Total Pressure Loss Characteristics in a Strut-Cavity Based Scramjet Combustor

Journal of Propulsion Technology ›› 2016, Vol. 37 ›› Issue (2): 339-345.

• Combustion , Heat and Mass Transfer • Previous Articles Next Articles

Total Pressure Loss Characteristics in a Strut-Cavity Based Scramjet Combustor

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China

Published:2021-08-15

支板/凹腔超声速燃烧室总压损失特性研究

赵永胜,林宇震,王建臣,刘伟

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191

作者简介:赵永胜，男，博士生，研究领域为超然冲压发动机。

Abstract

Abstract: The total pressure loss characteristics in a strut-cavity based scramjet combustor are experimentally investigated. Based on the wall pressure profiles，a one-dimensional analysis code was conducted to obtain the axial Mach number and total pressure profiles in the non-reacting and reacting cases. With the change of the equivalence ratio，the total pressure losses in the non-reacting and reacting cases were investigated，respectively. The results show that with the fuel equivalence ratio increased from 0.35 to 0.8，the total pressure losses in the reacting cases gradually decrease，and the final value is less than that in the non-reacting case. Simultaneously，the influences of the wall friction and combustion on the total pressure losses are reduced，while the influence of the shock wave structure increased.

Key words: Strut-cavity；Scramjet combustor；Total pressure loss characteristics；One-dimensional analysis

摘要： 为了研究支板/凹腔超声速燃烧室总压损失特性，基于实验测得的壁压，结合一维分析方法，得到了支板/凹腔超声速燃烧室冷态和热态的沿程马赫数与总压。对不同当量比下，燃烧室冷态与热态的总压损失特性进行了研究。研究表明:支板/凹腔超声速燃烧室在当量比为0.35～0.8的范围内，随着当量比的提高，热态的总压损失系数逐渐减小，会逐步小于冷态总压损失系数；其中壁面摩擦和燃烧对总压损失的影响随之减小，波系结构的影响随之增加。

关键词: 支板/凹腔；超声速燃烧室；总压损失特性；一维分析

ZHAO Yong-sheng,LIN Yu-zhen,WANG Jian-chen,LIU Wei. Total Pressure Loss Characteristics in a Strut-Cavity Based Scramjet Combustor[J]. Journal of Propulsion Technology, 2016, 37(2): 339-345.

赵永胜,林宇震,王建臣,刘伟. 支板/凹腔超声速燃烧室总压损失特性研究[J]. 推进技术, 2016, 37(2): 339-345.

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Total Pressure Loss Characteristics in a Strut-Cavity Based Scramjet Combustor

支板/凹腔超声速燃烧室总压损失特性研究

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