The Evolution of Thermal Barrier Coatings in Gas Turbine Engine Applications

  title={The Evolution of Thermal Barrier Coatings in Gas Turbine Engine Applications},
  author={Susan Manning Meier and Dinesh Kumar Gupta},
  journal={Journal of Engineering for Gas Turbines and Power-transactions of The Asme},
  • S. Meier, D. K. Gupta
  • Published 1 June 1992
  • Materials Science
  • Journal of Engineering for Gas Turbines and Power-transactions of The Asme
Thermal barrier coatings (TBCs) have been used for almost three decades to extend the life of combustors and augmentors and, more recently, stationary turbine components. Plasma-sprayed yttria-stabilized zirconia TBC currently is bill-of-material on many commercial jet engine parts. A more durable electron beam-physical vapor deposited (EB-PVD) ceramic coating recently has been developed for more demanding rotating as well as stationary turbine components. This ceramic EB-PVD is bill-of… 
Erosion of thermal barrier coatings
Abstract Thermal barrier coatings have been used within gas turbines for over 30 years to extend the life of hot section components. Thermally sprayed ceramics were the first to be introduced and are
Thermal barrier coating experience in gas turbine engines at Pratt & Whitney
Pratt & Whitney has accumulated more than three decades of experience with thermal barrier coatings (TBCs). These coatings were originally developed to reduce surface temperatures of combustors of
Thermal Barrier Coatings—A State of the Art Review
Abstract Thermal barrier coatings (TBCs) have seen considerable advancement since the initial testing and development of thermal spray coating. Thermal barrier coatings are currently been utilized in
Low Thermal Conductivity Coatings for Gas Turbine Applications
Plasma spraying of thermal barrier coatings (TBCs) on gas turbine parts is widely used today either to enable higher-turbine inlet temperatures with consequent improvement of combustion efficiency or
High Temperature Oxidation Behavior of Thermal Barrier Coatings
In power generating gas turbine plants, increasing turbine inlet gas temperature (TIT) results in enhancement of turbine efficiency and energy saving. State-of-the-art gas turbine plants aiming at
Thermocyclic Behavior of Variously Stabilized EB-PVD Thermal Barrier Coatings
The demand for increasing gas inlet temperatures in modern gas turbines up to 1500°C and above is the main reason for the need for more reliable thermal barrier coatings. New ceramics should provide
A review of the erosion of thermal barrier coatings
The application of thermal barrier coatings (TBCs) to components with internal cooling in the hot gas stream of gas turbine engines has facilitated a steep increase in the turbine entry temperature
High Temperature Erosion Properties of Yttria Stabalised Zirconia Thermal Barrier Coatings Using the High Velocity Oxygen Fuel Process With Acetylene.
The development of thermal barrier coatings for surface protection of components exposed to high temperature engine service has been a critical and significant requirement in the advancement of
Study on EB-PVD Zirconia Thermal Barrier Coatings for Gas Turbine Blade Protection
Abstract Thermal barrier coatings on hollow turbine blades of DD3 were studied. The DD3 single crystal alloy has excellent mechanical properties, equivalent to that of PWA 1480. The results show that


Ceramic thermal barrier coatings for commercial gas turbine engines
Thermal barrier coatings have been used for over 20 years to extend the durability of aircraft gas turbine engine combustors. Improvements to the chemical composition of the ceramic and to the
Ceramic Thermal Barrier Coatings for Turbine Engine Components
The durability of plasma sprayed ceramic thermal barrier coatings subjected to cyclic thermal environments has been improved substantially by improving the strain tolerance of the ceramic structure
Thermal Barrier Coating Life Prediction Model Development
A methodology is established to predict thermal barrier coating life in a environment similar to that experienced by gas turbine airfoils. Experiments were conducted to determine failure modes of the
Durability of zirconia thermal-barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation
Thermal barrier ceramic coatings of stabilized zirconia over a bond coat of Ni Cr Al Y were tested for durability on air cooled turbine rotor blades in a research turbojet engine. Zirconia stabilized
Mechanisms of degradation and failure in a plasma deposited thermal barrier coating
This paper describes and attempts to explain unusual constitutive behavior observed in the insulative ceramic coating layer, and presents details of the ceramic cracking damage accumulation process,
Mechanisms of Degradation and Failure in a PlasmaDeposited Thermal Barrier Coating," Journal of Engineering for Gas Turbines
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