Relevant bibliographies by topics / Blade coating

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Blade coating'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Blade coating"

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Qu, Bin, Zhou Sun, Fang Feng, Yan Li, Guoqiang Tong, and Rana Shahzad Noor. "Preparation and Anti-Icing of Hydrophobic Polypyrrole Coatings on Wind Turbine Blade." International Journal of Rotating Machinery 2020 (February 11, 2020): 1–9. http://dx.doi.org/10.1155/2020/8626457.

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This paper describes the method of preparing strong hydrophobic polypyrrole (PPy) on wind turbine blades. The water contact angle of strong hydrophobic PPy coatings was 127.2°. The strong hydrophobic PPy coatings exhibited excellent anti-icing properties. The maximum icing weight of strong hydrophobic PPy coating blade was almost 0.10 g while the maximum icing weight of no coating blade was found to be 26.13 g. The maximum icing thickness of a strong hydrophobic PPy coating blade was only 1.08 mm. The current research will provide a better technique to create anti-icing coatings on wind turbine blades and other outdoor equipment.
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Tabakoff, W., and M. Metwally. "Coating Effect on Particle Trajectories and Turbine Blade Erosion." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 250–57. http://dx.doi.org/10.1115/1.2906580.

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Gas turbine engines operating in dusty environments are exposed to erosion and performance deterioration. In order to improve the erosion resistance, nickel and cobalt superalloy blades and vanes are widely used in the hot section of gas turbines. Protective coatings have been used to enhance superalloy resistance to hot erosion. An investigation has been conducted to study coal ash particle dynamics and resulting blade erosion for both uncoated and coated blades of a two-stage axial flow gas turbine. A quasi-three-dimensional flow solution is obtained for each blade row for accurate computation of particle trajectories. The change in particle momentum due to collision with the turbine blades and casings is modeled using restitution parameters derived from three-component laser-Doppler velocimeter measurements. The erosion models for both blade superalloy and coatings are derived based on the erosion data obtained by testing the blade superalloy and coatings in a high-temperature erosion wind tunnel. The results show both the three-dimensional particle trajectories and the resulting blade impact locations for both uncoated and coated blade surfaces. In addition are shown the distribution of the erosion rate, impact frequency, impact velocity, and impact angle for the superalloy and the coating. The results indicate significant effects of the coating, especially on blade erosion and material deterioration.
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Jia, Yu Liang, Yun Song Zhao, Yu Shi Luo, Shuai Yang, Jian Wei Xu, and Ding Zhong Tang. "Effects of Coating on Surface Recrystallization of DD6 Single Crystal Blades." Materials Science Forum 747-748 (February 2013): 483–88. http://dx.doi.org/10.4028/www.scientific.net/msf.747-748.483.

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The fully heat-treated DD6 single crystal turbine blades were treated in three ways: (1) surface grinding, without coating; (2) firstly surface grinding, then surface coated with HY3(NiCrAlY) anti-oxidation coating; (3) after surface grinding, coated surface with the bond layer of NiCrAlY and top layer of YSZ(Y2O3stabilize ZrO2) for the double-layer thermal barrier coatings. All these three experimental blades were treated with vacuum heat-treatment at 1120°C for 4h. The effects of coating on surface recrystallization of single-crystal blades have been investigated. The results indicate that: just with surface polishing blade generated a 6~9μm thick cellular recrystallization zone on the surface. The γ' presented coarse morphology and distributed discretely within cellular, and the γ' growth direction was perpendicular to the cellular interface; blade surface coated with anti-oxidation coating after polishing formed a 3~6μm thick cellular recrystallization zone in the matrix interface. But the grain boundary was fuzzy and recrystallization morphology was incomplete; the matrix interface morphology of blade coated with thermal barrier coatings after polishing changed insignificantly, but some local cellular recrystallization was found. The results indicate that the coating changes the cellular recrystallization morphology of the original matrix of the blade, which can effectively reduce the occurrence degree of recrystallization.
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Khuengpukheiw, Ronnarit, Charnnarong Saikaew, and Anurat Wisitsoraat. "Wear resistance of HVOF sprayed NiSiCrFeB, WC-Co/NiSiCrFeB, WC-Co, and WC-Cr3C2-Ni rice harvesting blades." Materials Testing 63, no. 1 (January 1, 2021): 62–72. http://dx.doi.org/10.1515/mt-2020-0009.

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Abstract In this work, NiSiCrFeB, WC-Co/NiSiCrFeB, WC-Co, and WC-Cr3C2-Ni coatings were sprayed on rice harvesting blade surfaces using a high velocity oxygen fuel (HVOF) process. Each of the rice harvesting blades was sprayed with one of four coating materials using different spraying durations. The effects of coating materials and spraying durations on the average values of coated blade volume loss, hardness and surface roughness (Ra) were studied through real rice-harvesting field tests. Analysis of variance (ANOVA) and a multiple comparison approach with Tukey’s test were used in order to conduct a comparative performance analysis of the coating materials of rice harvesting blades. The experimental results indicated that the NiSiCrFeB coating exhibited the highest volume loss compared with all others. In addition, the WC-Co-coated blade had significantly greater hardness than those coated with NiSiCrFeB, WC-Co/NiSiCrFeB, or WC-Cr3C2-Ni. The rice harvesting blade coated with either WC-Co/NiSiCrFeB, WC-Co, or WC-Cr3C2-Ni using the shortest spraying duration was recommended for installation in rice harvesting machines.
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Góral, Marek, Maciej Pytel, Ryszard Filip, and Jan Sieniawski. "The Influence of Turbine Blade Geometry and Process Parameters on the Structure of Zr Modified Aluminide Coatings Deposited by CVD Method on the ZS6K Nickel Superalloy." Solid State Phenomena 197 (February 2013): 58–63. http://dx.doi.org/10.4028/www.scientific.net/ssp.197.58.

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The Zr modified aluminide coatings is an alternative concept for replacing Pt-modified aluminide bondcoat for thermal barrier coatings. In the paper the influence of process parameters on the chemical composition and the thickness of aluminide coatings will be presented. The zirconia-doped aluminide coating was deposited on turbine blades made from ZS6K nickel superalloy during the low-activity CVD process. In recent work the influence of turbine blade geometry on thickness of coating was observed. The thickest coating was observed on the trailing and leading edge on the blade cross-section. In the conducted research, the light and scanning electron microscopy were used as well as the EDS chemical composition microanalysis.
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Suder, K. L., R. V. Chima, A. J. Strazisar, and W. B. Roberts. "The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor." Journal of Turbomachinery 117, no. 4 (October 1, 1995): 491–505. http://dx.doi.org/10.1115/1.2836561.

