Le système barrière thermique (BT) est utilisé pour protéger les aubes de turbines à gaz aéronautiques. Aux températures de fonctionnement, une des causes de l'endommagement du système barrière thermique est la dégradation de la couche céramique isolante en zircone yttriée (8YPSZ : ZrO2 - 4% mol. Y2O3) par corrosion. Celle-ci est due à des dépôts d'oxydes à base de Ca, Mg, Al, Si, appelés CMAS provenant de diverses particules ingérées par le moteur. A haute température (~1200°C), le CMAS fond et s'infiltre dans la microstructure poreuse de la BT, se rigidifie au refroidissement provoquant, à terme, la délamination de la BT. A haute température, la BT subit une corrosion chimique induisant sa dissolution dans le CMAS liquide. L'ensemble de ces deux phénomènes conduit à la perte d'intégrité de la barrière thermique. Le présent travail s'est focalisé sur la compréhension des mécanismes de dégradation chimique en vue de proposer une solution de protection contre l'infiltration par les CMAS. Après expertise d'aubes de turbines de retour de vol, une reproduction de la corrosion de la barrière thermique par un CMAS modèle de type CAS et une étude thermodynamique et cinétique de la dissolution de différents oxydes des systèmes ZrO2 - Y2O3 et ZrO2 - Nd2O3 ont été menées dans le verre silicaté CAS pour comprendre le processus de dissolution de Zr et Y et définir une nouvelle composition de barrière thermique anti-CMAS. Le comportement en corrosion par le CAS de matériaux céramiques denses de compositions ZrO2 - 12% mol Nd2O3 et Zr2Nd2O7 ainsi qu'un revêtement déposé par EB-PVD ((La, Nd)2Zr2O7) a été testée. Les résultats obtenus font apparaître que : i) le CAS réplique le mécanisme de corrosion en service, soit la dissolution-re-précipitation. ii) l'oxyde ZrO2 se dissout progressivement et forme le zircon (ZrSiO4) dans le verre CAS, dès 30 min iii) les dopants (Nd2O3 et Y2O3) conduisent à la formation très rapide, de la phase apatite X8Ca2(SiO4)6O2 (X = Nd ou Y) après réaction avec le verre silicaté. En plus de la phase apatite, Y2O3 forme la phase Ca3Y2Si6O18, qui est instable entre 1300°C et 1400°C. iv) les composés dopés au néodyme (ZrO2 - 12% mol Nd2O3 et Zr2Nd2O7) se dissolvent et conduisent, quasi-spontanément, à la phase apatite Nd8Ca2(SiO4)6O2 ainsi qu'à la re-précipitation de grains de ZrO2 appauvris en néodyme. v) malgré la présence de Y2O3, les composés ZrO2 - 4% mol Y2O3, ZrO2 - 10% mol Y2O3 ne conduisent qu'à la re-précipitation de la zircone appauvrie en Y2O3. L'absence de phases secondaires notamment, la phase apatite, pourrait expliquer l'infiltration facile du CMAS dans la microstructure de la barrière thermique en zircone yttriée. vi) l'inhibition avérée de l'infiltration du CAS dans la microstructure poreuse de couches céramiques de nouvelles compositions semble être due à la formation rapide d'une couche superficielle fine et dense, constituée de zircone appauvrie en dopant et de phase apatite / Thermal barrier coating (TBC) system is used to protect aeronautical gas turbine blades. At operating temperatures, one of the damaging causes of thermal barrier system is the degradation of the insulating ceramic layer in zirconia (8YPSZ: ZrO2 - 4 mol %. Y2O3) by corrosion. The corrosion is due to calcium - magnesium alumino-silicates (CMAS) deposits from various particles ingested by the engine. At high temperature (~ 1200°C), the molten CMAS infiltrates the porous microstructure of the thermal barrier leads to i) the chemical dissolution of the thermal barrier zirconia and ii) the delamination of the TBC after cracking at low temperature due to the mismatch of CTE of the solid oxides constituting the CMAS and TBC. This study has contributed to understanding the mechanisms of chemical degradation in order to propose a solution to protect against infiltration by CMAS. After expertise of ex-service turbine blades, a reproduction of the thermal barrier corrosion by model CMAS (CAS) and thermodynamic and kinetic study of the solubility of different oxides of both ZrO2-Y2O3 and ZrO2-Nd2O3 systems were performed in the silicate glass (CAS) in order to understand the mechanism of Zr and Y dissolution and to define a new composition of TBC. The corrosion by the CAS of dense ceramic (ZrO2 - 12 mol% Nd2O3 and Zr2Nd2O7) and of a EB-PVD coating (La, Nd)2Zr2O7)was studied. The results obtained show that: i) CAS replicates the corrosion mechanism, i.e. dissolution-re-precipitation reaction ii) ZrO2 oxide dissolves gradually and forms zircon (ZrSiO4) in the glass after 30 min iii) (Nd2O3 and Y2O3) oxides lead very rapidly to the apatite X8Ca2(SiO4)6O2 (X = Nd, Y) phase formation, after reaction with silicate glass. In addition to the apatite phase, Y2O3 forms Ca3Y2Si6O18 phase, which is unstable at 1300°C and 1400°C iv) the compounds doped with Nd2O3 (ZrO2 - 12 mol% Nd2O3 and Zr2Nd2O7) dissolve and form almost spontaneously, the apatite Nd8Ca2(SiO4)6O2 phase and the ZrO2 depleted in Nd2O3 grains v) Although Y2O3 is a constitutent of the compounds ZrO2 - 4 mol% Y2O3, ZrO2 - 10 mol% Y2O3, the chemical corrosion of these compounds leads only to the re-precipitation of zirconia depleted Y2O3. The absence of secondary phases, particularly the apatite phase may explain the easy CMAS infiltration in the microstructure of the 8YPSZ thermal barrier vi) inhibition of CAS infiltration into the porous microstructure of ceramic layers of new compositions seems to be due to the rapid formation of a thin and dense layer, consisting in Nd-depleted zirconia and apatite phase

