Injector characterization for a gaseous oxygen-methane single element combustion chamber

¹ Technische Universität München (TUM) Institute for Flight Propulsion (LFA) 15 Boltzmannstr., Garching, Munich 85747, Germany
² Airbus Defense and Space Ottobrunn, Germany

Abstract

The results from an experimental investigation on an oxygen-methane single-injector combustion chamber are presented. They provide detailed information about the thermal loads at the hot inner walls of the combustion chamber at representative rocket engine conditions and pressures up to 20 bar. The present study aims to contribute to the understanding of the thermal transfer processes and to validate the in-house design tool Thermtest and a base for an attempt to simulate the flame behavior with large-eddy simulation (LES). Due to the complex flow phenomena linked to the use of cryogenic propellants, like extreme variation of flow properties and steep temperature gradients, in combination with intensive chemical reactions, the problem has been partially simplified by injecting gaseous oxygen (GOx) and gaseous methane (GCH₄).