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.
Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000; Paper 00-GT-638. Manuscript received by the IGTI, November 1999; final revision received by ASME Headquarters, February 2000. Associate Editor: D. Wisler.
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Corman , G. S., Dean , A. J., Brabetz , S., Brun , M. K., Luthra, K. L., Tognarelli , L., and Pecchioli, M. (June 19, 2002). "Rig and Engine Testing of Melt Infiltrated Ceramic Composites for Combustor and Shroud Applications ." ASME. J. Eng. Gas Turbines Power. July 2002; 124(3): 459–464. https://doi.org/10.1115/1.1455637
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