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The performance deterioration of a high-speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported. A 0.025 mm (0.001 in.) thick rough coating with a surface finish of 2.54–3.18 rms μm (100–125 rms μin.) is applied to the pressure and suction surface of the rotor blades. Coating both surfaces increases the leading edge thickness by 10 percent at the hub and 20 percent at the tip. Application of this coating results in a loss in efficiency of 6 points and a 9 percent reduction in the pressure ratio across the rotor at an operating condition near the design point. To separate the effects of thickness and roughness, a smooth coating of equal thickness is also applied to the blade. The smooth coating surface finish is 0.254–0.508 rms μm (10–20 rms μin.), compared to the bare metal blade surface finish of 0.508 rms pm (20 rms μin.). The smooth coating results in approximately half of the performance deterioration found from the rough coating. Both coatings are then applied to different portions of the blade surface to determine which portions of the airfoil are most sensitive to thickness/roughness variations. Aerodynamic performance measurements are presented for a number of coating configurations at 60, 80, and 100 percent of design speed. The results indicate that thickness/roughness over the first 2 percent of blade chord accounts for virtually all of the observed performance degradation for the smooth coating, compared to about 70 percent of the observed performance degradation for the rough coating. The performance deterioration is investigated in more detail at design speed using laser anemometer measurements as well as predictions generated by a quasi-three-dimensional Navier–Stokes flow solver, which includes a surface roughness model. Measurements and analysis are performed on the baseline blade and the full-coverage smooth and rough coatings. The results indicate that adding roughness at the blade leading edge causes a thickening of the blade boundary layers. The interaction between the rotor passage shock and the thickened suction surface boundary layer then results in an increase in blockage, which reduces the diffusion level in the rear half of the blade passage, thus reducing the aerodynamic performance of the rotor.
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Anzai, Seiichi. "Blade Coating Technology." JAPAN TAPPI JOURNAL 66, no. 9 (2012): 954–58. http://dx.doi.org/10.2524/jtappij.66.954.

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Giacomin, A. J., J. D. Cook, L. M. Johnson, and A. W. Mix. "Flexible blade coating." Journal of Coatings Technology and Research 9, no. 3 (November 1, 2011): 269–77. http://dx.doi.org/10.1007/s11998-011-9366-6.

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Fois, N., M. Watson, and MB Marshall. "The influence of material properties on the wear of abradable materials." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 231, no. 2 (August 5, 2016): 240–53. http://dx.doi.org/10.1177/1350650116649528.

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In aero-engines it is possible for the blades of the compressor, turbine or fan to incur into their casings. At these interfaces a lining of composite abradable material is used to limit damage to components and thereby sustain the efficiency and longevity of the engine as a whole. These composite materials must have good abradability and erosion resistance. Previously, the wear mechanisms at the contact between the blade and the coating have been characterised using stroboscopic imaging and force measurement on a scaled test-rig platform. This work is focused on the characterisation of the wear mechanism for two different hardnesses of abradable lining. The established stroboscopic imaging technique and contact force measurements are combined with sectioning of the abradable material in order to analyse the material’s response during the tests. A measure of the thermal properties and the resulting temperature of the linings during the test have also been made to further understand the effect of coating hardness. The wear mechanism, material response, contact force and thermal properties of the coating have been used to characterise the different material behaviour with different hardness. At low incursion rates, with a soft coating, the blade tip becomes worn after an initial adhesive transfer from the coating. Post-test sectioning showed blade material and significant compaction present in the coating. The harder coating produced adhesion on the blade tip with solidification observed in the coating. Thermal diffusivity measurements and modelling indicated that thermally driven wear observed was as a consequence of the increased number of boundaries between the metal and hBN phases present interrupting heat flow, leading to a concentration of surface heat. At higher incursion rates, the wear mechanism is more similar between the coatings and a cutting mechanism dominates producing negligible adhesion and blade wear.
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Ngoret, Joshua K., and Venkata P. Kommula. "Role of Aluminide coating degradation on Inconel 713 LC used for Compressor Turbines (CT) of Short-haul Aircrafts." MRS Advances 3, no. 38 (2018): 2281–96. http://dx.doi.org/10.1557/adv.2018.207.

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ABSTRACTThis paper investigates the role degradation of protective diffusion aluminide coating on Inconel 713LC used for CT blades of short-haul aircraft fleet played in having the blades prematurely retired from service at 6378 hours, as opposed to their pre-set service time of 10000 hours. The blade samples were subjected to various examinations; X-ray diffraction (XRD), X-ray fluorescence (XRF), scanning electron microscopy (SEM) and energy dispersive spectroscopy (EDS) analyse at the; tips, airfoil, as well as the base, transverse and longitudinal, sectioned and unsectioned. As affirmed by both the transverse and longitudinal sections examinations, it was established that thermal attack leading to deterioration of the coating was greater at the tip and airfoils of the blades (the hotter zones) and lesser towards the bases (colder zones). As a result, severe degradation of the core material at the tips and airfoils compared to the bases and more prevalent at the leading edges than trailing edges at the tips. The results further suggest that both active outward Ni diffusion and inward Al diffusion can coexist during exploitation of the blades in service. The study illustrates the role played by the aluminide coating in early failure of CT blades with the aim of bettering the surface coatings and enhancing coating technologies, managing CT blade material monitoring as well as to give insights on advancing CT blades maintenance practices.
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Dissertations / Theses on the topic "Blade coating"

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Chen, Qingyuan. "An experimental study of air entrainment in a blade coating system with a pressurised pond applicator." Diss., Georgia Institute of Technology, 1998. http://hdl.handle.net/1853/5807.

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Deblais, Antoine. "Etalement de fluides complexes." Thesis, Bordeaux, 2016. http://www.theses.fr/2016BORD0303/document.

