General Electric has developed SiC fiber-reinforced SiC-Si matrix composites produced by silicon melt infiltration for use in gas turbine engine applications. High temperature, high-pressure combustion rig testing, and engine testing has been performed on combustor liners and turbine shrouds made from such MI composites. Frame 5 sized combustor liners were rig tested under lean head end diffusion flame conditions for 150 hours, including 20 thermal trip cycles, with no observed damage to the ceramic liners. Similarly, 46-cm diameter, single-piece turbine shroud rings were fabricated and tested in a GE-2 gas turbine engine. The fabrication and testing of both components are described.
Issue Section:Gas Turbines: Ceramics
Keywords:ceramics, fibre reinforced composites, melt infiltration, materials testing, high-temperature effects, high-pressure effects, gas turbines, silicon compounds, carbon compounds, silicon
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Dean, A., Corman, G., Bagepalli, B., Luthra, K., DiMascio, P., and Orenstein, R., 1999, “Design and Testing of CFCC shroud and Combustor Components,” ASME Paper 99-GT-235.
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