled rotating detonation engine[J]. Acta Armamentarii,2021,42(6): 1185-1194. (in Chinese doi: 10.3969/j.issn.1000-1093.2021.06.008 WEI Wanli, ZHENG Quan, LU Jiangtao, et al. Effect of central cone on working process and performance of liquid-fueled rotating detonation engine[J]. Acta Armamentarii, 2021, 42(6): 1185-1194. (in Chinese) doi: 10.3969/j.issn.1000-1093.2021.06.008
[39]	郑权,李宝星,翁春生,等. 燃烧室长度对液态燃料旋转爆轰发动机性能影响实验研究[J]. 推进技术,2018,39(12): 2764-2771. ZHENG Quan,LI Baoxing,WENG Chunsheng,et al. Experimental investigation for effects of combustor length on liquid-fueled rotating detonation engine performance[J]. Journal of Propulsion Technology,2018,39(12): 2764-2771. (in Chinese ZHENG Quan, LI Baoxing, WENG Chunsheng, et al. Experimental investigation for effects of combustor length on liquid-fueled rotating detonation engine performance[J]. Journal of Propulsion Technology, 2018, 39(12): 2764-2771. (in Chinese)
[40]	潘锦珊. 气体动力学基础[M]. 北京: 国防工业出版社,1989.
[41]	SURESH A,HOFER D,TANGIRALA V. Turbine efficiency for unsteady periodic flows[R]. AIAA-2009-0504,2009.