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Ce travail de thèse porte sur l'étalement de fluides complexes. Il met en évidence la riche phénoménologie d'un acte simple : celui d'étaler avec un racloir (rigide ou souple) une émulsion ou une solution de polymères sur un substrat. Pour chacun des fluides modèles étudiés, nous nous sommes focalisés expérimentalement sur l'observation de l'écoulement au cours de l'entraînement de la solution. Dans des conditions données d'étalement, il apparaît qu'une émulsion o/w peut s'inverser via plusieurs mécanismes de déstabilisation, ou encore, dans le cas d'une solution de polymères, exhiber une instabilité de sa ligne de contact, donnant naissance à des filaments de tailles et de longueurs d'ondes spécifiques. Nous montrons que les différents paramètres d'étalement, comme par exemple la hauteur du racloir, la vitesse d'étalement, les propriétés du substrat ou encore la rhéologie des solutions, doivent être pris en compte pour construire des diagrammes de phase d'étalement séparant les domaines d'existence des instabilités observées (régime de recouvrement partiel), des domaines où la solution transite vers le recouvrement total du substrat. D'autre part, nous tirons l'avantage de ces instabilités pour nous permettre de déposer de façon contrôlée des structures variées, offrant d'intéressantes perspectives en termes d'applications
This study shows the rich phenomenology of a simple act : spreading complex solutions such as emulsion and polymer solution on a plate, by using a rigid and flexible blade respectively. Here, we experimentally study the flow of the solution over the course of its spreading. During the spreading and in certain conditions, different phenomena occur, namely, emulsion inversion in the case of o/w emulsion or a contact line instability in the case of the polymer solution, which gives rise to the formation of polymer filaments with a well-defined wavelength and characteristic sizes. We showed, thanks to spreading phase diagrams, that the the existence of the instability (partial wetting regime) is separated to a domain where the solution cover the substrate. Spreading parameters such as the height of the scraper, spreading velocity or properties of the fluids turns out to be crucial. Finally, we take advantage of the instabilities to print a variety of interesting patterns for further applications
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Cardoso, Lilian Soares. "Aplicação de transistores orgânicos na fabricação de inversores lógicos digitais." Universidade de São Paulo, 2016. http://www.teses.usp.br/teses/disponiveis/18/18158/tde-21032017-153241/.

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Esta tese tem por objetivo o desenvolvimento de metodologias eficientes e de baixo custo para ajustar as propriedades elétricas de OFETs de canal p e de canal n, a fim de possibilitar a fabricação do circuito complementar orgânico, semelhante a uma estrutura CMOS. O desempenho do circuito complementar fabricado foi otimizado, e também foi confeccionado por impressão um OFETs de canal operando em baixas tensões. Para a fabricação do CMOS orgânico foi proposto um método baseado na seleção adequada do solvente da camada dielétrica para ajustar o desempenho elétrico dos OFETs de canal p e de canal n. Os solventes, MEK, nBA e DMSO foram selecionados para a dissolução do PMMA por apresentarem diferenças nos valores de momento de dipolo, de ponto de ebulição e de graus de ortogonalidade em relação as camadas semicondutoras de P3HT e de P(NDI2OD-T2) dos OFETs. A análise dos resultados dos OFETs de canal p e de canal n demonstrou que a metodologia proposta é adequada tanto para o ajuste das propriedades elétricas destes dispositivos quanto para a otimização do desempenho dos mesmos. Os melhores desempenhos elétricos para os OFETs de canal p e de canal n foram obtidos quando utilizados o DMSO e o MEK como solventes do PMMA, respectivamente, devido à perfeita ortogonalidade destes solventes em relação às camadas semicondutoras. Os OFETs de canal p que utilizaram o DMSO e os OFETs de canal n que utilizaram o nBA foram os que apresentaram desempenhos elétricos semelhantes, sendo portanto aplicados na fabricação do CMOS. Valores de ganho entre 6,8 e 7,8 e de margem de ruído entre 28,3 V e 34,5 V foram obtidos para inversores complementares fabricados nesta etapa do trabalho. OFETs de canal p utilizando uma blenda de PTAA: diF TES ADT como camada semicondutora, o PEDOT:PSS como eletrodos dreno/fonte e o P(VDF-TrFE-CFE) como camada dielétrica também foram fabricados neste trabalho. A técnica de blade-coating foi utilizada para a deposição dos eletrodos dreno/fonte e da camada semicondutora, ao passo que a técnica de spray-coating foi utilizada para a deposição da camada dielétrica. Da análise dos resultados foi possível inferir que a utilização de um dielétrico com elevada constante dielétrica (K), como o P(VDF-TrFE-CFE), possibilita o funcionamento dos transistores a baixas tensões (≤ 8 V), porém com valores de mobilidade reduzidos devido à elevada desordem dipolar na interface provocada por este dielétrico. Para minimizar esses efeitos, uma fina camada de um polímero fluorado foi depositada entre a camada semicondutora e a dielétrica pela técnica de blade-coating, constituindo assim uma bicamada dielétrica nos OFETs. Dos resultados das medidas elétricas dos OFETs constituídos pela bicamada dielétrica foi observada permanência do funcionamento destes dispositivos a tensões inferiores a 8 V com desempenho elétricos superiores a resultados já publicados na literatura. Por fim, inversores lógicos unipolares com transistores de carga foram fabricados com os OFETs que utilizaram a bicamada dielétrica, sendo obtidos valores de ganho entre 1,2 e 1,6 e de margem de ruído entre 56% e 68,5% de ½ VDD.
This thesis aimed to develop an efficient and low cost method to adjust the electrical properties of p- and n-channel OFETs to allow us to build an organic CMOS and the optimization of printed p-channel OFETs to work at low voltages. We proposed a method to fabricate the organic CMOS, based on the careful selection of dielectric solvent, which was adjusted to obtain the best performance of p- and n-channel OFETs. The dielectric solvents as MEK, nBA and DMSO were selected to dissolve the PMMA dielectric polymer due their different physical properties as dipole moment and boiling point and because they showed slightly different degrees of orthogonality to the P3HT and P(NDI2OD-T2) semiconductor layers of the OFETs. The results showed that the careful selection of the dielectric solvent not only allows to tune the electrical characteristics of the p- and n-channel OFETs, but also to improve the performance of these devices. The best performances were achieved when DMSO and MEK were used as dielectric solvents of the p and n-channel OFETs, respectively, as result of the perfectly orthogonality of these solvents to the semiconductor layers. P-channel OFETs using DMSO and n-channel OFETs using nBA showed similar electrical characteristics and thus, they were used to construct the organic CMOS. The organic complementary inverters showed high gain and noise margin values in the range of 6,8 to 7,8 and 28,3 V to 34,5 V, respectively. Printed p-channel OFETs were also fabricated, in which the blend PTAA:diF TES ADT was used as semiconductor channel, PEDOT:PSS as the drain/source electrodes and P(VDF-TrFE-CFE) as the dielectric layer. The blade-coating technique was used to deposit the source/drain electrodes and the semiconductor layer, while the spray-coating technique was used to deposit the dielectric layer. It was observed that using high-k dielectric as P(VDF-TrFE-CFE) enable to reduce the operating voltage of the OFETs (≤8 V), however, this high-k dielectric also reduced the field effect mobility due the dipolar disorder at the semiconductor/dielectric interface. To minimize the dipolar issue at the interface, we inserted a thin fluoropolymer dielectric layer by blade-coating between the semiconductor and the high-k dielectric layers, thus constituting a dielectric bilayer on the OFETs. From the electrical measurements of the OFETs with the dielectric bilayer, it was observed that the devices were still working at 8 V and they also showed better performance in comparison to results already published. Finally, organic unipolar inverters with load transistors were fabricated using the p-channel OFETs with the dielectric bilayer and they showed reasonable performance, with gain and noise margin in the range of 1,2 to 1,6 and 56% e 68,5% of ½ VDD, respectively.
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Maillard, Mathilde. "Étalements de fluides à seuil." Thesis, Paris Est, 2015. http://www.theses.fr/2015PESC1111/document.

