scholarly journals Life Modeling of Thermal Barrier Coatings for Aircraft Gas Turbine Engines

1989 ◽  
Vol 111 (2) ◽  
pp. 301-305 ◽  
Author(s):  
R. A. Miller
Keyword(s):  
Thermal Barrier Coatings ◽  
Failure Mechanisms ◽  
Turbine Engines ◽  
Laboratory Model ◽  
Thermal Barrier ◽  
Nasa Lewis Research ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Barrier Coating ◽  
Coating Failure

Thermal barrier coating life models developed under the NASA Lewis Research Center’s Hot Section Technology (HOST) program are summarized. An initial laboratory model and three design-capable models are discussed. Current understanding of coating failure mechanisms is also summarized.

Progress Toward Life Modeling of Thermal Barrier Coatings for Aircraft Gas Turbine Engines

1987 ◽  
Vol 109 (4) ◽  
pp. 448-451 ◽  
Author(s):  
R. A. Miller
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Failure Mechanisms ◽  
Current Understanding ◽  
Turbine Engines ◽  
Laboratory Model ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings

Progress toward developing life models for simulating the behavior of thermal barrier coatings in aircraft gas turbine engines is discussed. A preliminary laboratory model is described as are current efforts to develop engine-capable models. Current understanding into failure mechanisms is also summarized.

Thermal Barrier Coatings – Why, How, Where and Where To

1998 ◽  
Author(s):  
J. Wigren ◽  
L. Pejryd
Keyword(s):  
Thermal Conductivity ◽  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Thermal Efficiency ◽  
Failure Mechanisms ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings

Abstract Thermal barrier coatings are used in several industries to improve thermal efficiency. Examples are gas turbine engines and marine diesels. The performance and life of thermal barrier coated components depend on a variety of factors all related to the specific application. This paper gives an overview of some of the aspects to consider and put special attention to. The different features, in the microstructure, will be discussed with respect to their appearance and influence on the performance of the TBC. Thermal conductivity, microstructure, failure mechanisms and different applications are highlighted.

scholarly journals Thermal-barrier coatings for more efficient gas-turbine engines

MRS Bulletin ◽  
2012 ◽  
Vol 37 (10) ◽  
pp. 891-898 ◽  
Author(s):  
David R. Clarke ◽  
Matthias Oechsner ◽  
Nitin P. Padture
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Image Position

Abstract

Ceramic thermal barrier coatings for commercial gas turbine engines

JOM ◽  
1991 ◽  
Vol 43 (3) ◽  
pp. 50-53 ◽  
Author(s):  
Susan Manning Meier ◽  
Dinesh K. Gupta ◽  
Keith D. Sheffler
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings

scholarly journals Ceramic Thermal Barrier Coatings for Gas Turbine Engines

1982 ◽  
Author(s):  
R. J. Bratton ◽  
S. K. Lau ◽  
C. A. Andersson ◽  
S. Y. Lee
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Critical Role ◽  
Thick Layer ◽  
Ceramic Coatings ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Combustion Gases

Ceramic thermal barrier coatings are currently under active development in the U.S. for both aircraft and industrial/Utility gas turbine operation. These coating systems generally consist of an oxidation-corrosion resistant metal bond coat of the MCrAlY type and either a single thick layer ceramic overcoat or a graded ceramic/MCrAlY overcoat. This paper summarizes studies conducted on the high-temperature corrosion resistance of ZrO2 · Y2O3, ZrO2 · MgO and Ca2SiO4 plasma sprayed coatings that are candidates for use as thermal barrier coatings in gas turbine engines. Coatings were evaluated in both atmospheric burner rig and pressurized passage tests using GT No. 2 fuel and that doped with corrosive impurities such as sodium, sulfur and vanadium. The test results showed that the coatings perform very well in the clean fuel pressurized passage tests as well as burner rig tests. With impure fuels, it was found that chemical reactions between the ceramic coatings and combustion gases/condensates played the critical role in coating degradation. This work was conducted for NASA and EPRI under contract NAS3-21377. Advanced coating development studies have also been conducted for NASA and DOE under contract DEN3-110.

Overview on Double Ceramic Layer Thermal Barrier Coatings

2014 ◽  
Vol 1053 ◽  
pp. 364-372 ◽  
Author(s):  
Liang Liang Huang ◽  
Hui Min Meng ◽  
Jing Tang ◽  
Sen Li ◽  
Ze Qin Yu
Keyword(s):  
Thermal Barrier Coatings ◽  
Ceramic Layer ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Structure System ◽  
Existing Problems ◽  
Novel Structure ◽  
The Subject

Thermal barrier coatings (TBCs) system has been the subject of vigorous research over the past decade, driven by the demands for enhanced reliability and substantially higher operating temperature envisaged for the next generations of gas turbine engines. As a novel structure system, the double ceramic layer design is a promising TBCs structure system , especially its long thermal cycling lifetime compared with the single ceramic layer. This paper mainly reviewed of development situation and the existing problems of several mainly double ceramic layer thermal barrier systems, including M-YSZ/YSZ, A2B2O7/YSZ, LTA/YSZ, LnMA/YSZ, ABO3/YSZ and so on. Many challenges remain but healthy and growing collaborations between the science and technology communities bode well for future progress in this area.

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