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Experimental Investigation of Self-Excited Combustion Instabilities in a LOX/LNG Rocket Combustor
Journal of Propulsion and Power ( IF 1.9 ) Pub Date : 2021-06-14 , DOI: 10.2514/1.b38289
Jan Martin 1 , Wolfgang Armbruster 1 , Justin Steven Hardi 1 , Dmitry Suslov 1 , Michael Oschwald 1
Affiliation  

Two types of combustion instabilities were observed in a multi-injector research combustor with liquid oxygen and liquefied natural gas (LOX/LNG) propellants operating at conditions similar to an upper stage rocket engine. The first was identified as an excited tangential acoustic mode of the combustion chamber and can be explained by coupling with the LOX injectors, similar to the mechanism previously observed in tests with LOX/H2 propellants. The other type is characterized by longitudinal acoustic oscillations with peak-to-peak amplitudes of at least 40% of the mean chamber pressure. Analysis of the test data suggests that sudden upstream displacement of a lifted flame may be the trigger mechanism for the second type of instabilities.



中文翻译:

LOX/LNG火箭燃烧器自激燃烧不稳定性的实验研究

在使用液氧和液化天然气 (LOX/LNG) 推进剂的多喷射器研究燃烧器中观察到两种类型的燃烧不稳定性,该燃烧器在类似于上级火箭发动机的条件下运行。第一个被确定为燃烧室的激发切向声学模式,可以通过与 LOX 喷射器耦合来解释,类似于先前在测试中观察到的机制熏鲑鱼/H2推进剂。另一种类型的特征是纵向声波振荡,其峰峰值幅度至少为平均腔室压力的 40%。对测试数据的分析表明,升起火焰的突然上游位移可能是第二种不稳定性的触发机制。

更新日期:2021-06-15
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