Abstract
To investigate the impact of combustor width on continuous rotating detonation (CRD) fueled by ethylene and air, a series of 3D simulations are conducted by changing the inner cylinder radius of an annular combustor while retaining the same outer cylinder radius. The results show that the CRD wave propagates more steadily and faster as the combustor width increases. The high-temperature zone at the backward-facing step preheats the propellants and contributes to the steady propagation of the CRD wave in 25- and 30-mm wide combustors. The highest and the lowest velocities are obtained in the 30- and 15-mm wide combustors at, respectively, 1880.27 and 1681.01 m/s. On the other hand, the average thrust decreases as the combustor width increases. The highest thrust is obtained in the 15-mm wide combustor while the lowest is in the 30-mm wide combustor, at 758.06 and 525.93 N, respectively. Nevertheless, the thrust is much more stable in the 25- and 30-mm wide combustors than in the 15- and 20-mm wide combustors.
摘要
目的
揭示燃烧室宽度对乙烯-空气爆震波传播特性的影响,分析爆震波流场特征和燃烧室宽度对发动机推进性能的影响,为实现稳定的碳氢燃料连续旋转爆震和高效的发动机推进性能提供一些燃烧室设计思路。
创新点
1. 采用三维数值仿真,验证了燃烧室头部后向台阶高温回流区对新鲜可燃气的预加热作用;2. 揭示了燃烧室宽度对发动机推力性能的影响。
方法
1. 通过三维数值仿真,对爆震波传播过程的瞬时压力监测曲线和流场温度云图进行分析,明晰爆震波在不同宽度燃烧室内的模态转换过程;2.对流场的温度、压力和组分分布云图及燃料的沿程分布情况进行分析,获得不同宽度燃烧室内的爆震波流场特征,揭示燃烧室宽度对爆震波传播稳定性的影响;3. 对推力监测曲线、轴向速度和压力的沿程分布情况进行分析,揭示燃烧室宽度对发动机推力性能的影响。
结论
1. 随着环形燃烧室宽度的增大,爆震波传播过程的稳定性显著提高,爆震波的传播速度明显增大;2. 在较宽的环形燃烧室头部形成的高温回流区对新鲜混合气的预加热作用有利于爆震波的稳定传播;3. 随着环形燃烧室宽度的增大,发动机的推力下降但推力的稳定性提高;4. 带凹腔的环形燃烧室有望获得稳定且高效的推进性能。
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
Anand V, George AS, de Luzan CF, et al., 2018. Rotating detonation wave mechanics through ethylene-air mixtures in hollow combustors, and implications to high frequency combustion instabilities. Experimental Thermal and Fluid Science, 92:314–325. https://doi.org/10.1016/j.expthermflusci.2017.12.004
Andrus IQ, Polanka MD, King PI, et al., 2017. Experimentation of premixed rotating detonation engine using variable slot feed plenum. Journal of Propulsion and Power, 33(6):1448–1458. https://doi.org/10.2514/1,B36261
Baurle RA, Mathur T, Gruber MR, et al., 1998. A numerical and experimental investigation of a scramjet combustor for hypersonic missile applications. Proceedings of the 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, p.1–17. https://doi.org/10.2514/6.1998-3121
Bykovskii FA, Vedernikov EF, 1996. Self-sustaining pulsating detonation of gas-mixture flow. Combustion, Explosion and Shock Waves, 32(4):442–448. https://doi.org/10.1007/BF01998496
Bykovskii FA, Zhdan SA, Vedernikov EF, 2006a. Continuous spin detonation of fuel-air mixtures. Combustion, Explosion and Shock Waves, 42(4):463–471. https://doi.org/10.1007/s10573-006-0076-9
Bykovskii FA, Zhdan SA, Vedernikov EF, 2006b. Continuous spin detonations. Journal of Propulsion and Power, 22(6): 1204–1216. https://doi.org/10.2514/1.17656
Bykovskii FA, Vedernikov EF, Polozov SV, et al., 2007. Initiation of detonation in flows of fuel-air mixtures. Combustion, Explosion, and Shock Waves, 43(3):345–354. https://doi.org/10.1007/s10573-007-0048-8
Cho KY, Codoni JR, Rankin BA, et al., 2016. High-repetition-rate chemiluminescence imaging of a rotating detonation engine. Proceedings of the 54th AIAA Aerospace Sciences Meeting, p.1–13. https://doi.org/10.2514/6.2016-1648
Fan WJ, Zhou J, Liu SJ, et al., 2021. Effects of the geometrical parameters of the injection nozzle on ethylene-air continuous rotating detonation. Journal of Zhejiang University-SCIENCE A (Applied Physics & Engineering), 22(7): 547–563. https://doi.org/10.1631/jzus.A2000314
Fang YS, Hu ZM, Teng HH, et al., 2017. Numerical study of inflow equivalence ratio inhomogeneity on oblique detonation formation in hydrogen—air mixtures. Aerospace Science and Technology, 71:256–263. https://doi.org/10.1016/j.ast.2017.09.027
Fujii J, Kumazawa Y, Matsuo A, et al., 2017. Numerical investigation on detonation velocity in rotating detonation engine chamber. Proceedings of the Combustion Institute, 36(2):2665–2672. https://doi.org/10.1016/j.proci.2016.06.155
