Thermal Cycle and Propulsive Performance of Turbine Engine with Continuous Detonation Afterburner

被引：0
|
作者：
Qiu H. [1 ]
Chen Y.-B. [1 ]
Xiong C. [1 ]
Gai J.-C. [1 ]
机构：
[1] School of Power and Energy, Northwestern Polytechnical University, Xi’an
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2022年 / 43卷 / 07期
关键词：
Afterburner; Continuous detonation; Performance model; Propulsive performance; Turbine engine;
D O I：
10.13675/j.cnki.tjjs.210079
中图分类号：
学科分类号：
摘要：
In order to improve the propulsive performance of conventional turbine engine，a continuous detonation afterburner can be used. An analytical model of thermodynamic process for the continuous detonation afterburner is established，which considers three kinds of coupled thermodynamic processes. By coupling the model with performance analytical model of conventional turbine engine，the propulsive performance and component characteristics of turbine engine with continuous detonation afterburner are investigated. The results show that the performance of turbine engine can be significantly enhanced by replacing the conventional afterburner with the continuous detonation afterburner because of its pressure-gain characteristics. On the other hand，the high temperature of the gas flow behind the turbine has negative effect on the pressure-gain of continuous detonation afterburner. This adverse effect can be weakened by carefully selecting cycle parameters of the engine. The component characteristics of continuous detonation afterburner are also affected by the inlet loss of combustor，the filling velocity of reactants and the mass fraction of deflagration products. © 2022 Journal of Propulsion Technology. All rights reserved.
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