Rocket engine combustors are prone to transverse instabilities that are characterized by
large amplitude high frequency oscillations in the acoustic pressure and the heat release …

Self-excited longitudinal combustion instabilities were analyzed in a sub-scale combustor
operating with a propellant combination of O 2/CH 4. Couplings between acoustics …

Self-excited combustion instabilities of transverse modes were experimentally investigated
in a rectangular multi-injector model combustor, operating with the bipropellants O 2/CH 4 …

Capturing the complex spatiotemporal flame dynamics inside a rocket combustor is
essential to validate high-fidelity simulations for developing high-performance rocket …

Combustion instabilities in a high-pressure, multi-element combustor are studied in order to
understand the relationship between the chamber and injector dynamics. A linear array of …

Self-excited high frequency combustion instability (HFCI) of first-order tangential (1T) mode
was observed in a staged-combustion LOX/Kerosene liquid rocket engine numerically. Two …

Experiments were performed to investigate the ensemble combustion of a linear array of
three coaxial liquid oxygen/gaseous hydrogen turbulent non-premixed jet flames, under the …

Experiments were performed to investigate the ensemble combustion of a linear array of
three coaxial liquid oxygen/gaseous hydrogen turbulent non-premixed jet flames. The …

基于自燃推进剂液/液双旋流喷嘴, 设计多喷嘴模型火箭发动机, 通过试验研究了氧燃比,
缩进长度对自燃推进剂模型火箭发动机高频纵向燃烧不稳定的影响. 结果表明: 在0.4 mm …

An experimental study was conducted to visualize the dynamics and spectra of single-
element shear coaxial liquid oxygen (LOX)/gaseous methane flames at high but still …