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Development of design methodologies for ceramic matrix composites for industrial gas turbine engines

Deliverables

Two structural test parts that are intended to be representative of gas turbine hot section components have been designed, manufactured and tested. The first is a combustor can tested in a high-pressure test rig, and the second is a combustor liner. Thermal, structural and dynamic finite element calculations were carried to simulate the behaviour under testing conditions. Design and analysis issues specific to CMC component simulation have been addressed. Software tools have been developed for the purpose of simplifying the FE modelling. Issues relating to the clamping arrangements for CMC cans have been identified. Following the FE simulations, tests were carried out at temperatures up to 1550°C resulting in very high combustion efficiency, and levels of carbon monoxide and unburned hydrocarbon emission levels consistently below 10ppmv. Several problems were highlighted by the tests which indicate a need for further development. However, the overall performance of both the combustor can and liner was very satisfactory. Computational damage prediction in ceramic composite materials and the test experience gained will help the partners with developing new and improved designs of combustion chambers for gas turbines.