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 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.

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.

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.

Sign in / Sign up

Export Citation Format

Share Document