Single crystal high-temperature alloy

Single crystal alloy materials have developed to the fourth generation, with a temperature bearing capacity increased to 1140 degree , approaching the temperature limit of metal materials. In the future, it is necessary to further meet the needs of advanced aeroengines, further expand the development of blade materials, and ceramic matrix composite are expected to replace single crystal superalloys to meet the use of hot end components at higher temperatures.
The difficulty and cycle of developing single crystal high-temperature alloy blades are related to their structural complexity. Single crystal blades with ordinary complexity have a shorter development cycle, but their application in aviation engines also requires a longer time. From single crystal solid blades to single crystal hollow blades, to high-efficiency air-cooled complex hollow blades, the technical difficulty span is large, and the corresponding development cycle span is also large. Generally, a single crystal hollow blade with ordinary complexity takes 1-2 years from drawing confirmation, mold design to trial production, and then to small-scale production. However, due to the complex service environment of single crystal blades, a large number of validation tests are required. Generally, a single crystal hollow blade with a common structure takes 5-10 years from development to application in aviation engines, and some may even take 15 years or more as the engine development progresses