Journal articles: 'Blade coating'

1

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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7

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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10

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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11

Weeks, Lisa, Pat Gane, Tony Lyons, and Douglas Bousfield. "Operational limits of blade coating associated with high aspect ratio pigments: Part I—bench top blade coater." February 2019 18, no. 2 (2019): 123–30. http://dx.doi.org/10.32964/tj18.2.123.

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Operational issues, such as stalagmite formations, scratches, or spits, develop during blade coating of high solids coatings at high web speeds. Coatings that contain high aspect ratio pigments exhibit these difficulties at lower solids concentrations and slower machine speeds than coatings comprised of more spherical shaped pigments. There are a number of potential reasons behind this phenomenon, but a clear mechanism is not well established. Using a bench top blade coater without a base sheet, the goal of this study is to understand the operational limits that occur due to the coating suspension interacting with the blade. Pigment suspensions are applied in excess in front of the blade. A camera mounted near the blade exit is used to detect defects and buildup on the backside of the blade. The machine speed at which deposits on the blade first appear was determined for three pigments having different shape factors and at varying weight fractions. A Newtonian fluid was also used in the coating device. A runnability window based on shape factor and solids content was developed. Small changes in the solids concentration displayed changes in the speed at which blade deposits begin to appear. No operational issues could be produced using the Newtonian fluid. Presence of the particles at solids concentration nearing their immobilization solids mustbe contributing to the development of runnability issues.

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12

Pranckh, F. R., and L. E. Scriven. "Elastohydrodynamics of blade coating." AIChE Journal 36, no. 4 (April 1990): 587–97. http://dx.doi.org/10.1002/aic.690360410.

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13

Wang, Can Ming, Hong Fei Sun, Qiang Song, and Qiong Qiong Yan. "Application of Wear Resistant Coating Technology on Coating Blade." Key Engineering Materials 353-358 (September 2007): 1761–64. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.1761.

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Coating blade wears seriously in paper coating process. Wear mechanism was analyzed in this article. A new technology of surface coating process was introduced to increase the hardness of the edge of coating blade and thus to prolong its service life. Surface coating preparing process on blade was studied and metal-ceramic compound coating prepared successfully on the edge of coating blade with AT13 (Al2O3+13%TiO2) wear resistant material by plasma spraying process. NiCrAl alloy powder was used as under coat material. Microstructure of the coating is dense. The coating bonds well with the matrix and have high hardness. Results of grain-abrasion testing show that wear-resisting property of the metal/ceramic compound coating is about 7-8 times as that of steel blade.

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14

Kováč, Ján, Pavol Harvánek, Jozef Krilek, Tomáš Kuvik, and Ján Melicherčík. "Analysis of cutting conditions in the process of cross-cutting wood by circular saws." BioResources 16, no. 1 (December 16, 2020): 1029–41. http://dx.doi.org/10.15376/biores.16.1.1029-1041.

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An analysis was conducted of the effects of cutting conditions in the cross-cutting of wood using circular saws. Gradual wear of the saw blade cutting wedges impacted the entire cutting process. Two different types of circular saw blades were used. One blade type featured sintered carbide tips and 54 saw blade teeth, whereas the other had high-speed steel with 56 teeth; both saw-blades were 600 mm in diameter with a rake angle of 20°. The two wood species were spruce (Picea abies) and beech (Fagus sylvatica). During sawing, the timber was fed at a velocity of vf = 6 and 12 m·min-1. The cutting speed (vc) was set at 60 m·s-1, 70 m·s-1 and 80 m·s-1. The saw blades were coated with three types of PVD coatings. The least energy intensive saw blade was a sintered carbide-free saw blade with a coating (AlTiN) at a displacement speed of 12 m·min-1 and cutting speed of 60 m·s-1 with a power of 1310,63 W. Any change of a saw blade considerably affected torque for all the wood species, so a particular type of saw blade will always have an impact on torque. Other parameters distinctively and individually influenced the process of wood sawing.

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15

Wang, Zhi De, Jing Li, Zhen Wei Guan, Yu Zhong Zhang, Yan Wang, and Zhi Yong Wang. "Fabrication and Evaluation of an Amino Modified Epoxy Coating for Anti-Scouring and Anti-Corrosion Application." Materials Science Forum 815 (March 2015): 684–89. http://dx.doi.org/10.4028/www.scientific.net/msf.815.684.

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Excellent performance is necessary for compressor blade when aircraft engine serves in harsh environment, where it will go through scouring from jet-stream and extraneous sand, shaking of blades and corrosion from corrosive medium, taking moisture, salt, SO2 for example. Due to the shortage of scouring resistant and anti-corrosion property, shedding of damaged coating is a fundamental reason for the breakdown of aircraft engine blades, which is also the technique bottleneck that hinders the engineering application of compressor blades. Aiming at such problems, an amino modified epoxy coating which performed excellent scouring resistent and anti-corrosion property was fabricated on blades in this paper. Physical properties, anti-corrosion performance, abrasion resistant profiles and scouring resistant test were comprehensively evaluated. Results showed that the coating displayed a high hardness (pendulum hardness 0.9), overlong pot life, well anti-corrosion performance and excellent scouring resistant property. Pot life extends from 8h which is that of common coatings to 36h, so that it is benefit to large scale coating in engineering application. The anti-corrosion performance is similar to traditional aluminizing/inorganic silicate protect coatings, and abrasion resistant property is superior to common protect coatings. Moreover, scouring resistance performance is 3~4 times that of traditional coatings. Hence, such protective coatings could ensure the long lasting of blades protection.

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Kizuka, N., K. Sagae, S. Anzai, S. Marushima, T. Ikeguchi, and K. Kawaike. "Conceptual Design of the Cooling System for 1700°C-Class, Hydrogen-Fueled Combustion Gas Turbines." Journal of Engineering for Gas Turbines and Power 121, no. 1 (January 1, 1999): 108–15. http://dx.doi.org/10.1115/1.2816296.

