Supercritical combustion has attracted significant interest due to its applications in high-pressure combustion devices. Validation of supercritical combustion modeling, however, has not been well reported because of the lack of experimental data with sufficient spatial and temporal resolution as well as the complexity associated with modeling and simulations. The present work begins to bridge this gap with a systematic examination of gaseous H2-O2 combustion of a shear coaxial injector at supercritical conditions, using both large-eddy simulation and detachededdy simulation approaches. The formulation accommodates the full conservation laws and real-fluid thermodynamics and transport theories. Turbulence/chemistry interactions are treated by means of the flamelet and flamelet/progress-variable approaches. A nonpremixed jet flame (Sandia flame D) was first considered for code validation at ideal-gas conditions. The gaseous H2-O2 combustion at supercritical conditions was then studied systematically using different combinations of turbulence closure and combustion models. Special attention was given to comparison with measured wall heat flux. The large-eddy simulation/flamelet, detached-eddy simulation/flamelet, and large-eddy simulation/flamelet/progress-variable approaches produced qualitatively similar results in terms of flow and flame structures as well as wall heat flux. The present work was also compared with studies conducted by other research groups.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science