Self-excited thermoacoustic instabilities as frequently observed in rocket motors, gas
turbines, ramjets, and aeroengine afterburners are highly detrimental and undesirable for …

We present a data-driven method for the early detection of thermoacoustic instabilities.
Recurrence quantification analysis is used to calculate characteristic combustion features …

The excitation mechanism of a thermoacoustic instability in a 42-element research rocket
thrust chamber with representative operating conditions with respect to European cryogenic …

Combustion instability is investigated in a model chamber by changing the recess length of
a gas-centered swirl coaxial injector ranging from 0 mm to 20 mm with a 4 mm interval …

This article describes an experimental investigation into the flame dynamics of a subscale
rocket combustor operating with five shear-coaxial injectors fed with methane and oxygen …

We study the spatio-temporal dynamics of high-frequency combustion instability in a model
single-element rocket combustor using an acoustic energy flux-based spatial network. The …

Large-eddy simulation is applied to compute the combustion instabilities in an experimental
42-injector hydrogen-oxygen (H2-O2) rocket engine. The unsteady, compressible, multi …

Hot fire tests of a multi-injector research combustor were performed with liquid-oxygen and
liquefied-natural-gas (LOX/LNG) propellants at chamber pressures from 30 up to 67 bar …

This paper uses a reactive flow large eddy simulation (LES) and decomposition techniques
to study combustion instabilities in a methane–oxygen combustor. This work examines two …

View Video Presentation: https://doi. org/10.2514/6.2021-3568. vid High-frequency
combustion instability was observed under certain conditions in a multi-injector research …