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The effects of three types of cooling systems on the calculated operating performances of a hydrogen-fueled thermal power plant with a 1,700°C-class gas turbine were studied with the goal of attaining a thermal efficiency of greater than 60 percent. The combination of a closed-circuit water cooling system for the nozzle blades and a steam cooling system for the rotor blades was found to be the most efficient, since it eliminated the penalties of a conventional open-circuit cooling system which ejects coolant into the main hot gas stream. Based on the results, the water cooled, first-stage nozzle blade and the steam cooled first-stage rotor blade were designed. The former features array of circular cooling holes close to the surface and uses a copper alloy taking advantage of recent coating technologies such as thermal barrier coatings (TBCs) and metal coatings to decrease the temperature and protect the blade core material. The later has cooling by serpentine cooling passages with V-shaped staggered turbulence promoter ribs which intensify the internal cooling.

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17

Michaut, Jerome, and Takuya Maekawa. "Influence by Coating Blade on Coating Machine Operation." JAPAN TAPPI JOURNAL 60, no. 12 (2006): 1838–43. http://dx.doi.org/10.2524/jtappij.60.1838.

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Rajasekar, N., P. M. Shivraj, C. J. Thomas Renald, K. Karthick, and M. P. Tamizhmani. "Thermal Analysis & Studies on Low Pressure Gas Turbine Blades Coated with Yitria Stabilized Zirconia (YSZ)." Advanced Materials Research 622-623 (December 2012): 1596–600. http://dx.doi.org/10.4028/www.scientific.net/amr.622-623.1596.

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The thermal barrier coatings have many potential applications in the protection of gas turbine engine components, essentially the turbine blades.In this study micro analysis was carried out on Yitria Stabilized Zirconia(YSZ) coated turbine blades and the results are compared with the uncoated blades.We have used the atmosphere plasma sprayed thermal barrier coating with a thickness of 0.25mm to withstand the high temperature of about 2000 C.We observed that by increasing the thermal coating thickness of about 0.25mm cause to increase 50% of the surface temperature of the turbine blade,which in turn increased the aero engine thrust.

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Anaraki, A. Pourkamali, J. Kadkhodapour, and N. Kangarani Farahani. "Study of solid particle impact effects and coating thickness on the erosion damage." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 16 (March 3, 2014): 2861–70. http://dx.doi.org/10.1177/0954406214524546.

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The development of high performance coatings for the protection against erosion requires understanding of their complex failure mechanisms occurring during solid particle impact. In the present work, a numerical analysis is carried out to study the effect of particle diameter, particle velocity, and coating thickness on erosion damage of gas turbine blade coating caused by solid particle erosion. For this purpose, the performance assessment of turbine blade coating is done using scanning electron microscopic testing. Furthermore, simulation of the impact of a solid particle on a plate is performed by finite element method using the commercially available software ABAQUS. In particular, the following values of the particle diameter ( dP), the particle velocity ( VP), and coating thickness ( tC) have been analyzed: 20 µm ≤ dP ≤80 µm, 80 m/s ≤ VP ≤120 m/s and 5 µm ≤ tC ≤12 µm. The results demonstrate that in erosion of gas turbine blade coating the particle velocity is 1.6 times more effective than the particle diameter and 7.3 times more effective than the coating thickness.

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Tabakoff, W., A. Hamed, and V. Shanov. "Blade Deterioration in a Gas Turbine Engine." International Journal of Rotating Machinery 4, no. 4 (1998): 233–41. http://dx.doi.org/10.1155/s1023621x98000190.

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A study has been conducted to predict blade erosion of gas turbine engines. The blade material erosion model is based on three dimensional particle trajectory simulation in the three-dimensional turbine flow field. The trajectories provide the special distribution of the particle impact parameters over the blade surface. A semi-empirical erosion model, derived from erosion tests of material samples at different particulate flow conditions, is used in the prediction of blade surface erosion based on the trajectory impact data. To improve the blade erosion resistance and to decrease the blade deterioration, the blades must be coated. For this purpose, an experimental study was conducted to investigate the behavior of rhodium platinum aluminide coating exposed to erosion by fly ash particles. New protective coatings are developed for erosion and thermal barrier. Chemical vapor deposition technique (CVD) was used to apply the ceramic TiC coatings on INCO 718 and stainless steel 410. The erosive wear of the coated samples was investigated experimentally by exposing them to particle laden flow at velocities from 180 to 305m/s and temperatures from ambient to538°C in a specially designed erosion wind tunnel. Both materials (INCO 718 and stainless steel 410) coated with CVD TiC showed one order of magnitude less erosion rate compared to some commercial coatings on the same substrates.

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Sadowski, Tomasz, and Daniel Pietras. "Heat Transfer Process in Jet Turbine Blade with Functionally Graded Thermal Barrier Coating." Solid State Phenomena 254 (August 2016): 170–75. http://dx.doi.org/10.4028/www.scientific.net/ssp.254.170.

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In the jet engine the temperature of exhaust gases should be as high as possible, from the point of view of its efficiency. The value of this temperature is limited by toughness of the turbine blades material. Superalloy Inconel 625, which is commonly used in aerospace industry, indicates 13% less yield point in 800OC than in 25OC. The temperature of exhaust gases can reach 1500OC. The blade material has to be protected due to this fact. The one possibility of turbine blade protection is using of thermal barriers coatings (TBC). The coating has a very low thermal conductivity and therefore it protects against the thermal shock failure of the substrate material. The TBC can be manufactured as: 1) monocrystalline, 2) layered structures (e.g. [1-3]) or 3) as a functionally graded material (e.g. [4-7]). The differences between the properties of blade material and TBC can lead to significant increase of the high shear stresses in the substrate-TBC interface.In this paper numerical analyses of cooled turbine blade with various kinds of functionally graded thermal coatings were performed. The main aim was to find the optimal material properties distribution of the functionally graded TBC to avoid damage initiation and growth between TBC and substrate. In the calculations the effect of temperature on material properties both mechanical and thermal was taken into consideration.