George AS, Driscoll RB, Anand V, et al., 2015. Fuel blending as a means to achieve initiation in a rotating detonation engine. Proceedings of the 53rd AIAA Aerospace Sciences Meeting, p.1–18. https://doi.org/10.2514/6.2015-0633
Gottiparthi KC, Génin F, Srinivasan S, et al., 2009. Simulation of cellular detonation structures in ethylene-oxygen mixtures. Proceedings of the 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, p.1–13. https://doi.org/10.2514/6.2009-437
Hsu PS, Slipchenko MN, Jiang NB, et al., 2020. Megahertzrate OH planar laser-induced fluorescence imaging in a rotating detonation combustor. Optics Letters, 45(20): 5776–5779. https://doi.org/10.1364/OL.403199
Kawasaki A, Inakawa T, Kasahara J, et al., 2019. Critical condition of inner cylinder radius for sustaining rotating detonation waves in rotating detonation engine thruster. Proceedings of the Combustion Institute, 37(3):3461–3469. https://doi.org/10.1016/j.proci.2018.07.070
Khokhlov AM, Austin JM, Pintgen F, et al., 2004. Numerical study of the detonation wave structure in ethylene-oxygen mixtures. Proceedings of the 42nd AIAA Aerospace Sciences Meeting and Exhibit, p.2–7. https://doi.org/10.2514/6.2004-792
Kindracki J, 2015. Experimental research on rotating detonation in liquid fuel—gaseous air mixtures. Aerospace Science and Technology, 43:445–453. https://doi.org/10.1016/j.ast.2015.04.006
Le Naour B, Falempin F, Coulon K, 2017. MBDA R&T effort regarding continuous detonation wave engine for propulsion-status in 2016. Proceedings of the 21st AIAA International Space Planes and Hypersonics Technologies Conference, p.1–8. https://doi.org/10.2514/6.2017-2325
Lin W, Zhou J, Liu SJ, et al., 2015. Experimental study on propagation mode of H2/air continuously rotating detonation wave. International Journal of Hydrogen Energy, 40(4):1980–1993. https://doi.org/10.1016/j.ijhydene.2014.11.119
Liu SJ, Lin ZY, Liu WD, et al., 2013. Experimental and three-dimensional numerical investigations on H2/air continuous rotating detonation wave. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 227(2):326–341. https://doi.org/10.1177/0954410011433542
Liu SJ, Liu WD, Lin ZY, et al., 2015. Experimental research on the propagation characteristics of continuous rotating detonation wave near the operating boundary. Combustion Science and Technology, 187(11):1790–1804. https://doi.org/10.1080/00102202.2015.1019620
Liu SJ, Peng HY, Liu WD, et al., 2020. Effects of cavity depth on the ethylene-air continuous rotating detonation. Acta Astronautica, 166:1–10. https://doi.org/10.1016/j.actaastro.2019.09.038
Nikitin VF, Dushin VR, Phylippov YG, et al., 2009. Pulse detonation engines: technical approaches. Acta Astronautica, 64(2–3):281–287. https://doi.org/10.1016/j.actaastro.2008.08.002
Peng HY, Liu WD, Liu SJ, et al., 2018. Experimental investigations on ethylene-air continuous rotating detonation wave in the hollow chamber with Laval nozzle. Acta Astronautica, 151:137–145. https://doi.org/10.1016/j.actaastro.2018.06.025
Peng HY, Liu WD, Liu SJ, et al., 2019a. The effect of cavity on ethylene-air continuous rotating detonation in the annular combustor. International Journal of Hydrogen Energy, 44(26):14032–14043. https://doi.org/10.1016/j.ijhydene.2019.04.017
Peng HY, Liu WD, Liu SJ, 2019b. Ethylene continuous rotating detonation in optically accessible racetrack-like combustor. Combustion Science and Technology, 191(4):676–695. https://doi.org/10.1080/00102202.2018.1498850
Peng HY, Liu WD, Liu SJ, et al., 2021. Effects of cavity location on ethylene—air continuous rotating detonation in a cavity-based annular combustor. Combustion Science and Technology, 193(16):2761–2782. https://doi.org/10.1080/00102202.2020.1760255
Schwer D, Kailasanath K, 2013. Fluid dynamics of rotating detonation engines with hydrogen and hydrocarbon fuels. Proceedings of the Combustion Institute, 34(2):1991–1998. https://doi.org/10.1016/j.proci.2012.05.046
