Certain sections of aero gas-turbine engines, which are widely used in aircrafts, regularly reach temperatures above 1,200 °C. Needless to say, any materials used in such harsh environments must be durable and up to the task. Ceramic matrix composites made of silicon carbide (SiC) have recently garnered interest as promising candidates for gas-turbine engines. However, these materials require a heat-resistant coating layer to prevent the oxidation of SiC and subsequent evaporation of SiO2, which is a process that leads to a decrease in the material volume and, therefore, structural defects such as large cracks or the topmost layer flaking off.