WikiVisually
The entire wiki reimagined as a visual magazine with video discovery · Watch your interests come alive
WikiVisually
The entire wiki reimagined as a visual magazine with video discovery · Watch your interests come alive
Nature The World Movies USA Top Art Fine & Rare History Ivy & Inquiry
Thermal barrier coating
Videos
Thermal barrier coatings are advanced materials systems usually applied to metallic surfaces on parts operating at elevated temperatures, such as gas turbine combustors and turbines, and in automotive
Thermal barrier coating (colored white) on a turbine guide vane in a V2500 turbofan engine
Thermal barrier coating (colored white) on a turbine guide vane in a V2500 turbofan engine
Observe that if columns are placed on a curved surface, normal to that surface, then column density will necessarily be high above valleys in the surf
Observe that if columns are placed on a curved surface, normal to that surface, then column density will necessarily be high above valleys in the surface and low above peaks in the surface due to the tilting of the straight rods.
Thermal barrier coating on an automotive exhaust system component
Thermal barrier coating on an automotive exhaust system component
Thermal barrier coating on a carbon composite material
Thermal barrier coating on a carbon composite material
Turbine blade
Videos
A turbine blade is a radial aerofoil mounted in the rim of a turbine disc and which produces a tangential force which rotates a turbine rotor. Each turbine disc has many blades. As such they are used
Thermal barrier coating
…strong. In fact, the repeated thermal shocks associated with turning the engine on and off many times is a main contributor to failure of TBC-coated turbine blades in airplanes. Over the course of repeated cycles of rapid heating and cooling, thermal shock leads to significant tensile strains perpendicular to the…
Turbine blade from a Turbo-Union RB199 jet engine. This is a blade with an outer shroud which prevents gas leaking round the blade tip in which case i
Turbine blade from a Turbo-Union RB199 jet engine. This is a blade with an outer shroud which prevents gas leaking round the blade tip in which case it wouldn't contribute to the force on the aerofoil. The platform at the base of the aerofoil forms a continuous annulus ring which, together with cooling-air cavity purge flow prevents hot gas leakage onto the turbine discs. The short extension, or shank, between the platform and fir-tree fixing in the disc allows space for cooling-air entry to blade, may control blade vibration modes and heat transfer to disc rim.
The turbine blades have a golden colour in this engine cutaway.
The turbine blades have a golden colour in this engine cutaway.
A turbine blade with thermal barrier coating. This blade has no tip shroud so tip leakage is controlled by the clearance between the tip and a station
A turbine blade with thermal barrier coating. This blade has no tip shroud so tip leakage is controlled by the clearance between the tip and a stationary shroud ring attached to the turbine case.
Laser-drilled holes permit film cooling in this first-stage V2500 nozzle guide vane.
Laser-drilled holes permit film cooling in this first-stage V2500 nozzle guide vane.