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声激励下气液针栓火箭发动机中的瞬态喷雾燃烧特性

Transient spray combustion characteristics in a gas-liquid pintle rocket engine under acoustic excitation.

作者信息

Jin Xuan, Zhu Chao, Chen Dejiang, Zhang Zhongpei

机构信息

Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang, 621000, China.

National Key Laboratory of Aerospace Physics in Fluids, China Aerodynamics Research and Development Center, Mianyang, 621000, China.

出版信息

Sci Rep. 2024 Jun 7;14(1):13135. doi: 10.1038/s41598-024-64027-2.

DOI:10.1038/s41598-024-64027-2
PMID:38849526
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC11637071/
Abstract

In order to investigate the acoustic oscillation characteristics of gas-liquid pintle rocket engines and elucidate the path by which spray combustion process provides energy to the combustor pressure oscillation, a LOX/GCH pintle engine with rectangular combustor was designed. By adding transverse velocity disturbance for the first time, the acoustic response of spray combustion process was simulated, and the effect of excitation amplitude on acoustic response was researched. Numerical results show that the adopted transverse velocity disturbance can excite the first-order transverse acoustic oscillation with same excitation frequency in the engine combustor. The acoustic response maintenance mechanism under extrinsic excitation is summarized for pintle engines. Besides, the temperature distribution inside the engine combustor tends to be uniform, and the low-frequency oscillation caused by the flame transverse swing gradually disappears. The amplitude of combustor pressure oscillation is dominated by excitement amplitude and phase difference between the pressure and heat release in combustion reaction region. In addition, the time-averaged combustor pressure can be amplified mainly by transverse velocity disturbance. The research work can provide a reference for related fire tests on the acoustic response of a subscale gas-liquid pintle engine.

摘要

为了研究气液针栓式火箭发动机的声学振荡特性，并阐明喷雾燃烧过程为燃烧室压力振荡提供能量的途径，设计了一种具有矩形燃烧室的液氧/气氢针栓式发动机。首次通过添加横向速度扰动，模拟了喷雾燃烧过程的声学响应，并研究了激励幅度对声学响应的影响。数值结果表明，所采用的横向速度扰动能够在发动机燃烧室内激发具有相同激励频率的一阶横向声学振荡。总结了针栓式发动机在外源激励下的声学响应维持机制。此外，发动机燃烧室内的温度分布趋于均匀，火焰横向摆动引起的低频振荡逐渐消失。燃烧室压力振荡的幅度主要由激励幅度以及燃烧反应区域压力与热释放之间的相位差决定。此外，燃烧室的时间平均压力主要可通过横向速度扰动放大。该研究工作可为亚尺寸气液针栓式发动机声学响应的相关点火试验提供参考。

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https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/2e529fe2ee4b/41598_2024_64027_Fig4_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/efbd78535534/41598_2024_64027_Fig5_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/7c6f0fa13772/41598_2024_64027_Fig6_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/f9b8f2d7cf25/41598_2024_64027_Fig7_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/b8607eea9499/41598_2024_64027_Fig8_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/ff5e001846a0/41598_2024_64027_Fig9_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/bb4c643c090c/41598_2024_64027_Fig10_HTML.jpg
https://cdn.ncbi.nlm.nih.gov/pmc/blobs/3909/11637071/fa2932162712/41598_2024_64027_Fig11_HTML.jpg

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