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Duramou, Yann, Rodolphe Bolot, Jean Louis Seichepine, Yoann Danlos, Pierre Bertrand, Ghislain Montavon, and Serge Selezneff. "Relationships between Microstructural and Mechanical Properties of Plasma Sprayed AlSi-Polyester Composite Coatings: Application to Abradable Materials." Key Engineering Materials 606 (March 2014): 155–58. http://dx.doi.org/10.4028/www.scientific.net/kem.606.155.

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Abradable coatings are widely used within aeroengines. These materials are applied onto the inner surface of compressor and turbine shroud sections using thermal spray processes, coating the periphery of the blade rotation path. The functionality of an abradable seal is to wear preferentially when rotating blades come into contact with it, while minimizing the over-tip clearance, and improving the overall efficiency of the engine. This study is concerned with the relationships between the microstructure and mechanical properties of atmospheric plasma sprayed AlSi-Polyester composite coatings.

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Tenango-Pirin, Oscar, Elva Reynoso-Jardón, Juan Carlos García, Yahir Mariaca, Yuri Sara Hernández, Raúl Ñeco, and Omar Dávalos. "Effect of Thermal Barrier Coating on the Thermal Stress of Gas Microturbine Blades and Nozzles." Strojniški vestnik – Journal of Mechanical Engineering 66, no. 10 (October 15, 2020): 581–90. http://dx.doi.org/10.5545/sv-jme.2020.6883.

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Thermal barrier coatings play a key role in the operational life of microturbines because they reduce thermal stress in the turbine components. In this work, numerical computations were carried out to assess new materials developed to be used as a thermal barrier coating for gas turbine blades. The performance of the microturbine components protection is also evaluated. The new materials were 8YSZ, Mg2SiO4, Y3Ce7Ta2O23.5, and Yb3Ce7Ta2O23.5. For testing the materials, a 3D gas microturbine model is developed, in which the fluid-structure interaction is solved using CFD and FEM. Temperature fields and stress magnitudes are calculated on the nozzle and blade, and then these are compared with a case in which no thermal barrier is used. Based on these results, the non-uniform temperature distributions are used to compute the stress levels in nozzles and blades. Higher temperature gradients are observed on the nozzle; the maximum temperature magnitudes are observed in the blades. However, it is found that Mg2SiO4 and Y3Ce7Ta2O23.5 provided better thermal insulation for the turbine components compared with the other evaluated materials. Mg2SiO4 and Y3Ce7Ta2O23.5 presented the best performance regarding stress and thermal insulation for the microturbine components. Keywords: thermal barrier coating, gas microturbine, turbine blade, thermal stress

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Lungu, Sergiu, Sevasti Mitsi, Antonescu Ion, Dragos Paraschiv, Constatin Rotariu, Ana Bădănac, Sorin Popa, and Camelia Elena Munteanu. "Research on the Growth Sustainability Active Organs of Agricultural Machinery." Applied Mechanics and Materials 809-810 (November 2015): 634–39. http://dx.doi.org/10.4028/www.scientific.net/amm.809-810.634.

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One way to increase the durability of the machine is active surface coatings using new technological processes such as thermal spray coatings, especially the plasma jet. Was made by coating nickel plating process of the plasma jet knife blade for removal of a group from the grower. In order to emphasize increasing the reliability of these knives by coating with nickel, they were mounted on a cultivator with a lot of knives witness, uncovered, and have been used extensively. Data on wear two groups of knives, coated with nickel and witness uncovered were recorded by photometric methods were processed and plotted statisitic. There was a significant decrease of 66.79% in average wear on the knife blades coated with nickel compared to the control, uncoated.

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Kachan, O., and S. Ulanov. "Features of the process of hot extrusion of blanks of the rotor blades of a GTE compressor." Innovative Materials and Technologies in Metallurgy and Mechanical Engineering, no. 1 (September 14, 2021): 41–46. http://dx.doi.org/10.15588/1607-6885-2021-2-7.

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Purpose. Improving the quality of manufacturing of blanks for compressor rotor blades by hot extrusion. Research methods and equipment. The research was carried out using a crank press with a force of 1000 kN, in split dies in accordance with a serial technological process. The dies were heated up to 150 ... 200 °С, to improve the work when extruding the blanks of the rotor blades made from the titanium alloy ВT8. The thickness of the copper coating was measured with an ИTMП-3 magnetic induction device with an error of ± 2 μm. X-ray spectral microanalysis was performed on an ISM-6360ALA scanning microscope. The billets were heated in an MП-2В furnace. Results. It has been established that the quality of blade blanks made of ВT8 titanium alloy obtained by hot extrusion is influenced by the state of the copper coating, which is preliminarily applied to the surface of the original blank. When the initial blanks are heated, copper is oxidized and in the temperature range of 250…700 °С the oxidation rate proceeds according to a linear pattern, and after 700…750 °С – according to a parabolic pattern. Oxidation of the copper coating occurs unevenly not only within one workpiece, but also within the batch, which leads to a decrease in durability and deterioration of the surface quality of the blade workpieces obtained by hot extrusion. Research carried out by X-ray spectral microanalysis of the copper coating revealed the presence of aluminum oxides of varying degrees of dispersion. The source of this material in the copper coating is caricature of corundum used in blowing into the surface of the billet, which is the reason for the appearance of scoring on the blade blank. It was also found that longitudinal marks on the blade are a consequence of the appearance of a matrix of tubercles (sagging) on the working surface of the die, caused by the adhesion of the deformable material of the blade to the base metal of the tool. Scientific novelty. The regularity of the influence of the heating temperature of the initial blank of the blade on the oxidation rate of the copper coating has been established. The mechanism of the influence of the oxidation of the copper coating and the adhesion of contacting materials during hot extrusion on the surface condition of the resulting blanks is disclosed. Practical value. The results obtained make it possible to improve the quality of the manufactured blanks of the compressor rotor blades by hot extrusion.

