The sub-project „Principle H2 combustion experiments“, which is embedded in the joint research project H2_TURB, has the target to contribute to the development of H2-combustion concepts for aero engines based on principle combustion experiments at ambient pressure at the Karlsruhe Institute of Technology. For aero-engines the stability and safety in a wide and transient operating range is essential. In addition, a compact combustion system is targeted. The stability range and nitrogen oxide emissions of H2-combustion concepts, suitable for aero-engines, will be determined for typical RQL (Rich-Quench-Lean) combustor concepts as well as lean concepts with an optimized degree of premixing. Relevant phenomena as i.e. the position of the flame in the quench module and near to the burner will be investigated for lean and rich conditions based on i.e. laser optical measurement techniques. The detailed experimental data of this sub-project will be utilized in the joint research project to identify weaknesses in the numerical modelling and to identify possibilities for optimization of the capability to model the relevant phenomena. The experimental results will aid to develop H2-Combustion concepts with low nitrogen oxide emissions regarding especially the application for retrofit of existing aero-engines. The investigations will advance the knowledge regarding the combustion of hydrogen in gas turbines for stationary as well as mobile applications and provides the possibility to use synergies and to boast the development.