Thermal barrier coatings for enhanced efficiency of gas turbine engines

Gurrappa, I.; Rao, A. Sambasiva

doi:10.1016/j.surfcoat.2006.06.026

Cited by 124 publications

(46 citation statements)

References 32 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Thus, the hot corrosion resistance of superalloys is as important as its high temperature strength in marine gas turbine engine applications [5][6][7][8]. Recent studies have shown that the high temperature strength materials are most susceptible to hot corrosion and the surface engineering plays a key role in effectively combating the hot corrosion problem [9][10][11][12][13].…”

Section: Fig 2 Failed Gas Turbine Blade Due To Type I and Ii Hot Comentioning

confidence: 99%

The Selection of Materials for Marine Gas Turbine Engines

Gurrappa¹,

Yashwanth²,

Gogia³

2012

Efficiency, Performance and Robustness of Gas Turbines

Self Cite

View full text Add to dashboard Cite

Section: Fig 2 Failed Gas Turbine Blade Due To Type I and Ii Hot Comentioning

confidence: 99%

The Selection of Materials for Marine Gas Turbine Engines

Gurrappa¹,

Yashwanth²,

Gogia³

2012

Efficiency, Performance and Robustness of Gas Turbines

Self Cite

View full text Add to dashboard Cite

“…Significant sintering and phase transformation were observed, and localized spallation of yttria partially stabilized zirconia (YSZ) was found near the tip of the serviced blade. Gurrappa and Rao [17] conducted the hot corrosion experiments on cylindrical specimens having various TBCs thicknesses and figured out that an optimum thickness of TBCs can enhance the life of underlying superalloy by about six hundred times. Yang et al [18] developed finite element (FE) model for the blade with TBCs to investigate the failure behavior under cyclic thermal loading.…”

Section: Introductionmentioning

confidence: 99%

Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis

Fan

et al. 2017

Mathematical Problems in Engineering

View full text Add to dashboard Cite

Thermal barrier coatings (TBCs) are deposited on the turbine blade to reduce the temperature of underlying substrate, as well as providing protection against the oxidation and hot corrosion from high temperature gas. Optimal ceramic top-coat thickness distribution on the blade can improve the performance and efficiency of the coatings. Design of the coatings thickness is a multiobjective optimization problem due to the conflicts among objectives of high thermal insulation performance, long operation durability, and low fabrication cost. This work developed a procedure for designing the TBCs thickness distribution for the gas turbine blade. Three-dimensional finite element models were built and analyzed, and weighted-sum approach was employed to solve the multiobjective optimization problem herein. Suitable multiregion top-coat thickness distribution scheme was designed with the considerations of manufacturing accuracy, productivity, and fabrication cost.

show abstract

“…Hitherto, only a few ceramic materials had been found to basically satisfy the basic requirements of thermal barrier coating, and among these materials Yttria Stablized Zirconia (YSZ) is the most generally used and studied material for thermal barrier coating application due to its excellent performance capabilities in applications operating under severe temperature condition like gas turbine and diesel engines [16][17][18][19]. Many applications including but not restricted to automotive industry, gas turbine, nuclear industries, aerospace and heavy-duty utilities such as diesel trucks have benefited from one of thermal barrier coating techniques [20][21][22][23][24][25][26][27][28][29][30]. Functionally graded thermal barrier coating (FG-TBC) is a new thermal barrier coating technique consisting of non-homogeneous materials whose composition and microstructure are varied according to a predetermined profile in order to enhance its thermo-mechanical properties and reduced spallation problems occurring in thermal barrier coated engineering materials [31][32][33].…”

Section: Introductionmentioning

confidence: 99%

Solvent Based Slurry Functional Graded Thermal Barrier Coating for Application in Automotive Turbocharger Turbine Volute Casing

Mohd¹,

Rabiu²,

Uday³

2016

Fifth International Conference on Advances in Mechanical, Aeronautical and Production Techniques - MAPT 2016

View full text Add to dashboard Cite

Abstract-Tremendous amount of heat is being lost at the turbine area of an automotive turbocharger during its operation. Application of ceramic thermal barrier coating to components operating under severe temperature condition such as automotive turbocharger turbine volute casing can reduce the heat lost to the environment, improve the efficiency and reliability of components and extend their service life. But high cost of installation and maintenance, complexity and spallation problem due to thermal expansion mismatch between the ceramic and the metal substrate have seriously restricted the acceptance and widespread practice of ceramic thermal barrier coating. In the present study, a solvent based slurry functionally graded thermal barrier coating technique was employed in depositing different compositions of Yttria stabilized zirconia and nickel powders on a nickel alloy substrate using a simple laboratory-scale surface coating machine. The coating compositions of 25wt% YSZ & 75wt% Ni, 60wt% YSZ & 40wt% Ni and 75wt% YSZ & 25wt% Ni were used for the deposition of the first layer, second layer and third layer of the functionally graded coating on the nickel substrate respectively. Experimental validation of heat transfer across the coating and adhesion tests were used to evaluate the suitability and integrity of the functionally graded coating produced for the intended application. The coating microstructure was also analyzed using optical microscope, scanning electron microscopy (SEM) and energy dispersive X-ray (EDX). The results have shown that, the functionally graded coating produced has the heat resistance capability of 35 0 C, 140 0 C and 250 0 C for one layer, two layer and three layer respectively. The adhesion strength of the coating improved with an increase in the number of the coating layers. There was no spallation problem observed from the coating, also no crack or deformation was observed from the results of the microstructural analysis of the functionally graded coating after the experimental heat transfer tests.

show abstract

Thermal barrier coatings for enhanced efficiency of gas turbine engines

Cited by 124 publications

References 32 publications

The Selection of Materials for Marine Gas Turbine Engines

The Selection of Materials for Marine Gas Turbine Engines

Design of Thermal Barrier Coatings Thickness for Gas Turbine Blade Based on Finite Element Analysis

Solvent Based Slurry Functional Graded Thermal Barrier Coating for Application in Automotive Turbocharger Turbine Volute Casing

Contact Info

Product

Resources

About