SILOET II Project 19, CMC and High Temperature Technologies

Future civil aerospace gas turbine competitiveness will rely on higher temperature core turbo machinery and higher temperature performance cycles to improve fuel burn and emissions. This project is focused on the development of new high temperature turbine capability. The application of novel Ceramic Matrix Composites will be explored as a potential new material system in the core turbines. A number of other technologies including new alloy chemistry and protective coating developments will also be developed. Testing will be carried out at specimen, component and sub-system level in rigs and engines.