In this paper, we present the numerical evidence of multiple bifurcations in thermoacoustic
instability as we decrease the equivalence ratio (ϕ) from fuel-rich (ϕ= 1.5) to fuel-lean (ϕ …

Prediction of combustion instability is essential in reducing development costs of large scale
rocket engines. Recently, high fidelity CFD models have shown some ability to represent the …

The longitudinal combustion instability characteristics of a pintle injector for a liquid rocket
engine combustor are investigated experimentally. The effects of the propellant total …

This work addresses the nature of supercritical hydrogen-oxygen flame coupling to
acoustics through visualization under conditions representative of upper-stage rocket …

Hot fire tests were performed with a newly developed single-injector research combustor
featuring a large optical access (255× 38 mm) for flame imaging. Within these tests the …

Combustion instabilities were investigated experimentally for a hydrogen-rich combustion in
a model afterburner installed at the end of a high-enthalpy wind tunnel. Air was supplied at …

This paper provides the first numerical proof of intermittency routes existing before and after
thermoacoustic instability, as we increase the oxidizer inlet temperature under fuel-lean (ϕ …

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

This paper compares the two dominant types of radiation from hydrogen flames under rocket-
combustion conditions: ultraviolet and blue radiation. The physical sources of both types are …

A laboratory-scale gas turbine model combustor fueled with methane is studied
experimentally with the aid of three-dimensional computed tomography of …