The development in thermal barrier coating (TBC) systems for cryogenic liquid rocket combustion chambers is addressed. It resulted in the preference for electron-beam physical vapor deposition techniques (EB-PVD) subsequently used for application of bond coats as well as zirconia TBCs. The high strength potential of age-hardening Cu alloys, e. g. CuCrZr as a well-suited substrate material class, inspired the search for temperature-cycle tolerant coating varieties that allow to follow heating and quenching procedures common for alloy strength optimization through age-hardening routines. LH_2 cooled sub-scale CuCrZr combustion chambers were coated with developmental TBC systems by in-house EB-PVD procedures. Close to reality rig tests at the Lampoldshausen test facility P8 at pressures of 110 bar and fueled with LO_2/LH_2 confirmed the aptitude of the TBC systems for rocket combustion chamber linings.
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