考虑喷注流强分布的纵向稳定性建模与分析

doi:10.7527/S1000-6893.2020.24510

流体力学与飞行力学

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考虑喷注流强分布的纵向稳定性建模与分析

汪广旭¹, 谭永华², 陈建华¹, 庄逢辰³, 洪流¹, 陈宏玉¹, 杨宝娥¹

1. 西安航天动力研究所液体火箭发动机技术重点实验室, 西安 710100;
2. 航天推进技术研究院, 西安 710100;
3. 航天工程大学宇航科学与技术系, 北京 101416

收稿日期:2020-07-09 修回日期:2020-07-31 出版日期:2021-06-15 发布日期:1900-01-01
通讯作者: 汪广旭 E-mail:wanggx@aliyun.com
基金资助:
液体火箭发动机技术重点实验室基金（614270419）

Modeling and analysis of longitudinal stability considering injection intensity distribution

WANG Guangxu¹, TAN Yonghua², CHEN Jianhua¹, ZHUANG Fengchen³, HONG Liu¹, CHEN Hongyu¹, YANG Baoe¹

1. Key Laboratory for Liquid Rocket Engine Technology, Xi'an Aerospace Propulsion Institute, Xi'an 710100, China;
2. Academy of Aerospace Propulsion Technology, Xi'an 710100, China;
3. Department of Aerospace Science and Technology, Space Engineering University, Beijing 101416, China

Received:2020-07-09 Revised:2020-07-31 Online:2021-06-15 Published:1900-01-01
Supported by:
Project Supported by the Science and Technology Foundation of Key Laboratory for Liquid Rocket Engine Technology (614270419)

摘要/Abstract

摘要： 喷注器流强分布是除声学阻尼装置以外使液体火箭发动机稳定工作的重要措施，通过控制喷注流强分布使推进剂的燃烧尽量远离主要振型的波腹区，减少热声耦合振荡的能量源，从而达到抑制高频振荡的效果。因此，建立喷注流强分布与稳定性之间的综合分析模型，研究流强分布的不稳定性抑制特性具有重要实际意义。针对采用自击式喷嘴器、液滴蒸发作为燃烧速率控制过程的某自燃推进剂缩尺燃烧室高频纵向燃烧不稳定问题，近似采用蒸发速率峰值区代替集中燃烧释热区，引入燃烧室三维声学控制方程以考虑多喷嘴条件下燃烧响应空间分布，建立了针对喷注器流强分布条件下的高频纵向燃烧稳定性分析模型，并对喷注流强的稳定性抑制特性进行了分析，给出了不同分布流强下燃烧室一阶纵向信号的增长率变化规律。研究表明，喷注流强分布有利于燃烧室稳定，"驼峰区"喷注孔径的增大对改善高频纵向不稳定性更为显著，"驼峰区"流强增加30%，相应的增长率降低15%。

关键词: 自燃推进剂, 液滴蒸发, 流强分布, 燃烧响应, 三维声学, 纵向稳定性, 增长率

Abstract: Apart from acoustic damping devices, injection intensity distribution is a main method for the stabilization of liquid rocket engines. Through injection intensity distribution control, propellant combustion moves far away from the node of the main acoustic mode, decreasing the coupled energy driving thermo-acoustic instability and thereby suppressing high frequency combustion instability. Therefore, it is highly significant to build a comprehensive analysis model between injection intensity distribution and instability. For the hypergolic sub-scaled combustor adopting a self-impinging injector and droplet vaporization as the rate-control process, the concentrated combustion zone can be approximately replaced by the area with the highest evaporation rate in analysis of high longitudinal combustion instability. To build a theoretical model for high longitudinal combustion instability considering injection intensity distribution and analysis of its instability suppression capability for injection intensity distribution, a three-dimensional thermo-acoustic equation for the combustion chamber with multiple injectors is introduced for spatial distribution of concentrated combustion response. Finally, the growth rates representing combustion instability of the first longitudinal mode with different injection intensity distributions are computed. Results indicate that the injector with higher injection intensity in the hump zone is more stable than that with lower intensity, with a typical result of 30% gain from injection intensity in the hump zone leading to a 15% reduction in the growth rate.

Key words: hypergolic propellant, droplet evaporation, injection intensity distribution, combustion response, three-dimensional acoustics, longitudinal stability, growth rates

中图分类号:

V434.4

汪广旭, 谭永华, 陈建华, 庄逢辰, 洪流, 陈宏玉, 杨宝娥. 考虑喷注流强分布的纵向稳定性建模与分析[J]. 航空学报, 2021, 42(6): 124510-124510.

WANG Guangxu, TAN Yonghua, CHEN Jianhua, ZHUANG Fengchen, HONG Liu, CHEN Hongyu, YANG Baoe. Modeling and analysis of longitudinal stability considering injection intensity distribution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 124510-124510.

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

考虑喷注流强分布的纵向稳定性建模与分析

Modeling and analysis of longitudinal stability considering injection intensity distribution

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