Thermal barrier coatings (TBC) are used in the hot sections of gas turbine engine in order to insulate the substrate at high temperature. Molten salt infiltration retards the durability of TBCs. The current standard material, i.e. 8YSZ is susceptible to molten salt infiltration. Therefore, alternate TBC materials are desirable. In addition to material composition, the TBC microstructure plays an important role in mitigating molten salt infiltration. Therefore, in this work, three different TBC variations were investigated. The first variation was a columnar microstructured 48YSZ TBC processed by SPS (48YSZ-SPS). The second variation was a columnar microstructured 8YSZ TBC processed by SPS (8YSZ-SPS), and the third variation was a lamellar microstructured 8YSZ TBC deposited by APS (8YSZ-APS). The as-sprayed TBC specimens were characterized by SEM/EDS, porosity analysis and XRD measurements. Later, the TBC specimens were exposed to hot corrosion test and their interaction with the molten salts were investigated using SEM (EDS and XRD). It was shown that an increase in stabilizer content (yttria content) in zirconia (in the case of 48YSZ) leads to an improved hot corrosion resistance due to the adequate amount of yttria content, which restricts the molten salt infiltration by forming needle like YVO4 phase. In terms of microstructure comparison, the infiltration behavior was similar for columnar microstructured 8YSZ and lamellar microstructured 8YSZ-APS as the molten salts infiltrated the coatings completely compared to the 48YSZ TBC. Furthermore, it seems that the molten salt infiltrates the TBC through globular pores, delamination cracks and splat boundaries in the case of APS-TBCs whereas the column gaps favor easier infiltration of molten salts in the case of columnar microstructured SPS processed TBCs.

This document describes work performed related to the determination of how elemental additions affect the interfacial fracture toughness of thermal barrier coatings at the bond coat/thermally grown oxide interface in gas turbines. These turbines are exposed to cyclical thermal loading, therefore a simulation was designed to model this interface in a temperature cycle between 200 K and 1000 K that included oxide growth between 2 μm and 27 μm. The fracture toughness of this interface was then determined to elucidate the function of elemental additions. It was shown that minimal concentrations of atomic species, such as hafnium and yttrium cause notable increases in the toughness of the bond coat/thermally grown oxide interface, while other species, such as sulphur, can dramatically reduce the toughness. Furthermore, it was shown that, contrary to some empirical results, the addition of platinum has a negligible effect on the fracture toughness of this interface.

