Demonstration of a CMC Combustion Chamber for Large Commercial Turbofan Engine

Ceramic Matrix Composites (CMCs) are considered as one of the most promising materials to replace superalloys for high temperature components of gas turbine engines. The use of CMC technology in the hot section of gas turbines provides higher temperature capability with high strength and toughness. The introduction of the technology in turbofan engines aims at operating the system at higher temperatures with reduced cooling air, thus enabling superior fuel efficiency and reduced harmful emissions.

The paper will provide an overview of a multi-year program aimed at demonstrating the feasibility of a large turbofan engine combustor fitted with inner and outer liners manufactured from our advanced Cerasep^®A415 material. The main tasks of the demonstration program include the evaluation and selection of the material along with design and engineering activities in order to adapt the annular combustor subsystem to the specific features of the CMC material.

Mechanical rig testing of sub-elements and rig combustion testing of subscale combustor using the selected material technology are implemented as risk-reduction steps prior to the full-scale combustor manufacturing and assembly.

The paper will also address the specific NDE performed on the CMC components and the rig test experience to-date of the full-scale combustor.