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Les fluides à seuil sont des matériaux utilisés dans de nombreux procédés industriels au cours desquels ils sont mis en écoulement via leur interaction avec des outils solides. Afin de mieux comprendre comment ils s'étalent sur des surfaces, nous avons étudié d'une part leur enduction verticale sur une plaque mince et d'autre part leur étalement horizontal à l'aide d'une lame. Ces deux études se sont appuyées sur des mesures macroscopiques permettant de suivre la force appliquée à l'outil et des mesures microscopiques de PIV pour déterminer les champs de vitesse dans le matériau. Après confirmation de leur validité par comparaison avec nos résultats expérimentaux, des simulations numériques basées sur la programmation conique ont permis de préciser les écoulements en jeu. Pour l'enduction par trempage, nous observons que dans notre gamme d'étude, le dépôt de fluide à seuil sur la plaque est millimétrique et d'épaisseur constante, sauf aux extrémités. Selon le rapport des forces visqueuses et plastiques, l'enduction est régie par un équilibre "seuillo-gravitaire" ou "visco-gravitaire". Nous avons ensuite caractérisé l'écoulement généré dans le bain par le déplacement de la plaque afin d'expliciter l'origine du phénomène d'enduction. Les simulations numériques précisent la forme de cet écoulement. L'étalement horizontal dans un canal à l'aide d'une lame mince conduit au déplacement d'un amas de fluide faiblement cisaillé par rapport à une région de fluide au repos, par l'intermédiaire d'une couche cisaillée. Nous montrons qu'un modèle simple permet de prédire la dynamique de croissance de l'amas et la relie à la force normale à la lame
Yield stress fluids are used in various industrial processes in which solid tools make them flow. To have a better understanding on how they spread on surfaces, we first studied the vertical coating on a thin plate and then the horizontal blade-coating. Both studies are based on macroscopic measures recording the force applied on the plate and on the microscopic determination on the velocity fields in the fluid by PIV. Numerical simulations based on cone programming, which validity had been confirmed in comparison to our experimental results, specified the flows at stake. In dip-coating, we observed than within our framework, the yield stress fluid deposit on the plate is millimetric and of constant thickness, except on the tips. According to the value of the viscous over plastic forces ratio, the coating is led by a "yield-gravity" or a "visco-gravity" balance. Then, we characterized the flow generated in the bath by the plate displacement in order to clarify the origin of the coating phenomenon. The numerical simulations specified the flow characteristics. The horizontal blade-coating in a channel involves the displacement of a weakly sheared cluster of fluid in relation to a part of fluid at rest, through a sheared layer. We showed that the growing dynamic of the cluster is described with a simple model which links it to the normal force to the plate
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Van, Dyke Jason. "Modeling Behaviour of Damaged Turbine Blades for Engine Health Diagnostics and Prognostics." Thèse, Université d'Ottawa / University of Ottawa, 2011. http://hdl.handle.net/10393/20312.

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The reliability of modern gas turbine engines is largely due to careful damage tolerant design a method of structural design based on the assumption that flaws (cracks) exist in any structure and will continue to grow with usage. With proper monitoring, largely in the form of periodic inspections at conservative intervals reliability and safety is maintained. These methods while reliable can lead to the early retirement of some components and unforeseen failure if design assumptions fail to reflect reality. With improvements to sensor and computing technology there is a growing interest in a system that could continuously monitor the health of structural aircraft as well as forecast future damage accumulation in real-time. Through the use of two-dimensional and three-dimensional numerical modeling the initial goals and findings for this continued work include: (a) establishing measurable parameters directly linked to the health of the blade and (b) the feasibility of detecting accumulated damage to the structural material and thermal barrier coating as well as the onset of damage causing structural failure.
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Hey, Andrew Stuart. "Series interconnects and charge extraction interfaces for hybrid solar cells." Thesis, University of Oxford, 2013. http://ora.ox.ac.uk/objects/uuid:f19e44a8-e394-4859-9649-734116bc22b8.

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This thesis investigates novel hole extraction interfaces and series interconnects for applications in organic photovoltaics, specifically in single junction solid-state dye-sensitized solar cells (DSSCs) and tandem DSSC/polymer bulk heterojunction solar cells. Improvements in hole extraction and device performance by using materials compatible with scalable deposition methods are presented, including tungsten- and molybdenum-disulphide (WS2 and MoS2), and p-type doped spiro-OMeTAD (2,2',7,7'-tetrakis-(N,N-di-p-methoxyphenylamine)9,9'-spirobifluorene) nanoparticle dispersions. WS2 and MoS2 hole extraction layers increase averaged short circuit currents by 20% and 16% respectively, and power conversion efficiencies by 19% and 14% respectively when compared with control devices. Similarly, doped spiro-OMeTAD nano-particle layers improved short circuit current densities by 32% and efficiencies by 9%. Tandem device interconnects using these novel hole extraction formats have been fabricated, but although devices did exhibit rectification, overall performance was poor. Possible reasons for their limited success have been analysed. Dye-sensitized solar mini-modules are also reported. In order to assure the scalability of DSSC technology, these larger area devices were constructed using doctor blade coating to deposit the hole transporter material. As well as achieving a respectable maximum power conversion efficiency of 2.6%, it has also been shown that the extent to which hole transporter infiltrates the mesoporous photoanode of these devices may be tuned by altering substrate temperature during deposition. It was found that an optimal coating temperature of 70 degrees C produced the best efficiency, with a corresponding pore-filling fraction of 41%.
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Long, K. "Aluminide-based coatings for turbine blade internal cooling passages." Thesis, Cranfield University, 2004. http://dspace.lib.cranfield.ac.uk/handle/1826/11002.

