High Pressure Optically Accessible Rocket Combustor Testing and Evaluation

This paper details the Multi-Purpose Optically Accessible Combustor (MOAC) and its utilization for injector design and combustion research. The MOAC is intended for experimentation and research of combustion of liquid and gaseous propellants. For the uses at the Center for Space Exploration Technology research, there is a particular focus on using the MOAC with liquid Oxygen and liquid Methane as propellant fuels. The MOAC system is versatile and can be used with a number of injector styles. Current interest centers on Shear Coaxial injectors common with Oxygen and Methane systems. Descriptions of the test procedure to ensure proper ignition and testing are described. Instrumentation critical to obtaining test data for analysis of the thermodynamic properties of both the propellants and the combustion chamber are detailed as well. Optical instrumentation associated with the MOAC system is thoroughly described to identify the characteristics of the spray and combustion dynamics. Finally testing parameters will be explained as well as a summary of initial test results concluded from initial testing.