High-pressure combustion test facility for detailed investigation of single sector and multi sector combustor test sections under realistic engine conditions.
DLR (CC BY-NC-ND 3.0).
Combustor test rig for the investigation of the burner‘s near field with laser-optical measurement techniques.
Optical investigation of fuel injection and droplet atomization in non-reactive conditions.
Characterisation of cooling efficiency of metal and ceramic combustion chamber wall elements under realistic operating conditions.
Test section OCORE2 (Optical-COmbustoR-Exit 2) ) with full optical access to combustor zones for laser-optical diagnostics under realistic engine conditions.
Large-Eddy-Simulation of combustor test section HOTS
Effusions cooled combustor exit, manufactured with Selective-Laser-Melting (SLM).
The Combustor department of the Institute of Propulsion Technology investigates the complex phenomena characterizing the flow-field in jet engine and gas turbine combustors. In our laboratories experimental studies are conducted for a deeper understanding of the turbulent flow-field, the chemical reactions, the heat transfer and their interactions in a combustion chamber under realistic operative conditions. All test facilities are built to allow optical access for a detailed investigation of the combustion processes.
Accurate numerical simulation tools are developed for supporting the experimental tests and the integrated design of combustion chambers.
Special effort is dedicated to study both experimentally and numerically advanced combustion concepts to reduce pollutant emissions.
These and other combustion chamber issues are analyzed in cooperation with other DLR departments, international research group and industrial partners.