CMC integration and demonstration for gas turbine engines (CINDERS)

Thermal protection systems (TPS) on ceramic matrix composites are being evaluated for gas turbine combustor applications that can operate at 1400 °C for the life of the engine. The following paper reviews the work conducted recently within the “CINDERS” project, which is aimed at developing and testing TPS suitable for CMC Cerasep G415 combustor liners. Several coating systems have been identified for development, characterisation, and testing. These have been applied by air plasma spraying and by wet processing methods. Validation assessment has been scheduled by means of rig testing a series of sub-element specimens and combustor liners. NDE techniques have been employed to detect internal defects and damage and to aid service life predictions. Characterisation of the CMC, in both the coated and uncoated conditions has been conducted, as well as modelling of the thermal and mechanical properties of the CMC and TPS. Manufacturing and life prediction methods have been developed and integrated into a practical component design “toolbox” for CMC combustor liners.