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Svoren, Jan, Lubomir Javorek, and Lubomir Nascák. "Interchange of Heat in Saw Disc Body During Cutting." International Journal of Engineering and Management Sciences 4, no. 1 (March 3, 2019): 488–94. http://dx.doi.org/10.21791/ijems.2019.1.60.

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The paper presents the experimental results of a research aimed at the distribution of the temperature on the circular saw blade body. The temperature was measured at two distances from the centre of the circular saw blade body (70 mm, 140 mm) by means of an infrared thermometer. Two circular saw blades with the diameter of 350 mm and a variable adjustment of the body (with slots and without the coating, with both slots and coating) were used for the longitudinal sawing of the spruce wood (Picea excelsa) with the thickness of h = 37 mm. Feed speeds ware vf1 = 14 mpm, vf2 = 17 mpm and vf3 = 20 mpm. Cutting revolutions n = 4100 /min. were constant. The measured temperature was in the range from 21 °C till 27 °C. The highest measured temperatures were recorded on the circular saw blade with the slots and coating.

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Park, Jun-Ik, Hyun-Seok Jeong, Premkumar Vincent, Jihwan Park, Do-Kyung Kim, Jaewon Jang, In Man Kang, et al. "Effect of High-Speed Blade Coating on Electrical Characteristics in Polymer Based Transistors." Journal of Nanoscience and Nanotechnology 20, no. 9 (September 1, 2020): 5486–90. http://dx.doi.org/10.1166/jnn.2020.17615.

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We explore the effect of high-speed blade coating on electrical characteristics of conjugated polymer-based thin-film transistors (TFTs). As the blade-coating speed increased, the thickness of the polymer thin-film was naturally increased while the surface roughness was found to be unchanged. Polymer TFTs show two remarkable tendencies on the magnitude of field-effect mobility with increasing blade-coating speed. As the blade-coating speed increased up to 2 mm/s, the fieldeffect mobility increased to 4.72 cm2V−1s−1. However, when the coating speed reached 6 mm/s beyond 2 mm/s, the field-effect mobility rather decreased to 3.18 cm2V−1s−1. The threshold voltage was positively shifted from 2.09 to 8.29 V with respect to increase in blade-coating speed.

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RENVALL, STIG, and STEFAN KUNI. "Coat weight control in bent blade mode." May 2013 12, no. 5 (June 1, 2013): 31–38. http://dx.doi.org/10.32964/tj12.5.31.

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Bent blade metering is the most common method used in board coating. As board machine speeds today have increased, new requirements have been set on blade geometry and accuracy of blade adjustments. A good understanding of the blade parameters and physical phenomena around the blade tip area is, therefore, necessary. Automatic coat weight profile adjustment using feedback from the coat weight measurement system is a great tool to improve the cross-direction coating uniformity and reel condition. In bent blade coating, however, the parameters for adjusting the cross-direction profilers need to be modified from those used in stiff blade coating. At high board coating speeds with bent blade, good coat weight control will require tuning of the blade parameters. To be able to reach a given coat weight at a high speed with a low tip angle, a high mechanical force is needed to control the high dynamic forces that are created in the blade tip area. The mechanical force can be increased either with a thicker blade or with a shorter free stick-out (i.e., shorter distance between the blade support bar and the blade tip). A higher tip angle can be used to decrease the dynamic forces to keep the coat weight in target; however, coating coverage and uniformity of the coating layer will then be reduced. Furthermore, blade wear is more severe at higher tip angles. For cross-direction profiling, a shorter free stick-out is suggested as a better approach than use of a thicker blade. The coat weight profile response and accuracy improves with a shorter stick-out as thinner blade with more flexibility can be used. Three alternative coat weight control methods for bent blade operation are discussed: blade load adjustment, beam angle adjustment, and load adjustment at constant tip angle. For effective coat weight cross-direction controls, the blade operating mode and parameters need to be chosen in accordance with the speed and coat weight range at which the coater is operating.

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Lu, Xin, Jie Tang, and Liwen Wang. "Simulation and Experimental Study on Rotor System Dynamic Analysis with the Blade-Coating Rubbing Faults." Shock and Vibration 2021 (September 10, 2021): 1–15. http://dx.doi.org/10.1155/2021/2442760.

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In the modern turbo-machinery, reducing the clearance between the blade tip and casing inner face is an effective method to improve the power performance, but the clearance reduction leads to increased risk of blade-casing rubbing. In this paper, a blade-coating rubbing force model which considered the abradable coating scraping is developed to simulate the rotor system dynamic characteristics at blade-casing rubbing faults with abradable coating. An experimental tester is established to simulate the rotor system blade-casing rubbing faults; the AlSi-ployphenyl ester abradable coating is prepared and introduced into the blade-casing experiment to verify the model. After the vibration and force analysis in simulation and experiment, the dynamic characteristics and the influence factors of blade-casing rubbing rotor system are studied.

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30

Wang, Jiao, Ya Shu Li, Yun Dong Sha, and Qing Kai Han. "Harmonic Responses of Blades with Piezoelectric or Piezomagnetic Coatings." Advanced Materials Research 706-708 (June 2013): 1782–85. http://dx.doi.org/10.4028/www.scientific.net/amr.706-708.1782.

