In the 1950s, to enhance the service life of turbine engine blades, the use of coatings to prevent chlorine spalling of the blades appeared, with Dipaluminized coatings first used on Allison or Curtiss Wright engines, and by 1957 research was being conducted to see if Aluminizing could prolong the service life of Co-based airfoils and blades. by 1957 it was being investigated whether aluminizing technology could extend the life of Co-based wings and blades.
In the 1960s, various high temperature alloys such as Inco713, IN100, B1900, etc., which have poor corrosion resistance and need to be plated with diffusion coatings for use on wings, began to develop and apply NiAl-based aluminized coatings, which belong to the first generation of coatings.
Coating preparation technology in the 1970s almost entirely by the penetration of plating technology (Packcementation) to replace the development of improved alumina coating, belonging to the second generation of coatings, the purpose of which is to try to reduce the coating and the substrate of the mutual diffusion, to strengthen the diffusion barrier in order to improve the coating of the use of the temperature of the coatings, which coatings are widely used in aircraft engines.
In the 1980s there can be adjusted to the composition of the coating can play a role in higher temperatures under the antioxidant MCrAlY coatings, to overcome the weakness of the traditional aluminum composite coatings and the substrate between the mutual constraints of the coating in the coating by adding X (Si, Hf or y) and other elements to further improve the antioxidant ability of the base metal MCrAIY coatings were first applied to aircraft engines, and then in the industrial engine and the military spacecraft also began to use. military spacecraft also began to be used.
Ceramic thermal barrier coatings developed in the 1990s using physical vapor deposition methods can provide significant thermal insulation through a thin layer of ceramic coating. However, due to the brittleness of ceramic materials and the thermal expansion mismatch with the base metal materials, a bonding layer is usually added between the ceramic and the base to improve the physical compatibility between the ceramic and the base.

Room termperature curing polysilazane, pls check IOTA 9150, IOTA 9150A. 
High termperature curing polysilazane, pls check IOTA 9108, IOTA 9118.