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Relevant bibliographies by topics / Low blade temperatures

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Academic literature on the topic 'Low blade temperatures'

Author: Grafiati

Published: 4 June 2021

Last updated: 2 February 2022

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Journal articles on the topic "Low blade temperatures"

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Cheng, Wenjie, Boqin Gu, and Chunlei Shao. "A numerical study on the steady flow in molten salt pump under various conditions for improved hydraulic performance." International Journal of Numerical Methods for Heat & Fluid Flow 27, no. 8 (2017): 1870–86. http://dx.doi.org/10.1108/hff-06-2016-0238.

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Purpose This paper aims to figure out the steady flow status in the molten salt pump under various temperatures and blade number conditions, and give good insight on the structure and temperature-dependent efficiencies of all pump cases. Finally, the main objective of present work is to get best working condition and blade numbers for optimized hydraulic performance. Design/methodology/approach The steady flow in the molten salt pump was studied numerically based on the three-dimensional Reynolds-Averaged Navier–Stokes equations and the standard k-ε turbulence model. Under different temperatur

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Bachelez, Andreas, and Steven A. Martinez. "Heat Generation by Two Different Saw Blades Used for Tibial Plateau Leveling Osteotomies." Journal of the American Animal Hospital Association 48, no. 2 (2012): 83–88. http://dx.doi.org/10.5326/jaaha-ms-5698.

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During tibial plateau leveling osteotomy (TPLO) the saw blade produces frictional heat. The purpose of this study was to evaluate and compare heat generated by two TPLO blade designs (Slocum Enterprises [SE] and New Generation Devices [NDG]), with or without irrigation, on cadaveric canine tibias. Thirty-six paired tibias were used to continuously measure bone temperatures during osteotomy through both cortices (i.e., the cis and trans cortices). Each pair was assigned to either an irrigation or nonirrigation group during osteotomy, and each tibia within a pair was osteotomized using a differe

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Arakere, N. K. "High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and Hydrogen." Journal of Engineering for Gas Turbines and Power 126, no. 3 (2004): 590–603. http://dx.doi.org/10.1115/1.1501075.

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Hot section components in high-performance aircraft and rocket engines are increasingly being made of single crystal nickel superalloys such as PWA1480, PWA1484, CMSX-4, and Rene N-4 as these materials provide superior creep, stress rupture, melt resistance, and thermomechanical fatigue capabilities over their polycrystalline counterparts. Fatigue failures in PWA1480 single crystal nickel-base superalloy turbine blades used in the space shuttle main engine fuel turbopump are discussed. During testing many turbine blades experienced stage II noncrystallographic fatigue cracks with multiple orig

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Guijarro, Rubén, Alberto Tapetado, David Sánchez Montero, and Carmen Vázquez. "Cleaving of PMMA Microstructured Polymer Optical Fibers with 3- and 4-Ring Hexagonal Cladding Structures." Polymers 13, no. 9 (2021): 1366. http://dx.doi.org/10.3390/polym13091366.

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The cleaving of a novel microstructured polymer optical fiber (mPOF) to obtain an acceptable connectorized fiber end-face is studied. The effect of the blade temperature and the speed of the cutting blade on the end-face is qualitatively assessed. Recently manufactured mPOFs with air-structured 3- and 4-ring hexagonal-like hole cladding structures with outer fiber diameters of around 250 μm are employed. Good quality end-faces can be obtained by cleaving mPOF fibers at room temperature for blade temperatures within the range 60–80 °C and at a low blade speed at 0.5 mm/s. The importance of the

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Wang, Xiaopeng, Wenchen Xu, Peng Xu, Haitao Zhou, Fantao Kong, and Yuyong Chen. "High Nb–TiAl Intermetallic Blades Fabricated by Isothermal Die Forging Process at Low Temperature." Metals 10, no. 6 (2020): 757. http://dx.doi.org/10.3390/met10060757.

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In this study, the isothermal die forging process of high Nb–TiAl (Ti-44Al-8Nb-0.2W-0.2B-Y, at.%) alloy blades was simulated using the ABAQUS V6.11 software and the blades were fabricated successfully. The influence of a low forging temperature (lower than 1000 °C) and strain rate on the distributions of effective strain and stress were analyzed. The results indicate that the effective strain exhibits negative temperature sensitivity and positive strain rate sensitivity. The stress exponent (n = 3.02) and the apparent activation energy (Q = 293.381 kJ/mol) of the present alloy suggests that th

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Cosack, T., L. Pawlowski, S. Schneiderbanger, and S. Sturlese. "Thermal Barrier Coatings on Turbine Blades by Plasma Spraying With Improved Cooling." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 272–76. http://dx.doi.org/10.1115/1.2906805.