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The development of aero-gas turbines is moving towards more efficient engines with higher pressure ratios and increased Turbine Entry Temperatures. This leads to increases in overall turbine blades temperatures which has resulted in the widescale development of turbine blades with film cooling and Thermal Barrier Coatings (TBCs) which reduce the metal temperature of the blade. The air used for film cooling is directed around the blade by internal passages within the blade, current engines are experiencing hot corrosion in areas of these internal passages, even with internal aluminide coatings. The trend for more efficient engines means that corrosion of the internal passages will become more common, coupled with the inability to inspect the internal passages of turbine blades in service, results in a requirement for an improved coating for the internal passages of turbine blades. The aim of this study was to develop a coating which provides improved corrosion and oxidation performance over a standard vapour aluminide on single crystal CMSX-4 turbine blades material. The coating needs to be compatible with the Rolls- Royce bond coat and the Rolls-Royce manufacturing strategy. The study investigated a number of additions which could be used to improve the performance of an aluminide coating. Silicon was selected as the optimum addition on the basis of performance and ease of deposition. The work then assessed the influence of various production parameters on the formation of a silicon-aluminide coating. It was possible to control the level of silicon deposited in the coating. Performance testing, using cyclic oxidation and salt recoat hot corrosion tests, of various silicon aluminides developed in this programme demonstrated at least a doubling in life compared with vapour aluminide coatings.
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Rakotomalala, Noémie. "Simulation numérique de l’écaillage des barrières thermiques avec couplage thermo-mécanique." Thesis, Paris, ENMP, 2014. http://www.theses.fr/2014ENMP0020/document.

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L'objectif de ce travail de thèse est de mettre en place une simulation thermo-mécanique couplée d'une aube revêtue permettant de modéliser l'écaillage de la barrière-thermique qui survient dans les conditions de service de l'aube. La barrière thermique est un revêtement isolant déposé à la surface du substrat monocristallin base Nickel AM1 constitutif de l'aube préalablement recouverte d'une sous-couche. Le mode de dégradation dominant dans ces systèmes est la création de fissures qui résultent de l'accroissement des ondulations hors-plan d'une couche intermédiaire d'oxyde formée en service entre la céramique et la sous-couche. En vue de modéliser ce phénomène d'écaillage, un ensemble d'outils numériques permettant de réaliser un calcul 3D par éléments finis thermo-mécanique couplé de l'aube revêtue est développé au sein du code de calcul par éléments finis Z-set. L'insertion d'éléments de zone cohésive mécanique et thermique au niveau de l'interface barrière-thermique/substrat permet de tenir compte simultanément des changements dans le processus de transert de charge et des variations du flux de chaleur causés par l'amorçage et la propagation d'une fissure interfaciale. L'élément fini d'interface mixte de Lorentz qui repose sur un Lagrangien augmenté, est mis en oeuvre. Afin de tenir compte des propriétés structurelles du revêtement, la modélisation de la barrière thermique est réalisée au moyen d'éléments de coque thermo-mécaniques reposant sur l'approche dite “Continuum Based”. Ces éléments sont développés puis validés dans le cadre de la thèse. La méthode utilisée pour réalier le couplage thermo-mécanique est l'algorithme partitioné CSS (Conventional Serial Staggered) sous-cyclé à pas de couplage fixe dont on montre les limitations dans le cas d'une simulation impliquant la propagation d'une fissure. L'introduction de pas de couplage adaptatifs contrôlés au moyen d'une variable interne du problème mécanique a permis de contourner ces limitations. L'ensemble des briques numériques est validé sur des cas tests de complexité croissante. Des cas d'applications effectués sur des géométries tubulaires à gradient thermique de paroi sont réalisés afin de tester le modèle couplé sur des structures et des chargements proches des conditions de service de l'aube. Enfin, des calculs thermo-mécaniques couplés sur aube revêtue sont présentés
The purpose of this thesis is to perform a coupled thermomechanical simulation of the failure of thermal barrier coatings for turbine blades under service conditions. The thermal barrier coating is an insulating component applied to the single crystal Nickel-based superalloy AM1 substrate which is covered with a bond coat beforehand. The main degradation mode of those systems is due to the initiation and propagation of cracks caused by the out-of-plane undulation growth of an oxide layer formed in service. A set of numerical tools is implemented into the Finite Element code Z-set in order to perform a 3D thermomechanically coupled simulation of the failure of thermal barrier coatings for turbine blades. Inserting thermomechanical cohesive zone elements at the interface between the coating and the substrate makes it possible to account for the changes in the load transfer and the variations in the heat flux as a consequence of interface degradations. The mixed finite interface element of Lorentz based on an Augmented Lagrangian is used. The thermal barrier coating is modelled by means of thermomechanical shell elements implemented using the Continuum-Based approach to take advantage of the structural properties of the coating layer. Moreover, the partitionned CSS (Conventional Serial Staggered) algorithm used to couple thermal and mechanical problems is assessed. The limitations of sub-cycling with constant coupling time-step are shown through a simulation with crack propagation. The introduction of adaptative time-stepping allows to circumvent that issue. The numerical tools are assessed on test cases with increasing complexity. Numerical simulations on cylindrical tube with a thermal through-thickness gradient are performed with realistic loading sequences. Finally, thermomechanical simulations on turbine blades covered with thermal barrier coating are shown
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Khan, Fahd. "Investigating into advanced coatings for bandsaw blades." Thesis, Northumbria University, 2011. http://nrl.northumbria.ac.uk/36301/.

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Bandsawing is an important metal cutting operation carried out in a variety of industries in order to remove raw material for secondary operations. Due to its continuous cutting action, bandsawing has over taken other cutting processes such as power hack sawing and circular sawing. Bandsawing operation offers numerous advantages such as high cutting rate, low kerf loss, longer tool life and high automation possibilities, due to its efficient and continuous cutting action. It is costly and time-consuming to test the wear of the full bandsaw products on a full-scale bandsaw machine. In order to overcome this, a single tooth test rig has been developed at Northumbria University, which utilizes a single bandsaw tooth instead of the complete bandsaw loop. Previous research has utilized this test rig for evaluating bi-metal saws while machining steels. Development of new, wear resistant and difficult-to-cut materials such as titanium alloys (e.g. Ti-17) imposes greater demands on bandsawing operations. Traditionally, high speed steels and cemented carbides have been employed to cut/machine these materials. The main disadvantage of high speed steel cutting tools is that it undergoes severe plastic deformation when cutting at temperatures above 600oC. Tungsten carbide cutting tools have proven their supremacy in almost all the machining processes and interrupted cutting of these difficult-to-cut titanium alloys. One of the challenges in design of cemented tungsten carbide tools is the optimization of toughness and wear resistance. This has led to the development of coated carbide tools, which accounts for the major portion of all commercial metal cutting inserts sold worldwide. This current research has furthered the use of single tooth test rig, by using un-coated and coated tungsten carbide tipped bandsaw blades while machining high performance titanium alloys (Ti-17). The purpose is to evaluate and assess the performance of un-coated and coated carbide bandsaw teeth and ascertain wear mechanisms and modes of single bandsaw tooth, in a way that is representative of full product testing. Two different coatings (AlTiN and TiAlSiN) were chosen to be deposited using arc evaporation PVD technique. These coatings were selected due to their properties in terms of wear resistance and structure: TiAlSiN is nano-structured, while AlTiN is conventional in terms of its grain size. These coatings were characterized using various techniques, such as electron microscopy and nano-indentation. Cutting tests were carried out using un-coated and coated carbide bandsaw teeth. Adhesive wear and diffusion wear were identified as the wear mechanisms, while flank wear and chipping were confirmed as the principal wear modes for the un-coated carbide bandsaw teeth. Cutting forces were found to be less while machining Ti-17 alloy using coated teeth as compared to the forces obtained while machining with un-coated teeth. Less material was found to be adhering to the coated teeth as compared to un-coated teeth. Finite element analyses (FEA) were carried out on interaction of the cutting tool and the workpiece to determine the stress concentration during the cutting process. It was found that the increase in the honing lengths on the carbide teeth reduced the stresses and moved the maximum stress from the edge of the rake face to the honed edge.
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Chien, H. H. "The mechanical properties of aluminide coatings." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.352970.

