Thermal Barrier Coatings for Turbine Hot-Section Components

The Challenge

Combustion liners, transition pieces, nozzle vanes, and shrouds in turbine hot sections operate under extreme combustion temperatures.

Standard metallic coatings can oxidize or lose strength under these conditions, limiting achievable operating temperatures and reducing component service life.

The Solution

Plasma Spray Processors applies a duplex thermal barrier coating (TBC) system consisting of an 8% yttria-stabilized zirconia (YSZ) ceramic top coat over an MCrAlY bond coat.

The engineered porosity within the ceramic layer provides low thermal conductivity and excellent strain tolerance during repeated thermal cycling.

• Duplex coating system with 8% YSZ ceramic top coat and MCrAlY bond coat.
• Engineered porosity for low thermal conductivity and cyclic strain tolerance.
• Applied using robotic APS technology for consistent coating thickness and quality.

The Result

• Higher allowable operating temperatures for turbine hot-section components.
• Extended service life for combustion liners, transition pieces, nozzle vanes, and shrouds.
• Thermal gradient across the coating protects the base alloy from extreme heat exposure.
• Improved durability and reliability in demanding power generation and aerospace applications.