Numerical Investigation on Unsteady Flow of Nozzle in Rotating Detonation Engine

doi:10.13675/j.cnki.tjjs.190721

Journal of Propulsion Technology ›› 2021, Vol. 42 ›› Issue (6): 1213-1222.DOI: 10.13675/j.cnki.tjjs.190721

• Aero-thermodynamics • Previous Articles Next Articles

Numerical Investigation on Unsteady Flow of Nozzle in Rotating Detonation Engine

1.School of Aerospace Engineering，Xiamen University，Xiamen 361102，China;2.State Key Laboratory of Laser Propulsion and Application，Beijing Power Machinery Institute，Beijing 100074，China

Online:2021-06-15 Published:2021-08-15

旋转爆震发动机喷管非定常流动特性的数值模拟研究

夏寒青¹，黄玥¹，张义宁²，尤延铖¹，李冬²，栾振业¹

1.厦门大学航空航天学院，福建厦门 361102;2.北京动力机械研究所激光推进及其应用国家重点实验室，北京 100074

作者简介:夏寒青，硕士生，研究领域为爆震喷管。E-mail：2291805863@qq.com
基金资助:
国家自然科学基金（51876182）；中央高校基本科研业务费（20720180058）；航空动力基金（6141B090325）。

Abstract

Abstract: To analyse the unsteady flow characteristics in the rotating detonation nozzle， a plug nozzle model is designed based on the characteristics method and time-average parameters of the rotating detonation combustor outlet. By changing the inlet/outlet pressure ratio of the plug nozzle （pressure ratios of 15， 30 and 45 respectively）， the relationship between the unsteady nozzle flow field and the performance of the nozzle is analyzed， and the effects of pressure ratio variation on the nozzle performance are investigated. The results show that after the oblique shock wave from the downstream of the rotating detonation combustor enters the nozzle， a spiral shock wave is spirally distributed around the plug nozzle wall， and the shock wave structure is mainly determined by the airflow angle and airflow velocity of shock wave front. According to the distribution of the spiral shock wave along with the plug nozzle， the working state of the detonation nozzle can be divided into four phases， such as free expansion phase， under-expansion phase， under-expansion to over-expansion transition phase， and over-expansion phase. The shock wave appears in the nozzle during the second stage （under-expansion）， and the strength increases with the propagation of the shock wave， reaching the maximum at the fourth stage （the nozzle is at the over-expanded state）. The nozzle performance is deteriorates during the second to fourth stages. The nozzle performance at a lower pressure ratio of 15 is higher than that at the high-pressure ratio of 30 and its peak thrust and fuel specific impulse are 992.05N and 1769.52s， respectively. Therefore， a higher inlet/outlet pressure ratio should be selected as a design point for the rotating detonation nozzle， consequently， the nozzle could work under a low-pressure ratio at more time to improve the efficiency of the nozzle.

Key words: Rotating detonation;Plug nozzle;Pressure ratio;Shock wave;Nozzle performance

摘要： 为分析旋转爆震喷管内非定常流动特性，基于特征线方法和旋转爆震燃烧室出口时均参数设计了一种塞式喷管模型，通过改变塞锥式喷管的进出口压比π（π=15，30，45），分析了喷管内非定常流场结构与喷管工作性能之间的相互关系，并探究了喷管进出口压比变化对喷管工作性能的影响。研究结果表明：旋转爆震燃烧室下游斜激波进入喷管后，在喷管内形成一道绕喷管壁面螺旋分布的激波，激波结构主要由波前气流角和激波前气流速度决定；爆震喷管局部工作状态依据相对螺旋激波位置分别存在自由膨胀状态、欠膨胀状态、欠膨胀与过膨胀过渡状态以及过膨胀状态四种情况，并随着激波的传播不断增强，在第四种工作状态达到最大（喷管处于过膨胀状态），且喷管在第二到第四种工作状态内工作性能变差；在低压比（π=15）工作条件下喷管性能优于高压比（π=30）工作条件下喷管性能，其最佳推力和燃料比冲分别为992.05N和1769.52s，因而旋转爆震喷管设计应选择较高的进出口压比作为设计点，使旋转爆震喷管更多的工作在低压比工作状态，以提高旋转爆震喷管工作效率。

关键词: 旋转爆震;塞锥式喷管;压比;激波;喷管性能

XIA Han-qing¹, HUANG Yue¹, ZHANG Yi-ning², YOU Yan-cheng¹, LI Dong², LUAN Zhen-ye¹. Numerical Investigation on Unsteady Flow of Nozzle in Rotating Detonation Engine[J]. Journal of Propulsion Technology, 2021, 42(6): 1213-1222.

夏寒青，黄玥，张义宁，尤延铖，李冬，栾振业. 旋转爆震发动机喷管非定常流动特性的数值模拟研究[J]. 推进技术, 2021, 42(6): 1213-1222.