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Books on the topic "Blade coating"

1

Technical Association of the Pulp and Paper Industry. Coating Fundamentals Committee., ed. Paper coating viscoelasticity and its significance in blade coating. Atlanta, Ga: TAPPI Press, 1996.

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Blade Coating Seminar (1988 Portland, Me.). 1988 Blade Coating Seminar: Portland Marriott, Portland, ME, October 12-14. Atlanta, GA, USA (P.O. Box 105113, Atlanta 30348): TAPPI Press, 1988.

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MacQuarrie, John. Ultrasonic characterization of a platinum aluminide coating on a gas turbine blade. Ottawa: National Library of Canada = Bibliothèque nationale du Canada, 1992.

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Blade Coating Seminar (1990 Minneapolis, Minn.). 1990 Blade Coating Seminar: Hyatt Regency Minneapolis, Minneapolis, MN, November 4-7. Atlanta, GA, USA: TAPPI Press, 1990.

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Blade Coating Seminar (1986 Appleton, Wis.). 1986 Blade Coating Seminar: Paper Valley Hotel, Appleton, WI, September 28-October 1. Atlanta, GA, USA (P.O. Box 105113, Atlanta 30348): TAPPI Press, 1986.

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Sadowski, Tomasz, and Przemysław Golewski. Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8.

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Coatings for high-temperature structural materials: Trends and opportunities. Washington, D.C: National Academy Press, 1996.

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Abdul-Aziz, Ali. Design evaluation using finite element analysis of cooled silicon nitride plates for a turbine blade application. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Abdul-Aziz, Ali. Design evaluation using finite element analysis of cooled silicon nitride plates for a turbine blade application. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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1990 Blade Coating Seminar: Hyatt Regency Minneapolis, Minneapolis, MN, November 4-7 (TAPPI notes). Tappi Press, 1990.

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Book chapters on the topic "Blade coating"

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Aidun, Cyrus K., and Nick G. Triantafillopoulos. "High-Speed Blade Coating." In Liquid Film Coating, 637–72. Dordrecht: Springer Netherlands, 1997. http://dx.doi.org/10.1007/978-94-011-5342-3_18.

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Wang, Can Ming, Hong Fei Sun, Qiang Song, and Qiong Qiong Yan. "Application of Wear Resistant Coating Technology on Coating Blade." In Key Engineering Materials, 1761–64. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-456-1.1761.

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Sinclair, Anthony, Michael O’Brien, and Victor DaSilva. "Nondestructive Depth Profiling of the Protective Coating on a Turbine Blade." In Review of Progress in Quantitative Nondestructive Evaluation, 1637–43. Boston, MA: Springer US, 1990. http://dx.doi.org/10.1007/978-1-4684-5772-8_211.

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Kleimenov, P., L. Lesnevskiy, M. Lyakhovetskiy, A. Ionov, and E. Marchukov. "Investigation into the Wear Process of Laser Cladding from TiC Multilayer Coating for GTE Shrouded Blade Platforms." In Lecture Notes in Electrical Engineering, 67–80. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1773-0_6.

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Che, Zhigang, Shui-li Gong, Shikun Zou, Ziwen Cao, and Qunxing Fei. "Investigation on the Key Techniques of Confined Medium and Coating Layer for Laser Shock Processing on Aeroengine Blade." In Proceedings of the 36th International MATADOR Conference, 527–30. London: Springer London, 2010. http://dx.doi.org/10.1007/978-1-84996-432-6_116.

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Sadowski, Tomasz, and Przemysław Golewski. "Protective Thermal Barrier Coatings." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 5–11. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_2.

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Srinivasan, Dheepa, N. Dayananda, Neha Kondekar, Mounika Gandi, and Hariharan Sundaram. "Oxidation Coating Life Extension in Gas Turbine Blades During Repair." In Superalloys 2016, 735–43. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2016. http://dx.doi.org/10.1002/9781119075646.ch79.

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Liang, Fei, Yong Tang, Jihua Gou, and Jay Kapat. "Development of Multifunctional Nanocomposite Coatings for Wind Turbine Blades." In Ceramic Transactions Series, 325–36. Hoboken, NJ, USA: John Wiley & Sons, Inc., 2011. http://dx.doi.org/10.1002/9781118019467.ch32.

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Urbahs, A., K. Savkovs, M. Urbaha, and I. Kurjanovičs. "Nanostructured Intermetal-Ceramic Coatings for Blades of Gas Turbine Engines." In NATO Science for Peace and Security Series B: Physics and Biophysics, 307–14. Dordrecht: Springer Netherlands, 2012. http://dx.doi.org/10.1007/978-94-007-4119-5_28.

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Sturlese, S., and L. Bertamini. "Segmented Thermal Barrier Coatings on Turbine Blades and Diesel Engine Components." In Materials for Advanced Power Engineering 1994, 705–16. Dordrecht: Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1048-8_58.

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Conference papers on the topic "Blade coating"

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Gebhard, Susanne, Tanja Wobst, Dan Roth-Fagaraseanu, and Matthew Hancock. "Advanced Coating Systems for Future Shroudless Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2017.