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Turbine blades were coated with a thermal barrier coating system consisting of an MCrAlY bond coat about 100 μm thick deposited by Low-Pressure Plasma Spraying (LPPS) and a 300 μm thick ZrO2-7 wt. % Y2O3 top coat. The latter was manufactured by both Atmosphere and Temperature Controlled Spraying (ATCS) and Air Plasma Spraying (APS) using internal air cooling through the cooling holes of the turbine blades. Coated blades were submitted to thermal cycling tests in a burner rig with hot gas temperature of 1485°C. In the case of ATCS coated blades the number of cycles until the first spallation at

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Weber, H. E. "Wave Engine Aerothermodynamic Design." Journal of Engineering for Gas Turbines and Power 114, no. 4 (1992): 790–96. http://dx.doi.org/10.1115/1.2906658.

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A method for aerothermodynamic preliminary design of a wave engine is presented. The engine has a centrifugal precompressor for the wave rotor, which feeds high and low-pressure turbines. Three specific wave engine designs are presented. Wave rotor blades are naturally cooled by the ingested air; thus combustion temperatures can be as high as 1900 K. Engine pressure ratios of over 25 are obtained in compact designs. It is shown that placing no nozzles at the end of the rotor blade passages yields the highest cycle efficiencies, which can be over 50 percent. Rotor blades are straight and easily

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Wilson, M., R. Pilbrow, and J. M. Owen. "Flow and Heat Transfer in a Preswirl Rotor–Stator System." Journal of Turbomachinery 119, no. 2 (1997): 364–73. http://dx.doi.org/10.1115/1.2841120.

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Conditions in the internal-air system of a high-pressure turbine stage are modeled using a rig comprising an outer preswirl chamber separated by a seal from an inner rotor-stator system. Preswirl nozzles in the stator supply the “blade-cooling” air, which leaves the system via holes in the rotor, and disk-cooling air enters at the center of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes, and pressure taps, enabling temperatures, heat fluxes, velocities, and pressures to be measured at a number o

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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 pollutant

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Ford, D. A., K. P. L. Fullagar, H. K. Bhangu, et al. "Improved Performance Rhenium Containing Single Crystal Alloy Turbine Blades Utilizing PPM Levels of the Highly Reactive Elements Lanthanum and Yttrium." Journal of Engineering for Gas Turbines and Power 121, no. 1 (1999): 138–43. http://dx.doi.org/10.1115/1.2816301.

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Turbine inlet temperatures have now approached 1650°C (3000°F) at maximum power for the latest large commercial turbofan engines, resulting in high fuel efficiency and thrust levels approaching or exceeding 445 kN (100,000 lbs.). High reliability and durability must be intrinsically designed into these turbine engines to meet operating economic targets and ETOPS certification requirements. This level of performance has been brought about by a combination of advances in air cooling for turbine blades and vanes, computerized design technology for stresses and airflow, and the development and app

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Dissertations / Theses on the topic "Low blade temperatures"

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Gillespie, David R. H. "Intricate internal cooling systems for gas turbine blading." Thesis, University of Oxford, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.365831.

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Antill, Marc. "The effect of repair welds on the high temperature low cycle fatigue behaviour of nickel base superalloy turbine blades." Thesis, University of Bristol, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.297923.

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Lin, Hsin-I., and 林欣熠. "Low-Temperature Growth of Photocatalytic TiO2 on Plastic Fan Blade for Air Purification and its Mechanical Performance." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/00301190415378974848.

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碩士<br>逢甲大學<br>材料科學所<br>97<br>Arc ion plating (AIP) beneficial from high cathode ionization rate, simple procedure, low process temperature, high film deposition rate, strong film adhesion and environmental friendly, are employed in this study to establish the coating technique for depositing photocatalytic titanium dioxide layer on poly-butylene terephthalate (PBT) surface. The correlation among deposition parameter, microstructure, crystalline structure and mechanical performance of TiO2 coating were discussed as well. Furthermore, the photodecomposition efficiency of methanol for TiO2-coated

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Conference papers on the topic "Low blade temperatures"

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Chappel, D., H. Howe, and L. Vo. "Abradable seal testing - Blade temperatures during low speed rub event." In 37th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3479.

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Kenkare, A. S., and T. M. Kilner. "A Low-Cost Undergraduate Test Rig for Heat Transfer in Turbine Blade Cooling." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-156.

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Although turbine blade cooling has consistently led to the use of higher turbine inlet temperatures leading to improved cycle efficiencies, very little of this technology has found its way into undergraduate laboratory work. The cost of modern blade heat transfer research rigs virtually rules out the possibility of introducing this topic in undergraduate teaching laboratories of Universities or Polytechnics in the UK operating within tight budgetary constraints. However, the underlying principles of blade cooling heat transfer may be demonstrated quite easily by using inlet temperatures about

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Van Treuren, Kenneth, Tyler Pharris, and Olivia Hirst. "Using Turbulence Intensity and Reynolds Number to Predict Flow Separation on a Highly Loaded, Low-Pressure Gas Turbine Blade at Low Reynolds Numbers." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75976.

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The low-pressure turbine has become more important in the last few decades because of the increased emphasis on higher overall pressure and bypass ratios. The desire is to increase blade loading to reduce blade counts and stages in the low-pressure turbine of a gas turbine engine. Increased turbine inlet temperatures for newer cycles results in higher temperatures in the low-pressure turbine, especially the latter stages, where cooling technologies are not used. These higher temperatures lead to higher work from the turbine and this, combined with the high loadings, can lead to flow separation

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Sidwell, Vince, and David Darmofal. "A Selective Assembly Method to Reduce the Impact of Blade Flow Variability on Turbine Life." In ASME Turbo Expo 2004: Power for Land, Sea, and Air. ASMEDC, 2004. http://dx.doi.org/10.1115/gt2004-53930.

