当前位置: X-MOL 学术Acta Astronaut. › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Single pulse combustion test of high-frequency instability of rocket engine
Acta Astronautica ( IF 3.5 ) Pub Date : 2021-01-01 , DOI: 10.1016/j.actaastro.2020.08.024
Ryoya Umeoka , Yuuki Mishina , Takeshi Kanda

Abstract Combustion tests were conducted to investigate the high-frequency combustion instability of liquid-propellant rocket engines. An experimental apparatus was designed to examine the rapid and large pressure increase that occurs near the propellant injector, based on the mechanism of the off-design combustion model. The propellants were 2-propanol and gaseous oxygen. The propanol jet created a semi-enclosed base space near the injection port. Pressure in the semi-enclosed space due to combustion was 1.5–3 times higher than the pressure prior to combustion. The duration of the pressure increase ranged from 0.03 to 2 ms. The pressure increase and its duration agreed with the features of the high-frequency combustion instability of liquid-propellant rocket engines. The model temperatures affected the pressure increase and the duration of pressure change.

中文翻译:

火箭发动机高频不稳定性单脉冲燃烧试验

摘要 通过燃烧试验研究液体推进剂火箭发动机的高频燃烧不稳定性。基于非设计燃烧模型的机制,设计了一个实验装置来检查推进剂喷射器附近发生的快速和大的压力增加。推进剂是2-丙醇和气态氧。丙醇射流在注射口附近形成了一个半封闭的基础空间。由于燃烧,半封闭空间内的压力比燃烧前的压力高 1.5-3 倍。压力增加的持续时间为 0.03 到 2 毫秒。压力升高及其持续时间符合液体火箭发动机高频燃烧不稳定性的特点。
更新日期:2021-01-01
down
wechat
bug