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A successful prediction that whether a compressor blade is able to overcome the resonance fatigue and fatigue life of forced vibration is based on its harmonic response analysis.Hard coatings with metal or ceramic substrate are effective to change the natural characteristics and vibration amplitude of a compressor blade so that to improve the anti-vibration fatigue capability. In this paper, modal analysis and harmonic response analysis based on the finite element method are achieved to investigate the contributions of the two different hard coatings on the natural characteristics and vibration amplitude of a compressor blade. The two kinds of hard coatings are modeled by both anisotropic materials and involving their piezoelectric or piezomagnetic effects. The blade is modeled as an isotropic one. The natural frequencies and vibration amplitude of blade with different coating thickness are numerically calculated and compared. Results show that the hard coatings with different thickness play an important role in the natural characteristics and harmonic response analysis of the blade.

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31

Ion, Ion, Anibal Portinha, Jorge Martins, Vasco Teixeira, and Joaquim Carneiro. "Analysis of the energetic/environmental performances of gas turbine plant: Effect of thermal barrier coatings and mass of cooling air." Thermal Science 13, no. 1 (2009): 147–64. http://dx.doi.org/10.2298/tsci0901147i.

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Zirconia stabilized with 8 wt.% Y2O3 is the most common material to be applied in thermal barrier coatings owing to its excellent properties: low thermal conductivity, high toughness and thermal expansion coefficient as ceramic material. Calculation has been made to evaluate the gains of thermal barrier coatings applied on gas turbine blades. The study considers a top ceramic coating Zirconia stabilized with 8 wt.% Y2O3 on a NiCoCrAlY bond coat and Inconel 738LC as substrate. For different thickness and different cooling air flow rates, a thermodynamic analysis has been performed and pollutants emissions (CO, NOx) have been estimated to analyze the effect of rising the gas inlet temperature. The effect of thickness and thermal conductivity of top coating and the mass flow rate of cooling air have been analyzed. The model for heat transfer analysis gives the temperature reduction through the wall blade for the considered conditions and the results presented in this contribution are restricted to a two considered limits: (1) maximum allowable temperature for top layer (1200?C) and (2) for blade material (1000?C). The model can be used to analyze other materials that support higher temperatures helping in the development of new materials for thermal barrier coatings.

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Park, Jun-Ik, Hyeon-Seok Jeong, Do-Kyung Kim, Jaewon Jang, In Man Kang, Philippe Lang, Yun-Hi Kim, Hyeok Kim, and Jin-Hyuk Bae. "Importance of Blade-Coating Temperature for Diketopyrrolopyrrole-based Thin-Film Transistors." Crystals 9, no. 7 (July 5, 2019): 346. http://dx.doi.org/10.3390/cryst9070346.

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In this work, the effect of blade-coating temperature on the electrical properties of a conjugated donor–acceptor copolymer containing diketopyrrolopyrrole (DPP)-based thin-film transistors (TFTs) was systematically analyzed. The organic semiconductor (OSC) layers were blade-coated at various blade-coating temperatures from room temperature (RT) to 80 °C. No remarkable changes were observed in the thickness, surface morphology, and roughness of the OSC films as the blade-coating temperature increased. DPP-based TFTs exhibited two noticeable tendencies in the magnitude of field-effect mobility with increasing blade-coating temperatures. As the temperature increased up to 40 °C, the field-effect mobility increased to 148% compared to the RT values. On the contrary, when the temperature was raised to 80 °C, the field-effect mobility significantly reduced to 20.9% of the mobility at 40 °C. These phenomena can be explained by changes in the crystallinity of DPP-based films. Therefore, the appropriate setting of the blade-coating temperature is essential in obtaining superior electrical characteristics for TFTs. A blade-coating temperature of 40 °C was found to be the optimum condition in terms of electrical performance for DPP-based TFTs.

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33

Chan, K. S., N. S. Cheruvu, and G. R. Leverant. "Coating Life Prediction for Combustion Turbine Blades." Journal of Engineering for Gas Turbines and Power 121, no. 3 (July 1, 1999): 484–88. http://dx.doi.org/10.1115/1.2818498.

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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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34

Nicolaus, Martin, Kai Möhwald, and Hans Jürgen Maier. "Thermally Sprayed Nickel-Based Repair Coatings for High-Pressure Turbine Blades: Controlling Void Formation during a Combined Brazing and Aluminizing Process." Coatings 11, no. 6 (June 16, 2021): 725. http://dx.doi.org/10.3390/coatings11060725.

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Turbine blades must withstand severe loading conditions and damage can occur during operation due to heat, pressure, foreign objects and hot gas corrosion, despite the protective coatings applied onto the turbine blades. Instead of replacing the damaged components, maintenance, repair and overhaul are key to extend the total service life. Besides welding, the repair of turbine blades by brazing is an established repair process in the industry and involves many individual steps that often require a high degree of manual work. In the present study, a hybrid joining and coating technology was developed to shorten the state-of-the-art process chain for repairing turbine blades. With this approach, a repair coating, which consists of a filler metal, a hot gas corrosion protective layer and an aluminum top layer, is applied by atmospheric plasma spraying. The coated turbine blade then undergoes a heat-treatment so that a brazing and aluminizing process is carried out simultaneously. Due to diffusion and segregation processes, pores can occur in the heat-treated coating. In the present study, a full factorial design of experiment was performed to reduce the pores in the coating. The microstructure of the repair coating was investigated by optical- and scanning electron microscopy (SEM), and the impact of the process parameters on the resulting microstructure is discussed.

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35

Maillard, M., C. Mézière, P. Moucheront, C. Courrier, and P. Coussot. "Blade-coating of yield stress fluids." Journal of Non-Newtonian Fluid Mechanics 237 (November 2016): 16–25. http://dx.doi.org/10.1016/j.jnnfm.2016.10.002.

