Pressurization Characteristics and Flow Field Analysis of Methane/Oxygen Rotating Detonation Combustor at High Temperature and High Pressure Inlets

被引：0
|
作者：
Sun Z.-P. [1 ]
Huang Y. [1 ]
Luan Z.-Y. [1 ]
Gao S.-J. [1 ]
You Y.-C. [1 ]
机构：
[1] School of Aerospace Engineering, Xiamen University, Xiamen
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2022年 / 43卷 / 11期
关键词：
Numerical simulation; Pressure gain; Rotating detonation combustor; Theoretical analysis; Thrust;
D O I：
10.13675/j.cnki.tjjs.210751
中图分类号：
学科分类号：
摘要：
In order to establish an analysis model of rotating detonation pressurization ratio and engine performance，and analyze the pressurization ratio and propulsion performance of rotating detonation combustor under different flow conditions ，the flow characteristics of a rotating detonation combustor under different incoming flow conditions were simulated by using the Navier-Stokes equation of two-dimensional viscous unsteady reaction，and the stable propagation and pressurization characteristics of detonation wave under high incoming flow temperature and pressure were obtained.Theoretical analysis shows that the pressurization ratio of the combustor is determined by the total inlet temperature，the temperature rise of the combustor and the absolute Mach number of the wavefront reactants. When the inlet pressure is given，the unit thrust is also determined by these three parameters. Numerical simulation verifies the pressurization characteristics obtained from theoretical analysis，and obtains the detailed flow field structure of initiation and stable propagation of rotating detonation wave under high temperature and high pressure flow conditions. When the injection pressure is constant，the absolute Mach number in front of detonation wave decreases slowly with little change as the total inlet temperature rises，and the total outlet temperature of combustion chamber is almost constant，that is，the pressurization ratio and thrust performance of combustion chamber are mainly affected by the total inlet temperature. When the total inlet temperature increases，the fuel mass flow decreases gradually，the detonation wave intensity decreases significantly，and the pressurization ratio and unit thrust decrease logarithmically. © 2022 Journal of Propulsion Technology. All rights reserved.
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  • [1] Ma J Z，, Luan M Y，, Xia Z J，, Et al., Recent Progress，Development Trends，and Consideration of Continuous Detonation Engines［J］, AIAA Journal, 58, 12, pp. 4976-5035, (2020)
  • [2] Fotia M，, Schauer F，, Hoke J., Experimental Study of Performance Scaling in Rotating Detonation Engines Operated on Hydrogen and Gaseous Hydrocarbon Fuel［C］, Glasgow：20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, (2015)
  • [3] Kailasanath K，, Schwer D A., High-Fidelity Simulations of Pressure-Gain Combustion Devices Based on Detonations［J］, Journal of Propulsion and Power, 33, 1, pp. 153-162, (2017)
  • [4] Paxson D., A Simplified Model for Detonation Based Pressure-Gain Combustors［C］, Nashville：46th AIAA/ASME/ SAE/ASEE Joint Propulsion Conference and Exhibit, (2010)
  • [5] Paxson D, Kaemming T., Foundational Performance Analyses of Pressure Gain Combustion Thermodynamic Benefits for Gas Turbines［C］, Nashville：50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, (2012)
  • [6] Paxson D，, Kaemming T., Influence of Unsteadiness on the Analysis of Pressure Gain Combustion Devices［J］, Journal of Propulsion and Power, 30, 2, pp. 377-383, (2014)
  • [7] Zheng H，Qi L，, Zhao N，, Et al., A Thermodynamic Analysis of the Pressure Gain of Continuously Rotating Detonation Combustor for Gas Turbine［J］, Applied Sciences, 8, 4, (2018)
  • [8] Tsuboi N，, Watanabe Y，, Kojima T，, Et al., Numerical Estimation of the Thrust Performance on a Rotating Detonation Engine for a Hydrogen-Oxygen Mixture［J］, Proceedings of the Combustion Institute, 35, 2, pp. 2005-2013, (2015)
  • [9] Yi T H, Turangan C，, Et al., Propulsive Performance of a Continuously Rotating Detonation Engine［J］, Journal of Propulsion and Power, 27, 1, pp. 171-181, (2011)
  • [10] Qi L, Zhao N，, Wang Z，, Et al., Pressure Gain Characteristic of Continuously Rotating Detonation Combustion and Its Influence on Gas Turbine Cycle Performance［J］, IEEE Access, 99, 6, pp. 70236-70247, (2018)
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