Schwer DA, Kailasanath K, 2012. Feedback into mixture plenums in rotating detonation engines. Proceedings of the 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, p.1–17. https://doi.org/10.2514/6.2012-617
Stewart DS, Kasimov AR, 2006. State of detonation stability theory and its application to propulsion. Journal of Propulsion and Power, 22(6):1230–1244. https://doi.org/10.2514/1.21586
Sun J, Zhou J, Liu SJ, et al., 2017. Effects of injection nozzle exit width on rotating detonation engine. Acta Astronautica, 140:388–401. https://doi.org/10.1016/j.actaastro.2017.09.008
Sun J, Zhou J, Liu SJ, et al., 2018a. Numerical investigation of a rotating detonation engine under premixed/non-premixed conditions. Acta Astronautica, 152:630–638. https://doi.org/10.1016/j.actaastro.2018.09.012
Sun J, Zhou J, Liu SJ, et al., 2018b. Plume flowfield and propulsive performance analysis of a rotating detonation engine. Aerospace Science and Technology, 81:383–393. https://doi.org/10.1016/j.ast.2018.08.024
Sun J, Zhou J, Liu SJ, et al., 2019. Interaction between rotating detonation wave propagation and reactant mixing. Acta Astronautica, 164:197–203. https://doi.org/10.1016/j.actaastro.2019.08.010
Tang XM, Wang JP, Shao YT, 2015. Three-dimensional numerical investigations of the rotating detonation engine with a hollow combustor. Combustion and Flame, 162(4): 997–1008. https://doi.org/10.1016/j.combustflame.2014.09.023
Wang YH, Le JL, Wang C, et al., 2018. A non-premixed rotating detonation engine using ethylene and air. Applied Thermal Engineering, 137:749–757. https://doi.org/10.1016/j.applthermaleng.2018.04.015
Wilhite J, Driscoll R, George AS, et al., 2016. Investigation of a rotating detonation engine using ethylene-air mixtures. Proceedings of the 54th AIAA Aerospace Sciences Meeting, p.1–7. https://doi.org/10.2514/6.2016-1650
Yang CL, Wu XS, Ma H, et al., 2016. Experimental research on initiation characteristics of a rotating detonation engine. Experimental Thermal and Fluid Science, 71:154–163. https://doi.org/10.1016/j.expthermflusci.2015.10.019
Yao SB, Tang XM, Wang JP, 2017. Numerical study of the propulsive performance of the hollow rotating detonation engine with a Laval nozzle. International Journal of Turbo & Jet-Engines, 34(1):49–54. https://doi.org/10.1515/tjj-2015-0052
Yi TH, Lou J, Turangan C, et al., 2011. Propulsive performance of a continuously rotating detonation engine. Journal of Propulsion and Power, 27(1): 171–181. https://doi.org/10.2514/1.46686
Yungster S, Radhakrishnan K, 2005. Structure and stability of one-dimensional detonations in ethylene-air mixtures. Shock Waves, 14(1):61–72. https://doi.org/10.1007/s00193-005-0242-0
Acknowledgments
This work is supported by the National Natural Science Foundation of China (No. 51776220) and the Postgraduate Scientific Research Innovation Project of Hunan Province, China.
Author information
Authors and Affiliations
Corresponding authors
Additional information
Author contributions
Wei-dong LIU and Hao-yang PENG designed this numerical study. Wei-jie FAN carried out the simulations and analyzed the results under their guidance. Shi-jie LIU and Jian SUN provided important suggestions on the improvement of the simulations. All authors reviewed and revised the manuscript carefully and approved the content of the manuscript.
Conflict of interest
Wei-jie FAN, Wei-dong LIU, Hao-yang PENG, Shi-jie LIU, and Jian SUN declare that they have no conflict of interest.
Rights and permissions
About this article
Cite this article
Fan, Wj., Liu, Wd., Peng, Hy. et al. Numerical study on ethylene-air continuous rotating detonation in annular combustors with different widths. J. Zhejiang Univ. Sci. A 23, 388–404 (2022). https://doi.org/10.1631/jzus.A2100448
Received:
Accepted:
Published:
Issue Date:
DOI: https://doi.org/10.1631/jzus.A2100448
Key words
- Continuous rotating detonation (CRD)
- Ethylene-air
- Combustor width
- Propagation mode
- Propulsive performance