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36

Chang, Yu-Han, Shin-Rong Tseng, Chun-Yu Chen, Hsin-Fei Meng, En-Chen Chen, Sheng-Fu Horng, and Chian-Shu Hsu. "Polymer solar cell by blade coating." Organic Electronics 10, no. 5 (August 2009): 741–46. http://dx.doi.org/10.1016/j.orgel.2009.03.001.

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37

Corvalán, Carlos M., and Fernando A. Saita. "Blade coating on a compressible substrate." Chemical Engineering Science 50, no. 11 (June 1995): 1769–83. http://dx.doi.org/10.1016/0009-2509(95)00013-u.

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38

Saita, Fernando A. "Simplified models of flexible blade coating." Chemical Engineering Science 44, no. 4 (1989): 817–25. http://dx.doi.org/10.1016/0009-2509(89)85255-8.

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39

KRITZINGER, JOHANNES, WOLFGANG BAUER, PEKKA SALMINEN, and JANET PRESTON. "A novel approach to quantify spatial coating-layer formation." November 2010 9, no. 11 (December 1, 2010): 7–13. http://dx.doi.org/10.32964/tj9.11.7.

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A straightforward correlation of coating thickness and base sheet surface height (topography) data does not clearly show the expected differences between a contour coat-like structure for curtain coating or a leveling coat-like structure for blade coating. We defined a measure to clearly distinguish between these different kinds of spatial coating-layer formation. Filtering in the frequency domain preserves only the large structures in the coating-layer thickness and the base sheet topography data. The coefficient of determination (R²) and the slope of a linear regression model, between filtered coating thickness and base sheet surface height (topography), are the measures used to describe the leveling behavior of a coating layer. Three application systems—blade, film press, and curtain coating—were compared. Analysis of the original data showed only minor differences in the coating-layer formation between the application systems. For the filtered data where large structures are preserved, curtain coating gave an almost ideal contour coat, where coating thickness was hardly influenced by base sheet topography. The coating thickness in blade coating strongly depended on local base sheet surface height variations. A film press application of the coating layer resulted in a coating structure between curtain and blade coating.

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40

Hamed, Awatef A., Widen Tabakoff, Richard B. Rivir, Kaushik Das, and Puneet Arora. "Turbine Blade Surface Deterioration by Erosion." Journal of Turbomachinery 127, no. 3 (March 1, 2004): 445–52. http://dx.doi.org/10.1115/1.1860376.

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This paper presents the results of a combined experimental and computational research program to investigate turbine vane and blade material surface deterioration caused by solid particle impacts. Tests are conducted in the erosion wind tunnel for coated and uncoated blade materials at various impact conditions. Surface roughness measurements obtained prior and subsequent to the erosion tests are used to characterize the change in roughness caused by erosion. Numerical simulations for the three-dimensional flow field and particle trajectories through a low-pressure gas turbine are employed to determine the particle impact conditions with stator vanes and rotor blades using experimentally based particle restitution models. Experimental results are presented for the measured blade material/coating erosion and surface roughness. The measurements indicate that both erosion and surface roughness increase with impact angle and particle size. Computational results are presented for the particle trajectories through the first stage of a low-pressure turbine of a high bypass turbofan engine. The trajectories indicate that the particles impact the vane pressure surface and the aft part of the suction surface. The impacts reduce the particle momentum through the stator but increase it through the rotor. Vane and blade surface erosion patterns are predicted based on the computed trajectories and the experimentally measured blade coating erosion characteristics.

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41

Khaliq, Sabeeh, and Zaheer Abbas. "Non-isothermal blade coating analysis of viscous fluid with temperature-dependent viscosity using lubrication approximation theory." Journal of Polymer Engineering 41, no. 8 (June 14, 2021): 705–16. http://dx.doi.org/10.1515/polyeng-2021-0087.

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Abstract Blade coating process is studied in a nonisothermal analysis of viscous fluid with temperature-dependent viscosity by employing both plane and exponential coaters. The governing expressions are nondimensionalized and simplified under the assumption of lubrication approximation theory. Then, perturbative technique is used to find the solution for velocity, pressure, temperature distribution, and coating thickness. The influence of dimensionless parameter ε, Graetz number Gz, and normalized coating thickness γ on the velocity, maximum pressure, temperature distribution, and pressure gradient is portrayed through graphs, whereas load and coating thickness variations reported in a tabular manner. It is found that maximum pressure, coating thickness, and blade load decreases for temperature variations in viscosity, which leads to improved efficiency of blade coating process and life of the moving substrate.

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42

Tait, Jeffrey G., Tamara Merckx, Wenqi Li, Cindy Wong, Robert Gehlhaar, David Cheyns, Mathieu Turbiez, and Paul Heremans. "Blade Coating: Determination of Solvent Systems for Blade Coating Thin Film Photovoltaics (Adv. Funct. Mater. 22/2015)." Advanced Functional Materials 25, no. 22 (June 2015): 3444. http://dx.doi.org/10.1002/adfm.201570150.

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43

Frąckowiak, Andrzej, Aleksander Olejnik, Agnieszka Wróblewska, and Michał Ciałkowski. "Application of the Protective Coating for Blade’s Thermal Protection." Energies 14, no. 1 (December 24, 2020): 50. http://dx.doi.org/10.3390/en14010050.

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This paper presents an algorithm applied for determining temperature distribution inside the gas turbine blade in which the external surface is coated with a protective layer. Inside the cooling channel, there is a porous material enabling heat to be transferred from the entire volume of the channel. This algorithm solves the nonlinear problem of heat conduction with the known: heat transfer coefficient on the external side of the blade surface, the temperature of gas surrounding the blade, coefficients of heat conduction of the protective coating and of the material the blade is made of as well as of the porous material inside the channel, the volumetric heat transfer coefficient for the porous material and the temperature of the air flowing through the porous material. Based on these data, the distribution of material porosity is determined in such a way that the temperature on the boundary between the protective coating and the material the blade is made of is equal to the assumed distribution To. This paper includes results of calculations for various thicknesses of the protective coating and the given constant values of temperature on the boundary between the protective coating and the material the blade is made of.

