Joining of ceramic matrix composites to high temperature ceramics for thermal protection systems
Abstract The current work reports a novel approach for the integration of external protective SiC multilayers with ceramic matrix composite (C f /SiC) with the view of application in aerospace heat protection systems. The integration method is based on diffusion brazing bonding. As a joining agent the MAX Phase Ti 3 SiC 2 produced by self propagating high temperature synthesis, has been employed. The pressure applied during the joining process and its effect on the microstructure of the integrated structure is discussed. Microstructural analysis of the resulting joints is conducted using scanning electron microscopy coupled with energy dispersive spectroscopy and X ray diffraction measurements. Analysis of the joints showed that the bonds are uniform, dense, with few crack vertical to the interface which are not detrimental for the performance of the joints. Ground re entry tests showed that the joints survive 5 re entry cycles at 1391 and 1794 degC without any detectable damage.