William E. Anderson

TL;DR: In this article, the first published in the United States on the subject since NASA's Liquid Rocket Combustion Instability (NASA SP-194) in 1972, the authors cover four major subject areas: engine phenomenology and case studies, fundamental mechanisms of combustion instability, combustion instability analysis and engine and component testing.

TL;DR: In this paper, an experimental study of spontaneous longitudinal high-frequency combustion instabilities in a high-pressure model rocket combustor is described, where a traversing axial oxidizer inlet is used to vary the coupled resonances between the variable-length oxidizer tube and the fixed-length combustion chamber, thereby changing the temporal and spatial relationship between the fluid mechanical resonances in the oxidizer tubes and the local pressure oscillations at the head end of the combustor.

TL;DR: In this paper, a hybrid RANS/large eddy simulation of a non-premixed, high-pressure laboratory combustor that produces self-excited longitudinal instabilities is presented.

TL;DR: In this paper, a single injector element liquid rocket combustion experiment was designed and conducted to investigate the combustion dynamics of a gas-centered, liquid-swirled coaxial injector component.

TL;DR: In this article, three numerical simulations of an unstable laboratory rocket combustor were performed to assess the effect of grid resolution and dimensionality on the ability to predict and model combustion instability, showing that two-dimensional axisymmetric simulations using both coarse and fine grids are able to capture the amplitude of the first longitudinal mode within an order of magnitude of what was measured in the experiment.