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Shroudless turbine designs offer the advantages of weight reduction and lower mechanical loads on the one hand but bear challenges as high gap sensitivity and high temperatures of the static parts on the other hand. In the last years, a lot of work was carried out in order to develop a sealing system for a shroudless design consisting of an abrasive blade tip coating and an abradable segment coating addressing all the requirements defined. Aside from being abradable, the segment coatings have to be mechanically stable, withstand high thermo-mechanical loadings and have to work for thicknesses larger than 1 mm. Due to the limited temperature capability of the currently used segment coating material yttria-stabilised zirconia, which combines advantageously a suitable thermal conductivity with a high thermal expansion coefficient, new ceramic materials for the segment coating had to be developed. A very promising sealing system combines an abrasive blade tip coating with an yttria-stabilised zirconia / magnesia alumina spinel double-layer abradable coating system with a 3D interface structure between the bond coat and the ceramic coatings. The present work gives an overview of the development and the performance of this sealing system.
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Scrinzi, Erica, Iacopo Giovannetti, Nuo Sheng, and Luc Leblanc. "Development of New Abradable/Abrasive Sealing Systems for Clearance Control in Gas Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2065.

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Abradable/abrasive sealing systems are currently used in gas turbines to reduce the blade tip gas leakage and consequently improve the turbine efficiency. The coatings selection is directly related to the section in which they are used. Seal systems for hot gas paths are primarily required to withstand high temperature. The abradable coating should be easily removed by the tip blade without causing significant blade wear, whereas the blades should have sufficient cutting capabilities. Durability properties, such as erosion resistance, are also required. Owing to their temperature capabilities, porous ceramic coatings are successfully used as abradable coatings. Although they are characterized by good abradability properties, their resistance to environmental attacks, such as solid particle erosion, is limited by the porous microstructure which negatively affects their service life. It is apparent that durability and abradability are the main targets to be simultaneously achieved for ensuring longer service life and improved efficiency. The present work is aimed at developing new abradable/abrasive coatings pairs able to ensure both the durability performances of the coatings and good abradability properties. Three ceramic abradable coatings with DVC and porous microstructure have been studied. The down-selection process has been carried out by considering the microstructure, the hardness, the tensile adhesion strength, the erosion resistance, and the furnace cycle test resistance. A composite coating made by NiCoCrAlY matrix containing abrasive grits applied by electrolytic process was selected as abrasive material system. The abrasive grits (patent application in process by GE Oil&Gas) consists of a mixture of ceramic particles. These grits ensure both short-term cutting capability and thermal stability, assuring the clearance maintenance over time. The abradability of the seal system was assessed by a properly designed test, namely Rub Rig test, which simulates the blade incursion in the abradable coating. Surface patterns on abradable coating were also considered to further enhance the abradability. Engine tests are foreseen for assessing the service behavior of this seal system.
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Hamanaka, Viviane N., Remco J. van Dasselaar, Marcos H. M. O. Hamanaka, Natanael L. Dias, Vinicius L. Pimentel, Maria Cecilia Q. Bazetto, Hany Aziz, and Fernando J. Fonseca. "Blade Coating System for Organic Electronics." In 2019 34th Symposium on Microelectronics Technology and Devices (SBMicro). IEEE, 2019. http://dx.doi.org/10.1109/sbmicro.2019.8919343.

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Pejryd, Lars, and Jan Wigren. "Engine Test Experience With HVOF WC-Co Coated Fan Blade Dampers." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-435.

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Tungsten carbide thermal spray coatings are important to the aerospace industry for reducing wear on jet engine components, fanblade mid-span dampers being one example. However, the fatigue life of a component is often reduced when a coating is applied and for some cases the coating can fail due to spallation and cracking. Coating failures can result in decreased engine performance and costly maintenance. To provide insight and possible explanations for the reduced service life of coated mid-span dampers, identify the best coating and application processes for future use, and to develop methods for improving coating performance, a comprehensive experimental research program was conducted. The program involved coating performance in jet engine tests, coating crack resistance in bending, low cycle fatigue properties of the coating and substrate, and microstructures for a wide range of coating compositions and application processes. Eleven coatings were ranked according to their performance relative to the other coatings in each evaluation category. Five of the coatings were selected for engine test runs. Results from the engine test runs for more than 800h (AMT-cycle) were compared to bend and low cycle fatigue evaluations and to meassured residual stresses. Strong correlation between engine performance and the residual stresses in the coating-substrate system was found. Results from the program were used for selecting a suitable coating system for final in-service use.
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Conner, Jeffrey A., and Michael J. Weimer. "Coating Rejuvenation: New Repair Technology for High Pressure Turbine Blades." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0641.

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With the evolution of advanced directionally solidified and single crystal nickel base superalloy turbine blades, managing life cycle costs of high pressure turbine (HPT) blades has become increasingly more difficult. Today’s advanced high pressure turbine blades in aero and aero-derivative turbines feature thin walls (<.030 inches), complex internal geometries, three dimensional (3D) aerodynamic shapes, multiple protective coatings and complex film cooling schemes. A major contributor to blade life cycle cost is the ability to perform multiple repairs without compromising the integrity of these complex components. Repair of HPT blades has traditionally fallen into two categories: mini or partial repairs where blade tips are restored and coated, and full repairs where flowpath coatings are removed, blade tips restored and new coating(s) applied to flowpath surfaces. Historically, the number of full repairs allowed ranges from zero to two based on numerous design considerations, one of which is maintaining a minimum wall thickness. Removal of protective coatings during full repair reduces wall thickness which limits the number of times a full repair can be performed. Furthermore, blades that have sufficient design allowance to permit two full repairs typically have very low yields at the second full repair due to thinning of airfoil walls below minimum thickness limits. The life of a given HPT blade is therefore controlled to a large degree by at what shop visit a full repair is performed. GE Engine Services has developed a new blade repair approach — Coating Rejuvenation — which significantly extends blade life by restoring protective coatings and maintaining wall thickness. Included in the Coating Rejuvenation repair are technologies that allow: removal of physical vapor deposited (PVD) thermal barrier coatings from external surfaces and cooling holes without impacting the bond coat; removal of oxidation and corrosion products from engine exposed coatings without impacting adjacent intact coating; restoration of coating composition to optimize environmental resistance; and upgrade of existing aluminide coatings to platinum aluminide coatings without removal of the existing coating. Combined together, these technologies can be used to support a comprehensive blade repair workscope plan that dramatically increases the life of HPT blades and decreases the life cycle cost for these components. Overviews of these technologies are presented in this paper along with information on how the technology was matured. Due to pending patent applications with the US Patent & Trademark Office as well as pending patent applications in other countries, significant technical detail cannot be presented at this time.
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Van Roode, Mark, and Jose Aurrecoechea. "Rainbow Field Test of Coatings for Hot Corrosion Protection of Gas Turbine Blades and Vanes: I — Blade Coatings." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-242.

