一种双模态超燃燃烧室芯流面积的一维计算方法

推进技术 ›› 2018, Vol. 39 ›› Issue (8): 1803-1809.

一种双模态超燃燃烧室芯流面积的一维计算方法

张云峰,杨庆春,徐旭

北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:张云峰，男，硕士生，研究领域为超燃冲压发动机技术。E-mail: heliosxuanyuan@163.com 通讯作者:徐旭，男，博士，教授，研究领域为高超声速飞行器机体/推进系统一体化技术，冲压发动机技术，液体/固体火箭发动机技术，高超声速流体力学，两相流体力学等。

One Dimensional Method for Calculation of DualMode Scramjet Combustor Core Flow Area

School of Astronautics，Beihang University，Beijing 100191，China,School of Astronautics，Beihang University，Beijing 100191，China and School of Astronautics，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得双模态超燃冲压发动机一维性能计算的重要参数——燃烧室芯流面积，基于实验测量的壁面静压数据，发展了一种芯流面积的计算方法。计算中，通过选取分离区下游合适的参考截面，获得了燃烧室释热分布模型中的经验常数，从而得到了适用于当前工况的燃烧室芯流面积分布及流动情况，有效地降低了计算方法对来流条件、构型、燃料当量比及喷注方式等多种因素的依赖。与不同工况流场数值仿真结果的对比表明:该方法能够对超燃燃烧室内芯流面积、马赫数的变化情况进行较为准确的捕捉，燃烧效率误差在7%之内，具有较好的通用性。

关键词: 超燃燃烧室；一维分析；释热分布；芯流面积

Abstract: To obtain the combustor core flow area， which is one of the key factors in the one dimensional calculation of the dual-mode scramjet， a method based on the static pressure measured in the experiment was developed. In this method， the empirical constant， which is suitable for the current condition， of the heat distribution model was obtained through choosing the reference surface downstream of the separation region， and it helped to reduce the dependence on the factors such as the inflow conditions， the configuration of combustor， the equivalence ratio of the fuel， the types of the injection and so on. The comparison with the simulation results indicated that， this method could calculate the core fluid area and Mach number of the scramjet combustor accurately， makethe error of the combustion effect less than 7%， and show good versatility.

Key words: Scramjet combustor；One-dimensional analysis；Heat release distribution；Core flow area

张云峰,杨庆春,徐旭. 一种双模态超燃燃烧室芯流面积的一维计算方法[J]. 推进技术, 2018, 39(8): 1803-1809.

ZHANG Yun-feng,YANG Qing-chun,XU Xu. One Dimensional Method for Calculation of DualMode Scramjet Combustor Core Flow Area[J]. Journal of Propulsion Technology, 2018, 39(8): 1803-1809.

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