scholarly journals Zirconia and Pyrochlore Oxides for Thermal Barrier Coatings in Gas Turbine Engines

2014 ◽  
Vol 1 (2) ◽  
pp. 118-131 ◽  
Author(s):  
Jeffrey W. Fergus
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Pyrochlore Oxides

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.

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.

scholarly journals Microstructure Based Material-Sand Particulate Interactions and Assessment of Coatings for High Temperature Turbine Blades

2017 ◽  
Author(s):  
Muthuvel Murugan ◽  
Anindya Ghoshal ◽  
Michael Walock ◽  
Andy Nieto ◽  
Luis Bravo ◽  
...  
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Thermal Barrier Coatings ◽  
Turbine Blades ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Barrier Coatings ◽  
Turbine Engine

Gas turbine engines for military/commercial fixed-wing and rotary wing aircraft use thermal barrier coatings in the high-temperature sections of the engine for improved efficiency and power. The desire to further make improvements in gas turbine engine efficiency and high power-density is driving the research and development of thermal barrier coatings with the goal of improving their tolerance to fine foreign particulates that may be contained in the intake air. Both commercial and military aircraft engines often are required to operate over sandy regions such as in the middle-east nations, as well as over volcanic zones. For rotorcraft gas turbine engines, the sand ingestion is adverse during take-off, hovering near ground, and landing conditions. Although most of the rotorcraft gas turbine engines are fitted with inlet particle separators, they are not 100% efficient in filtering fine sand particles of size 75 microns or below. The presence of these fine solid particles in the working fluid medium has an adverse effect on the durability of turbine blade thermal barrier coatings and overall performance of the engine. Typical turbine blade damage includes blade coating wear, sand glazing, Calcia-Magnesia-Alumina-Silicate (CMAS) attack, oxidation, and plugged cooling holes, all of which can cause rapid performance deterioration including loss of aircraft. The objective of this research is to understand the fine particle interactions with typical turbine blade ceramic coatings at the microstructure level. Finite-element based microstructure modeling and analysis has been performed to investigate particle-surface interactions, and restitution characteristics. Experimentally, a set of tailored thermal barrier coatings and surface treatments were down-selected through hot burner rig tests and then applied to first stage nozzle vanes of the gas generator turbine of a typical rotorcraft gas turbine engine. Laser Doppler velocity measurements were performed during hot burner rig testing to determine sand particle incoming velocities and their rebound characteristics upon impact on coated material targets. Further, engine sand ingestion tests were carried out to test the CMAS tolerance of the coated nozzle vanes. The findings from this on-going collaborative research to develop the next-gen sand tolerant coatings for turbine blades are presented in this paper.

The Effects of Environmental Contaminants on Industrial Gas Turbine Thermal Barrier Coatings

1996 ◽  
Author(s):  
H. E. Eaton ◽  
N. S. Bornstein ◽  
J. T. DeMasi-Marcin
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Gas Turbines ◽  
Chemical Properties ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Silicon Iron ◽  
Barrier Coatings ◽  
Industrial Gas Turbine

Thermal barrier coatings, (TBCs) play a crucial role in the performance of advanced aircraft gas turbine engines that power the commercial and military fleets. The same technology is currently being applied to the industrial gas turbines. However the task is more challenging. The environment of the industrial gas turbine is far more demanding. Studies are in progress delineating the relationships between time, temperature and the sinterability of candidate ceramics for use in industrial gas turbine engines. Typical sintering aids include the oxides and alkali salts of silicon, iron, magnesium and calcium. Other experiments focus on the role of the alkali compounds as they affect the mechanical and chemical properties of candidate materials.

scholarly journals Al2O3-modified PS-PVD 7YSZ thermal barrier coatings for advanced gas-turbine engines

2020 ◽  
Vol 4 (1) ◽  
Author(s):  
Xiaofeng Zhang ◽  
Ziqian Deng ◽  
Hong Li ◽  
Jie Mao ◽  
Chunming Deng ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coatings ◽  
Plasma Spray ◽  
Physical Vapor Deposition ◽  
Atmospheric Plasma ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
High Deposition Rate ◽  
Gas Turbine Engines ◽  
Barrier Coatings

Abstract Plasma spray-physical vapor deposition (PS-PVD), called the third-generation method for thermal barrier coatings (TBCs) fabrication, has great potential for their using in gas-turbine engines. Compared to atmospheric plasma spray (APS), called the first-generation TBCs, and electron beam-PVD (EB-PVD), called the second generation, PS-PVD has many interesting features, including non-line sight deposition, high deposition rate, and microstructural flexibility, among others. Such advantages make them a promising approach to prepare thermal barrier coatings for advanced gas-turbine engines. Using PS-PVD, feather-like columnar TBCs with good strain tolerance and low thermal conductivity can be fabricated. However, prior to their application in gas-turbine engines, some disadvantages, such as CMAS (CaO–MgO–Al2O3–SiO2, etc.) corrosion and oxidation resistance, need to be addressed. In this work, a method to develop Al2O3-modified PS-PVD 7YSZ TBCs was proposed. The experimental results demonstrate that the Al2O3-modification process is an effective approach to address the aforementioned weaknesses of traditional PS-PVD 7YSZ TBCs.

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