Because of their good mechanical resistance at high temperature, Ni-based superalloys are used for aero-engine and land-based turbines but undergo "dry" oxidation between 900 and 1500°C. These materials are thus coated with nickel-aluminide coatings (BC). An additional thermal barrier coating (TBC) is generally applied in the hottest sections of the turbines (T>1050°C) to lower the impact of the temperature on the substrate. In the framework of the European research programme "PARTICOAT", this PhD work was focused on the growth mechanisms of a full protective coating system (BC+TBC) in a single step process, using a water-based slurry containing a dispersion of Al micro-particles to satisfy the European environmental directives. The rheological and physico-chemical characterizations showed the slurry stability up to seven days. After depositing the latter by air spraying, a tailored thermal treatment resulted in a nickel-aluminide coating (β-NiAl) similar to the conventional industrial ones but through an intermediate Al liquid phase stage. Simultaneously, the oxidation of the Al micro-particles brought aboutthe formation of a top alumina "foam" (PARTICOAT concept). After a validation step of the mechanisms involved in pure Ni substrate, the extrapolation of the process to several Ni-based superalloys (René N5 (SX), CM-247 (DS), PWA- 1483 (SX) and IN-738LC (EQ)) revealed different coating compositions and microstructures. A particular attention was therefore paid onto the effect of alloying elements (Cr, Ta, Ti) as well as their segregation in the coating. The high temperature behaviour of the coated samples has been studied through isothermal oxidation (1000h in air between 900 and 1100°C) and showed that the oxidation and interdiffusion phenomena ruled the degradation mechanisms. Besides, the electrodeposition of ceria before the application of the PARTICOAT coating allowed to strongly limit interdiffusion phenomena and stabilized the nickel aluminide coating.

<p>Thermal barrier coatings (TBC) are used for reduction of component temperatures in gas turbines. The service temperature for turbines can be as high as 1100ºC and the components are exposed to thermal cycling and gases that will cause the component to oxidize and corrode. The coatings are designed to protect the substrate material from this, but eventually it will lead to failure of the TBC. It is important to have knowledge about when this failure is expected, since it is detrimental for the gas turbine.</p><p>The scope of this thesis has been to see if an existing life model for thin TBC also is valid for thick TBC. In order to do so, a thermal cycling fatigue test, a tensile test and finite element calculation have been performed. The thermal cycling fatigue test and finite element calculation were done to find correlations between the damage due to thermal cycling, the number of thermal cycles and the energy release rate. The tensile test was preformed to find the amount accumulated strain until damage.</p><p>The thermal cycling lead to failure of the TBC at the bond coat/top coat interface. The measurment of damage, porosity and thickness of thermally grown oxide were unsatisfying due to problems with the specimen preparation. However, a tendency for the damage development were seen. The finite element calculations gave values for the energy release rate the stress intensity factors in mode~I and mode~II that can be used in the life model. The tensile test showed that the failure mechanism is dependent of the coating thickness and it gave a rough value of the maximum strain acceptable.</p>

Approximately 10% of all energy consumed in the United States is derived from high temperature gas turbine engines. As a result, a 1% increase in engine efficiency would yield enough energy to satisfy the demands of approximately 1 million homes and savings of over $800 million in fuel costs per year. Efficiency of gas turbine engines can be improved by increasing the combustor temperature. Modern engines now operate at temperatures that far exceed the material limitations of the metals they are comprised of in the pursuit of increased thermal efficiency. Various techniques to thermally protect the turbine components are used to allow for safe operation of the engines despite the extreme environments: film cooling, internal convective cooling, and thermal barrier coatings. Historically, these thermal protection techniques have been studied separately without account for any conjugate effects. The end goal of this work is to provide a greater understanding of how the conjugate effects might alter the predictions of thermal behavior and consequently improve engine designs to pursue increased efficiency. The primary focus of this study was to complete the first open literature, high resolution experiments of a modeled first stage turbine vane with both active film cooling and a simulated thermal barrier coating (TBC). This was accomplished by scaling the thermal behavior of a real engine component to the model vane using the matched Biot number method. Various film cooling configurations were tested on both the suction and pressure side of the model vane including: round holes, craters, traditional trenches and a novel modified trench. IR thermography and ribbon thermocouples were used to measure the surface temperature of the TBC and the temperature at the interface of the TBC and vane wall, respectively. This work found that the presence of a TBC significantly dampens the effect of altering film cooling conditions when measuring the TBC interface temperature. This work also found that in certain conditions adiabatic effectiveness does not provide an accurate assessment of how a film cooling design may perform in a real engine. An additional focus of this work was to understand how contaminant deposition alters the cooling performance of a vane with a TBC. This work focused on quantifying the detrimental effects of active deposition by seeding the mainstream flow of the test facility with simulated molten coal ash. It was found that in most cases, except for round holes operating at relatively high blowing ratios, the performance of film cooling was negatively altered by the presence of contaminant deposition. However, the cooling performance at the interface of the TBC and vane wall actually improved with deposition due to the additional thermal resistance that was added to the exterior surface of the model vane. / text

