Compared to RQL combustion in hydrogen-fueled aero engines, the state of knowledge for technically premixed combustion with hydrogen in aircraft engines is still far behind. This applies to the conceptual level as well as to the optimization of promising concepts. However, the further development of premixed hydrogen combustion is expected to bring several benefits, especially in the reduction of NOx emissions. Therefore, this project investigates the behaviour of an innovative, premixed injection and combustion concept suitable for the use of hydrogen. Therefore, steady-state (mixture formation and heat release distribution) and transient (ignition, start-up, and shutdown) behavior will be evaluated, and thermoacoustic investigation of premixed combustion with the lowest NOx emissions will be conducted. GE-Aviation will design the injection and combustion system and deliver them to TUM, where the above-mentioned experiments will be performed.
In addition, a novel axially staged system will be developed at TUM, and the first functional tests will be performed. This system is intended to apply the developed technology for staged hydrogen combustion from stationary gas turbines to aircraft engines, thus paving the way for new approaches to emission reduction. The staged system has an increased reduction potential compared to the non-staged one. The stages are tailored to different operating points in various configurations to meet the demands of various flight conditions and, thus, different load requirements. This concept is first designed through simulation and then experimentally tested, with measurements focusing on emissions.