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44

Bai, Xupeng, Yongming Yao, Zhiwu Han, Junqiu Zhang, and Shuaijun Zhang. "Study of Solid Particle Erosion on Helicopter Rotor Blades Surfaces." Applied Sciences 10, no. 3 (February 3, 2020): 977. http://dx.doi.org/10.3390/app10030977.

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In this study, titanium alloy (Ti-4Al-1.5Mn), magnesium alloy (Mg-Li9-A3-Zn3), or aluminum alloy (Al7075-T6) were used to construct the shell model of helicopter rotor blade to study the solid particle erosion of helicopter rotor blades. The erosion resistance of the three materials at different angles of attack (6°, 3°, or 0°) and particle collision speeds (70, 150, or 220 m/s) was examined using the finite volume method, the discrete phase method, and erosion models. In addition, the leading edge of the helicopter blades was coated with two types of bionic anti-erosion coating layers (V- and VC-type), in an attempt to improve erosion resistance at the angles of attack and particle collision speeds given above. The results showed that Ti-4Al-1.5Mn had the best erosion resistance at high speed, followed by Al7075-T6 and Mg-Li9-A3-Zn3. The angle of attack appeared to affect only the surface area of the blade erosion, while the erosion rate was not affected. Finally, the results of this article showed that the V-type bionic coating had better erosion resistance than the VC-type coating at the same impact speeds. The angle of attack did not have a significant effect on the erosion rate of the bionic coating.

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Kumar, Manoj, and Rohit Upadhyaya. "Corrosion and wear analysis of HVOLF sprayed WC-10CO-4Cr coating on geothermal turbine blade." World Journal of Engineering 16, no. 6 (December 2, 2019): 768–74. http://dx.doi.org/10.1108/wje-03-2019-0089.

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Purpose The purpose of this paper is to develop the high pressure high-velocity oxy-liquid fuel sprayed WC-10Co-4Cr coatings on geothermal turbine 9Cr-1Mo steel for protection against wear and corrosion. Design/methodology/approach The microstructural characterization of as-deposited and corroded coating was done and presented using X-ray diffraction and scanning electron microscope/energy dispersive spectroscopy analysis. Findings The developed coating offered 50 per cent enhanced microhardness (1,200 HV) and 100 per cent enhanced wear resistance, in comparison to bare geothermal turbine steel, respectively. The coating has shown enhanced life in the simulated working conditions (fog test and dip test). This may be because of the high microhardness of the developed coating as per the proven tribological theories. Originality/value Coating offered excellent corrosion resistance in the harsher simulated environments to geothermal turbines.

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Kanwal, Marya, Xinhua Wang, Hasan Shahzad, Yingchun Chen, and Hui Chai. "Blade coating analysis of viscous nanofluid having Cu–water nanoparticles using flexible blade coater." Journal of Plastic Film & Sheeting 36, no. 4 (March 9, 2020): 348–67. http://dx.doi.org/10.1177/8756087920910480.

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This article presents the blade coating analysis of viscous nanofluid passing over a porous substrate using a flexible blade coater. Water-based copper nanoparticles are considered to discuss the blade coating process. The lubrication approximation theory is applied to develop the flow equations. The analytical solution is obtained for velocity, volumetric flow rate, and pressure gradient, while shooting method is applied to obtain the pressure, thickness, and load. Different models for dynamic viscosity have been applied to observe the impact of related parameters on pressure, pressure gradient, and velocity. These results are presented graphically. Interesting engineering quantities such as load, deflection, and thickness are computed numerically and are shown in the tabulated form. It is found that nanoparticle volume fraction increases the pressure gradient, pressure and has minor effects on velocity. For model 1, an increase in the volume fraction reduces the coating thickness, load, and deflection, while model 2 has opposite effects on the mentioned quantities. Also, model 2 has a greater impact on pressure and pressure gradient when compared to model 1.

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47

Wang, Yong, Zilong Zhang, Jie Chen, Houlin Liu, Xiang Zhang, and Marko Hočevar. "Effect of Blade Coating on a Centrifugal Pump Operation under Sediment-Laden Water Flow." Strojniški vestnik – Journal of Mechanical Engineering 66, no. 10 (October 15, 2020): 591–601. http://dx.doi.org/10.5545/sv-jme.2020.6707.

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Applying a high strength coating on a blade’s surface could significantly prolong the service life of a centrifugal pump under sediment-laden water flow because of its protection. To explore the effect of blade coating, the characteristics of energy, vibration and pressure fluctuation of a centrifugal pump (the specific speed (ns) is 81.46) with different polyurethane coating thickness coefficients were experimentally studied under sediment-laden water flow. Keeping the blade outlet angle, blade inlet angle and blade shape unchanged, the head H and efficiency η under both sediment-laden flow and clear water flow decrease significantly as the coating thickness coefficient increases. The axis rotating frequency and blade passing frequency are the main excitation frequencies of the pump vibration velocity amplitude and outlet pressure fluctuation. The vibration velocity amplitude and outlet pressure fluctuation at the frequency of 1 BPF are the largest. At the frequency of 1 axis rotating frequency, they are the second in all cases. The peak values of both vibration velocity amplitude and outlet pressure fluctuation are proportional to the coating thickness coefficient. An analysis was performed for several increasing coating thicknesses, corresponding to coating coefficients from K0 to K3. When the coating thickness coefficients are K0, K1, and K2, the peak value of vibration velocity amplitude under sediment-laden flow is larger than that under clear water flow, but the very small difference between them undercoating thickness coefficient K3. The peak values of pressure fluctuations under different flow rates decrease first and then increase with the increasing coating thickness coefficient, and lowest points are all located at the coating thickness coefficient K1.