From many years YSZ is used as the top coat material for TBC's, as it has good phase stability up to 1200°C, higher fracture toughness, lower thermal conductivity, erosion resistance &amp; higher coefficient of thermal expansion. But, it has a drawbacks at high temperature such as sintering and transformation of phases. For this reason new ceramic materials with pyrochlores crystal structure such as Gd2Zr2O7 are being considered as it has high melting points, phase stability, lower thermal conductivity and CMAS resistance. But it has low fracture toughness when compared to YSZ. In order to take advantage of low thermal conductivity and high thermal stability of gadolinium zirconate and avoiding the drawbacks of low coefficient of thermal expansion and low toughness using YSZ, a double/multi-layer coatings approach is being used. Therefore, multi-layer TBCs are sprayed and compared with single layer coating in this work. These coatings are processed by suspension plasma spraying. For single layer coating YSZ is used, for double layer coating YSZ as the intermediate coating and Gd2Zr2O7 as the top coat is used. Additionally, a triple layer coating system comprising YSZ, Gd2Zr2O7 and dense Gd2Zr2O7 as top coat is also sprayed. The as sprayed coatings are characterized for microstructure analysis using optical microscope and scanning electron microscope (SEM), elemental analysis of TGO using Energy-Dispersive Spectrometer (EDS). XRD analysis was done to identify various phases in the coating. Porosity analysis using Archimedes principle was carried out. Thermal cyclic fatigue (TCF) test of the sprayed coatings was carried out at 1100°C. Failure analysis of the TCF specimens was carried out using SEM/EDS. TCF results showed that the triple layer coatings (dense Gd2Zr2O7/Gd2Zr2O7/YSZ) had higher thermal cyclic fatigue life and lower TGO thickness when compared to single layer (YSZ) and double layer (Gd2Zr2O7/YSZ) TBCs.

Thermal barrier coatings (TBC) are used for reduction of component temperatures in gas turbines. The service temperature for turbines can be as high as 1100ºC and the components are exposed to thermal cycling and gases that will cause the component to oxidize and corrode. The coatings are designed to protect the substrate material from this, but eventually it will lead to failure of the TBC. It is important to have knowledge about when this failure is expected, since it is detrimental for the gas turbine. The scope of this thesis has been to see if an existing life model for thin TBC also is valid for thick TBC. In order to do so, a thermal cycling fatigue test, a tensile test and finite element calculation have been performed. The thermal cycling fatigue test and finite element calculation were done to find correlations between the damage due to thermal cycling, the number of thermal cycles and the energy release rate. The tensile test was preformed to find the amount accumulated strain until damage. The thermal cycling lead to failure of the TBC at the bond coat/top coat interface. The measurment of damage, porosity and thickness of thermally grown oxide were unsatisfying due to problems with the specimen preparation. However, a tendency for the damage development were seen. The finite element calculations gave values for the energy release rate the stress intensity factors in mode~I and mode~II that can be used in the life model. The tensile test showed that the failure mechanism is dependent of the coating thickness and it gave a rough value of the maximum strain acceptable.

This document describes work performed related to the determination of how elemental additions affect the interfacial fracture toughness of thermal barrier coatings at the bond coat/thermally grown oxide interface in gas turbines. These turbines are exposed to cyclical thermal loading, therefore a simulation was designed to model this interface in a temperature cycle between 200 K and 1000 K that included oxide growth between 2 μm and 27 μm. The fracture toughness of this interface was then determined to elucidate the function of elemental additions. It was shown that minimal concentrations of atomic species, such as hafnium and yttrium cause notable increases in the toughness of the bond coat/thermally grown oxide interface, while other species, such as sulphur, can dramatically reduce the toughness. Furthermore, it was shown that, contrary to some empirical results, the addition of platinum has a negligible effect on the fracture toughness of this interface.

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