SiC/SiC has excellent heat resistance and will replace superalloy in the application of aero-engine
High thrust-to-weight ratio is the goal of advanced aero-engines. However, with the increase of thrust-to-weight ratio, turbine inlet temperature keeps increasing, and the existing superalloy material system is difficult to meet the requirements of advanced aero-engines. For example, the turbine inlet temperature of existing engines with thrust-to-weight ratio of level 10 has reached 1500℃, while the average inlet temperature of engines with thrust-to-weight ratio of 12~15 will exceed 1800℃, which is far beyond the service temperature of superalloys and intermetallic compounds.
At present, the nickel-based superalloy with the best heat resistance can only reach about 1100℃. The service temperature of SiC/SiC can be increased to 1650℃, which is considered as the most ideal aero-engine hot end structure material.
In Europe and the United States and other aviation developed countries, SiC/SiC has been practical application and mass production in the aero-engine stationary parts, including M53-2, M88, M88-2, F100, F119, EJ200, F414, F110, F136 and other types of military/civil aero-engines; The application of rotating parts is still in the stage of development and test. The basic research in China started slowly, and there is a huge gap between it and the engineering applied research in foreign countries, but it has also made achievements.
In January 2022, a new kind of ceramic matrix composite is by northwestern polytechnical university using domestic materials to build aircraft engine turbine disc whole successful completion of the first flight test, it is also the first time a domestic ceramic matrix composite rotor equipped with air flight test platform, but also to promote the ceramic matrix composites components on the unmanned aerial vehicle (uav)/drone large-scale application.
Post time: Aug-23-2022