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A rainbow field test sponsored by the Electric Power Research Institute (EPRI) under contract RP2465-1 was performed to evaluate the comparative hot corrosion resistance of commercially available coatings for gas turbine blades and vanes. The 10,307-hr field test was carried out on a Solar Turbines Incorporated Centaur T-4000 gas turbine operating on a lower grade liquid fuel at the Favianca site of the Owens-Illinois, Inc. glass manufacturing facility in Valera, Venezuela. This paper reviews the results of an evaluation of the performance of three modified aluminides, three MCrAlY overlays, and one duplex NiCoCrAlY/ZrO2-2OY2O3 overlay applied as coatings to the first-stage MAR-M421 and IN-738LC rotor blades, Visual and metallographic examination and remnant coating thickness measurements established that the MCrAlY overlay coatings were generally more effective than a Cr-aluminide and two Pt-aluminides protecting the first-stage blades. Individual differences between the various coatings were established. A remnant coating thickness index (RCTI) was defined to express coating survival and protectiveness quantitatively. The results of blade airfoil temperature estimates were correlated with the hot corrosion morphology.
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Sugita, Y., M. Ito, N. Isobe, S. Sakurai, C. R. Gold, T. E. Bloomer, and J. Kameda. "High Temperature Degradation of Coating and Substrate in Gas Turbine Blade." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-358.

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This paper studied high temperature degradation behavior of gas turbine blades consisting of CoNiCrAlY coatings and Rene 80 substrates using a small punch (SP) testing technique at 295–1223 K and scanning Auger microprobe (SAM). In SP tests, coating cracks continuously propagated along the radial direction at 295 K and many cracks discretely were formed along more random directions at higher temperatures. The ductility of the coating at 295 K was reduced and the ductile-brittle transition temperature was increased during long time exposure of gas turbine blades to high temperature oxidation environments. SAM analyses on cross sections and fracture surfaces of the coatings indicated that oxidation and S segregation near the coating surface are profoundly induced in-service. The relationship between the mechanical properties and microstructural/chemical evolution near the coating surface is presented which serves as a data base for determining the remaining life of gas turbine blades.
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Driscoll, Matthew, Eric McFetridge, and William Arseneau. "Evaluation of At Sea Tested LM2500 Rainbow Rotor Blade Coatings." In ASME Turbo Expo 2002: Power for Land, Sea, and Air. ASMEDC, 2002. http://dx.doi.org/10.1115/gt2002-30263.

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This paper discusses the performance of various high pressure turbine (HPT) blade coatings applied to refurbished LM2500 components that were operated in a frigate class marine application. In the early 1990s, an LM2500 propulsion gas turbine engine was removed from the Australian Navy ship HMAS DARWIN for overhaul. In an effort to reduce the cost of overhaul, it was proposed to refurbish the HPT blades instead of the standard practice of replacing the blades with new parts. Included in the proposal to replace the blades with refurbished parts, various coatings were applied in order to evaluate the cost effectiveness of refurbishing blades during overhaul vice replacing with new components. The HPT “Rainbow” Rotor is a paired blade configuration and was built up in 1991 using refurbished blades coated with the standard BC 21 (overlay CoCrAlY) and an industrial standard platinum aluminide (diffusion) coating. In addition, BC 23 coating was applied to several new production blades and installed in the Rainbow Rotor as a control to evaluate the refurbished parts performance. In May 2000, the Rainbow Rotor set of LM2500 blades was removed from service after having accumulated in excess of 11,500 operating hours. This paper details the coating compositions tested and the resultant metallurgical analysis of these blades/coatings.
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Chan, Kwai S., N. Sastry Cheruvu, and Gerald R. Leverant. "Coating Life Prediction for Combustion Turbine Blades." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-478.

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A life prediction method for combustion turbine blade coatings has been developed by modeling coating degradation mechanisms including oxidation, spallation, and aluminum loss due to inward diffusion. Using this model, the influence of cycle time on coating life is predicted for GTD-111 coated with an MCrAlY, PtAl, or aluminide coating. The results are used to construct a coating life diagram that depicts failure and safe regions for the coating in a log-log plot of number of startup cycles versus cycle time. The regime where failure by oxidation, spallation, and inward diffusion dominates is identified and delineated from that dominated by oxidation and inward diffusion only. A procedure for predicting the remaining life of a coating is developed. The utility of the coating life diagram for predicting the failure and useful life of MCrAlY, aluminide, or PtAl coatings on the GTD-111 substrate is illustrated and compared against experimental data.
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Hu, Weifei, Weiyi Chen, Xiaobo Wang, Zhenyu Liu, Jianrong Tan, and Yeqing Wang. "Wind Turbine Blade Coating Fatigue Induced by Raindrop Impact." In ASME 2020 Power Conference collocated with the 2020 International Conference on Nuclear Engineering. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/power2020-16510.

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Abstract With the increase of wind energy production demand, the need to manufacture larger wind turbine blades is on the rise. Because of the high tip speed of the large blade, the blade could be impacted by high-speed objects such as raindrops. This research focuses on developing a computational model for analyzing wind turbine blade coating fatigue induced by raindrop impact. A stochastic rain texture model is used to simulate a realistic rain event determined by a rain intensity and a rain duration. A smoothed particle hydrodynamic approach is implemented to calculate the impact stress considering a single raindrop. A stress interpolation method is proposed to accurately and efficiently estimate the impact of stress under a random rain event. Besides, a crack growth law is used to explain the process of coating shedding. Through a method for calculating crack growth length based on stress, this paper analyzes crack growth life as a function of the rain intensity and the rain duration. This function, together with the statistics of rainfall history, provides a new approach for estimating the expected fatigue life of the blade coating.
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Reports on the topic "Blade coating"

1

Youchison, Dennis L., and Michail A. Gallis. High efficiency turbine blade coatings. Office of Scientific and Technical Information (OSTI), June 2014. http://dx.doi.org/10.2172/1177057.

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Stick, Daniel, and Adrian Casias. Recipe for coating ceramic blades for ion trapping. Office of Scientific and Technical Information (OSTI), September 2020. http://dx.doi.org/10.2172/1660784.

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Amarendra K. Rai. DEVELOPMENT OF PROTECTIVE COATINGS FOR SINGLE CRYSTAL TURBINE BLADES. Office of Scientific and Technical Information (OSTI), December 2006. http://dx.doi.org/10.2172/895828.

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Kameda, J., T. E. Bloomer, Y. Sugita, A. Ito, and S. Sakurai. Mechanical properties of aluminized CoCrAlY coatings in advanced gas turbine blades. Office of Scientific and Technical Information (OSTI), July 1997. http://dx.doi.org/10.2172/505288.

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Sugita, Y., M. Ito, S. Sakurai, T. E. Bloomer, and J. Kameda. Characterization of mechanical properties of aluminized coatings in advanced gas turbine blades using a small punch method. Office of Scientific and Technical Information (OSTI), April 1997. http://dx.doi.org/10.2172/459436.

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