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48

Akoshima, Megumi, Tetsuya Baba, Mitsue Ogawa, Takashi Tanaka, Yoshio Harada, Akira Kawasaki, and Fumio Ono. "Thermal Diffusivity Measurements of the Layered Materials by the Laser Flash Method." Materials Science Forum 631-632 (October 2009): 103–8. http://dx.doi.org/10.4028/www.scientific.net/msf.631-632.103.

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Ceramics-based thermal barrier coatings are used as heat and wear shields of blades of gas turbine. There are strong needs to evaluate thermophysical properties of coatings, such as thermal conductivity, thermal diffusivity and heat capacity of them. Since coatings are attached on substrates, it is not easy to measure these properties separately. In order to evaluate the thermal diffusivity of coating attached on substrate, we have tried to apply the multi-layer model based on the response function method and established a procedure for the measurement by the laser flash method. We verified the procedure by the measurements from room temperature to about 1000 K for two-layer ceramics sample prepared by the doctor blade tape casting method. The thermally sprayed CoNiCrAlY coating on the SUS304 substrate was also used for verification. The thermal diffusivity of coating attached on substrate approximately agreed with that of the single-layer coating removed from substrate. In the case of the ceramics sample, the thermal diffusivity of the coating including the interfacial thermal resistance determined within about 20 % uncertainty. We compared the laser flash measurement signals of the samples prepared by the thermal spraying with variant thickness and found the difference among them. It was found that the procedure has enough resolution to detect the heat shield effect caused by the change with about 200 m in thickness. The result shows that the procedure and analysis were practically effective for the thermal diffusivity estimation of coating attached on the substrate without remove from substrate.

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49

Myna, Roman, Raphaela Hellmayr, Maria Georgiades, Lena Maria Leiter, Stephan Frömel-Frybort, Rupert Wimmer, and Falk Liebner. "Can Surface Coating of Circular Saw Blades Potentially Reduce Dust Formation?" Materials 14, no. 18 (September 7, 2021): 5123. http://dx.doi.org/10.3390/ma14185123.

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Coating of steel is a frequently applied approach to increase the resistance of moving machine parts towards abrasion, surface oxidation, and corrosion. Here, we show that plating circular saw blades with certain metals can help to reduce the electrical charging of wood dust during cutting, which has significant implications for occupational safety, healthcare, and lifetime of filter systems. With the example of beech wood planks, machine net energy consumption EV (J cm−3) and cumulated field strength E→V (kV m−4) as caused by electrically charged particles were compared for cutting of 10- and 20-mm deep grooves (800 mm length) using saw blades of different toothing (24, 60 teeth) and surface coating (Cu, Ag, and Cr). To ensure uniform feed per tooth (fz = 0.063 mm), saw blades were operated at different rotation speeds (4000 vs. 1600 rpm). The results demonstrate that the extent of electrostatic sawdust charging can be manipulated to a certain extent by the type of saw blade plating. Coating with chromium turned out to be most effective in shifting the electrostatic charge of the wood particles towards neutralization. Lowering of rotation speed using circular saw blades of higher toothing was an additional measure significantly reducing electrostatic charging of wood dust. Hence, cutting with a chrome-coated blade with 60 teeth can be specifically recommended as the reduction of electrical saw dust charging is not associated with higher machine power consumption.

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Villeneuve, Eric, Caroline Blackburn, and Christophe Volat. "Design and Development of an Experimental Setup of Electrically Powered Spinning Rotor Blades in Icing Wind Tunnel and Preliminary Testing with Surface Coatings as Hybrid Protection Solution." Aerospace 8, no. 4 (April 2, 2021): 98. http://dx.doi.org/10.3390/aerospace8040098.

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Abstract:

In order to study ice protection systems for rotating blades, a new experimental setup has been developed at the Anti-Icing Materials International Laboratory (AMIL). This system consists of two small-scale rotating blades in a refrigerated icing wind tunnel where atmospheric icing can be simulated. Power is brought to the blades through a slip ring, through which the signals of the different sensors that are installed on the blades also pass. As demonstrated by the literature review, this new setup will address the need of small-scale wind tunnel testing on electrically powered rotating blades. To test the newly designed apparatus, preliminary experimentation is done on a hybrid ice protection system. Electrothermal protection is combined with different surface coatings to measure the impact of those coatings on the power consumption of the system. In anti-icing mode, the coatings tested did not reduce the power consumption on the system required to prevent ice from accumulating on the leading edge. The coatings however, due to their hydrophobic/superhydrophobic nature, reduced the power required to prevent runback ice accumulation when the leading edge was protected. One of the coatings did not allow any runback accumulation, limiting the power to protect the whole blades to the power required to protect solely the leading edge, resulting in a potential 40% power reduction for the power consumption of the system. In de-icing mode, the results with all the substrates tested showed similar power to achieve ice shedding from the blade. Since the coatings tested have a low icephobicity, it would be interesting to perform additional testing with icephobic coatings. Also, a small unheated zone at the root of the blade prevented complete ice shedding from the blade. A small part of the ice layer was left on the blade after testing, meaning that a cohesive break had to occur within the ice layer, and therefore impacting the results. Improvements to the setup will be done to remedy the situation. Those preliminary testing performed with the newly developed test setup have demonstrated the potential of this new device which will now allow, among other things, to measure heat transfer, force magnitudes, ice nucleation, and thermal equilibrium during ice accretion, with different innovative thermal protection systems (conductive coating, carbon nanotubes, impulse, etc.) as well as mechanical systems. The next step, following the improvements, is to measure forced convection on a thermal ice protection system with and without precipitation and to test mechanical ice protection systems.

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Journal articles on the topic 'Blade coating'

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