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A selective assembly method is proposed that decreases the impact of blade passage manufacturing variability on the life of a row of cooled turbine blades. The method classifies turbine blades into groups based on the effective flow areas of the blade passages, then a row of blades is assembled exclusively from blades of a single group. A simplified classification is considered in which blades are divided into low-flow, nominal-flow, and high-flow groups. For rows assembled from the low-flow class, the blade plenum pressure will tend to rise and the individual blade flows will be closer to the

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Amano, R. S., Krishna Guntur, and Jose Martinez Lucci. "Computational Study of Gas Turbine Blade Cooling Channel." In 2010 14th International Heat Transfer Conference. ASMEDC, 2010. http://dx.doi.org/10.1115/ihtc14-22920.

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It has been a common practice to use cooling passages in gas turbine blade in order to keep the blade temperatures within the operating range. Insufficiently cooled blades are subject to oxidation, to cause creep rupture, and even to cause melting of the material. To design better cooling passages, better understanding of the flow patterns within the complicated flow channels is essential. The interactions between secondary flows and separation lead to very complex flow patterns. To accurately simulate these flows and heat transfer, both refined turbulence models and higher-order numerical sch

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Martin, Evan L., Lesley M. Wright, and Daniel C. Crites. "Computational Investigation of Jet Impingement on Turbine Blade Leading Edge Cooling With Engine-Like Temperatures." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68811.

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A numerical investigation of leading edge impingement is completed in this study. Impingement onto a half cylinder, concave surface is used to model the leading edge of a modern gas turbine airfoil. The temperature difference between the impinging jet and the target surface is varied from ΔT = 60°F (33.3°C) (typical of traditional laboratory experiments) to ΔT = 1000°F (555.6°C) (representative of temperature differences encountered in modern engines). Over this range of temperatures, the simulations are validated against experimental data and extended to engine-like conditions. In addition to

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Amano, R. S., Krishna Guntur, Jose Martinez Lucci, and Yu Ashitaka. "Study of Flow Through a Stationary Ribbed Channel for Blade Cooling." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23031.

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The firing temperature in gas turbine relates itself directly to the power output and the efficiency of the turbine. The higher the firing (operating) temperatures, higher the wall temperature of blades. However, an increase in the firing temperature is limited by the first stage blade material properties. This is because the higher firing temperature may cause a creep rupture, oxidizing, melting and ultimately failing of blades. Prior to blade cooling, the firing temperature was the same as the blade material temperature. Advancements in cooling technology have resulted in high firing tempera

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Byerley, Aaron R., and August J. Rolling. "Exploring the Impact of Elevated Turbine Blade Cooling Effectiveness and Turbine Material Temperatures on Gas Turbine Engine Performance and Cost." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-44061.

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Since the 1950’s, the turbine inlet temperatures of gas turbine engines have been steadily increasing as engine designers have sought to increase engine thrust-to-weight and reduce fuel consumption. In turbojets and low-bypass turbofan engines, increasing the turbine inlet temperature boosts specific thrust, which in some cases can support supersonic flight without the use of an afterburner. In high-bypass gas turbine engines, increasing the turbine inlet temperature makes possible higher bypass ratios and overall pressure ratios, both of which reduce specific fuel consumption. Increased turbi

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Thibault, D., P. K. Dubois, B. Picard, A. Landry-Blais, J. S. Plante, and M. Picard. "Experimental Assessment of a Sliding-Blade Inside-Out Ceramic Turbine." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15137.

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Abstract In order to reach 40% efficiency, sub-MW turbines must operate in a recuperated gas Brayton cycle at a turbine inlet temperature (TIT) above 1300°C. Current sub-MW turbines have material-related operating temperature limits. Still to this day, there is no cost-effective rotor design which operates at such high temperatures. This paper introduces a novel, sliding-blade, inside-out ceramic turbine (ICT) wheel configuration, which could enable high-efficiency sub-MW recuperated engines to be achieved with cheap monolithic ceramic blades. The inside-out configuration uses a rotating struc

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Cosi, Lorenzo, Jonathon Slepski, Steven DeLessio, Michele Taviani, and Amir Mujezinovic´. "Design, Manufacturing and Testing of a New Family of Steam Turbine Low Pressure Stages." In ASME 2007 Power Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/power2007-22056.

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New low pressure (LP), stages for variable speed, mechanical drive and geared power generation steam turbines have been developed. The new blade and nozzle designs can be applied to a wide range of turbine rotational speeds and last stage blade annulus areas, thus forming a family of low pressure stages—High Speed (HS) blades and nozzles. Different family members are exact scales of each other and the tip speeds of the corresponding blades within the family are identical. Thus the aeromechanical and aerodynamic characteristics of the individual stages within the family are identical as well. L

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