Abstract: Ceramic-matrix composites (CMCs) inherit the advantages of high temperature resistance and corrosion resistance, overcome the brittleness of monolithic ceramic, and possess lower density, better high-temperature durability strength and better designability compared with the superalloys, and are the ideal material for the new generation of aeroengine thermal structures. Since the 1980s, Europe and the United States and other developed countries after millions of hours of testing, assessment, and validation, has proved that revolutionary change as substituting a CMCs in place of a superalloy has come. This paper systematically analyzes different preparation processes and physical/mechanical properties of CMCs, the structural design, component assessment and engineering applications of CMCs in the hot-section components of aeroengines combustion chambers, turbines, and exhaust systems, and establishes the relationships between the CMCs preparation process, mechanical properties, component design and engineering applications. From the airworthiness point of view, the airworthiness certification requirements, airworthiness design and compliance validation methods of CMCs components are also given. Case studies were also conducted for the CMCs mixer and center body of SAFRAN (France) and the CMCs turbine shroud of GE (USA).