References

[1] 马虎，武晓松，王栋，等. 旋转爆震发动机数值研究［J］. 推进技术， 2012， 33（5）.
[2] 刘世杰，林志勇，孙明波，等. 旋转爆震波发动机二维数值模拟［J］. 推进技术， 2010， 31（5）： 634-640.
[3] Voitsekhovskii B V. Maintained Detonations［J］. Soviet Physics Doklady， 1959， 9（6）：1254-1256 .
[4] Cullen R E， Nicholls J A， Ragland K W. Feasibility Studies of a Rotating Detonation Wave Rocket Motor［J］. Journal of Spacecraft and Rockets， 1966， 3（6）： 893-898.
[5] Lu F K， Braun E M. Rotating Detonation Wave Propulsion： Experimental Challenges， Modeling， and Engine Concepts［J］. Journal of Propulsion and Power， 2011， 30（5）： 1-18.
[6] Driscoll R， Aghasi P， George A S， et al. Three-Dimensional Numerical Investigation of Reactant Injection Variation in a H₂/Air Rotating Detonation Engine［J］. International Journal of Hydrogen Energy， 2016， 41（9）：5162-5175.
[7] Driscoll R， George A S， Gutmark E J. Numerical Investigation of Injection Within Axisymmetric Rotating Detonation Engine［J］. International Journal of Hydrogen Energy， 2016， 41（3）： 2052-2063.
[8] Sousa J， Paniagua G， Morata E C. Thermodynamic Analysis of a Gas Turbine Engine with a Rotating Detonation Combustor［J］. Applied Energy， 2017， 195： 247-256.
[9] Yao S， Tang X， Luan M， et al. Numerical Study of Hollow Rotating Detonation Engine with Different Fuel Injection Area Ratios［J］. Proceedings of the Combustion Institute， 2017， 36（2）： 2649-2655.
[10] Xu X Y. Numerical Simulation of Injection Schemes with Separate Supply of Fuel and Oxidizer Effects on Rotating Detonation Engine［J］. Acta Aeronautica ET Astronautica Sinica， 2016， 37（4）： 1184-1195.
[11] Braun J， Garcia J S， Paniagua G. Evaluation of the Unsteadiness Across Nozzles Downstream of Rotating Detonation Combustors［R］. AIAA 2017-1063.
[12] Fujii J， Kumazawa Y， Matsuo A， et al. Numerical Investigation on Detonation Velocity in Rotating Detonation Engine Chamber［J］. Proceedings of the Combustion Institute， 2016， 155（6）：1540-7489.
[13] 郑榆山，王超，王宇辉，等. 旋转爆震三维非预混混合特性及流场结构研究［J］. 推进技术， 2019， 40（2）： 407-415.
[14] 高剑，马虎，裴晨曦，等. 喷管对旋转爆震发动机性能影响的实验［J］. 航空动力学报， 2016， 31（10）： 2443-2453.
[15] Yi T H， Lou J， Turangan C， et al. Effect of Nozzle Shapes on the Performance of Continuously-Rotating Detonation Engine［R］. AIAA 2010-152.
[16] Rankin B A， Hoke J， Schauer F. Periodic Exhaust Flow Through a Converging-Diverging Nozzle Downstream of a Rotating Detonation Engine［R］. AIAA 2014-1015.
[17] Eto S， Tsuboi N， Takayuki K， et al. Three-Dimensional Numerical Simulation of a Rotating Detonation Engine： Effects of the Throat of a Converging-Diverging Nozzle on Engine Performance［J］. Combustion Science and Technology， 2016， 188（11-12）： 2105-2116.
[18] Braun J， Saracoglu B H， Paniagua G. Unsteady Performance of Rotating Detonation Engines with Different Exhaust Nozzles［J］. Journal of Propulsion and Power， 2016， 36（2）： 2665-2672.
[19] Jourdaine N ， Tsuboi N ， Ozawa K ， et al. Three-Dimensional Numerical Thrust Performance Analysis of Hydrogen Fuel Mixture Rotating Detonation Engine with Aerospike Nozzle［J］. Proceedings of the Combustion Institute， 2019， 37（3）： 3443-3451.
[20] Kindracki J， Wolański P， Gut Z. Experimental Research on the Rotating Detonation in Gaseous Fuels-Oxygen Mixtures ［J］. Shock Waves， 2011， 21（2）： 75-84.
[21] Fotia M L， Schauer F， Kaemming T， et al. Experimental Study of the Performance of a Rotating Detonation Engine with Nozzle［J］. Journal of Propulsion and Power， 2015， 32（3）： 674-681.
[22] Kato Y， Ishihara K， Matsuoka K， et al. Study of Combustion Chamber Characteristic Length in Rotating Detonation Engine with Convergent-Divergent Nozzle［R］. AIAA 2016-1406.
[23] Hishida M， Fujiwara T， Wolanski P. Fundamentals of Rotating Detonations［J］. Shock Waves， 2009， 19（1）.
[24] Jiang P， Liao Z， Huang Z， et al. Influence of Shock Waves on Supersonic Transpiration Cooling［J］. International Journal of Heat and Mass Transfer， 2019， 129：965-974.

Numerical Investigation on Unsteady Flow of Nozzle in Rotating Detonation Engine

旋转爆震发动机喷管非定常流动特性的数值模拟研究

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