Relevant bibliographies by topics / Low pressure turbine material

Academic literature on the topic 'Low pressure turbine material'

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Published: 14 March 2023

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Journal articles on the topic "Low pressure turbine material"

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Straka, František, Pavel Pánek, and Pavel Albl. "Plastic Behavior of Steam Turbine Low Pressure Part." Applied Mechanics and Materials 827 (February 2016): 197–200. http://dx.doi.org/10.4028/www.scientific.net/amm.827.197.

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Low-pressure steam turbine parts are generally exposed to lowest steam parameters only and it could seem that they should not be susceptible to permanent deformation. However, this assumption is incorrect and permanent changes in geometry become visible in low-pressure turbine casings when they are disassembled after the first time in operation. The driving mechanism of the plastic deformation of the low-pressure casings is mainly the non-uniform temperature field. This paper deals with results obtained from a numerical FEM simulation of a steam turbine low pressure part, which includes elastic-plastic behavior of the material, and results measured under the real conditions.
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Arai, Mikiya, Ryuzo Imamura, Kenji Matsuda, Yukiya Nakagawa, and Takahito Hosokawa. "Development of TiAl Blades for Large Low Pressure Turbine." Materia Japan 36, no. 4 (1997): 394–96. http://dx.doi.org/10.2320/materia.36.394.

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Zhao, Yaping, Jianjun Feng, Zhihua Li, Mengfan Dang, and Xingqi Luo. "Analysis of Pressure Fluctuation of Tubular Turbine under Different Application Heads." Sustainability 14, no. 9 (April 24, 2022): 5133. http://dx.doi.org/10.3390/su14095133.

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The vigorous development of low-head hydraulic resources and tidal energy with greater stability and predictability is drawing attention to tubular turbines. However, many problems, such as incorrect unit association relationship, insufficient unit output, and severe vibration, occur frequently in tubular turbines, particularly when the water head is low. These phenomena cannot be known through model machine tests and numerical studies. Therefore, this study takes the tubular turbine with different water heads as the research object, in accordance with the actual boundary conditions. The unsteady numerical research for the prototype machine is conducted while considering the free surface in the reservoir area and water gravity. The internal flow characteristics of the tubular turbine with different water heads and the influence of free surface on its performance are analyzed. The research indicates the following: affected by the free surface and the water gravity, the pressure in the entire flow passage of the horizontal tubular turbine increases with the increase in the submerged depth. In addition, the short water diversion section allows the water flow from the reservoir area to still have a certain asymmetry before reaching the runner. During the rotation process of the runner, the surface pressure and torque of the blade have evident periodic fluctuations, and the amplitude of the fluctuations will increase significantly with the decrease in H/D1. Moreover, in the case of small H/D1, the amplitude of pressure pulsation in the draft tube is larger, and concentrated high-frequency pressure pulsation occurs. These factors will lead to the occurrence of material fatigue damage, unstable output, and increased vibration in low-head tubular turbines.
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Zhao, Yaping, Jianjun Feng, Zhihua Li, Mengfan Dang, and Xingqi Luo. "Analysis of Pressure Fluctuation of Tubular Turbine under Different Application Heads." Sustainability 14, no. 9 (April 24, 2022): 5133. http://dx.doi.org/10.3390/su14095133.

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The vigorous development of low-head hydraulic resources and tidal energy with greater stability and predictability is drawing attention to tubular turbines. However, many problems, such as incorrect unit association relationship, insufficient unit output, and severe vibration, occur frequently in tubular turbines, particularly when the water head is low. These phenomena cannot be known through model machine tests and numerical studies. Therefore, this study takes the tubular turbine with different water heads as the research object, in accordance with the actual boundary conditions. The unsteady numerical research for the prototype machine is conducted while considering the free surface in the reservoir area and water gravity. The internal flow characteristics of the tubular turbine with different water heads and the influence of free surface on its performance are analyzed. The research indicates the following: affected by the free surface and the water gravity, the pressure in the entire flow passage of the horizontal tubular turbine increases with the increase in the submerged depth. In addition, the short water diversion section allows the water flow from the reservoir area to still have a certain asymmetry before reaching the runner. During the rotation process of the runner, the surface pressure and torque of the blade have evident periodic fluctuations, and the amplitude of the fluctuations will increase significantly with the decrease in H/D1. Moreover, in the case of small H/D1, the amplitude of pressure pulsation in the draft tube is larger, and concentrated high-frequency pressure pulsation occurs. These factors will lead to the occurrence of material fatigue damage, unstable output, and increased vibration in low-head tubular turbines.
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5

Zhao, Yaping, Jianjun Feng, Zhihua Li, Mengfan Dang, and Xingqi Luo. "Analysis of Pressure Fluctuation of Tubular Turbine under Different Application Heads." Sustainability 14, no. 9 (April 24, 2022): 5133. http://dx.doi.org/10.3390/su14095133.

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The vigorous development of low-head hydraulic resources and tidal energy with greater stability and predictability is drawing attention to tubular turbines. However, many problems, such as incorrect unit association relationship, insufficient unit output, and severe vibration, occur frequently in tubular turbines, particularly when the water head is low. These phenomena cannot be known through model machine tests and numerical studies. Therefore, this study takes the tubular turbine with different water heads as the research object, in accordance with the actual boundary conditions. The unsteady numerical research for the prototype machine is conducted while considering the free surface in the reservoir area and water gravity. The internal flow characteristics of the tubular turbine with different water heads and the influence of free surface on its performance are analyzed. The research indicates the following: affected by the free surface and the water gravity, the pressure in the entire flow passage of the horizontal tubular turbine increases with the increase in the submerged depth. In addition, the short water diversion section allows the water flow from the reservoir area to still have a certain asymmetry before reaching the runner. During the rotation process of the runner, the surface pressure and torque of the blade have evident periodic fluctuations, and the amplitude of the fluctuations will increase significantly with the decrease in H/D1. Moreover, in the case of small H/D1, the amplitude of pressure pulsation in the draft tube is larger, and concentrated high-frequency pressure pulsation occurs. These factors will lead to the occurrence of material fatigue damage, unstable output, and increased vibration in low-head tubular turbines.
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6

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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Kozakiewicz, Adam, Stanisław Jóźwiak, Przemysław Jóźwiak, and Stanisław Kachel. "Material Origins of the Accelerated Operational Wear of RD-33 Engine Blades." Materials 14, no. 2 (January 11, 2021): 336. http://dx.doi.org/10.3390/ma14020336.

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The structural and strength analysis of the materials used to construct an important engine element such as the turbine is of great significance, at both the design stage and during tests and training relating to emergency situations. This paper presents the results of a study on the chemical composition, morphology, and phased structure of the metallic construction material used to produce the blades of the high- and low-pressure turbines of the RD-33 jet engine, which is the propulsion unit of the MiG-29 aircraft. On the basis of an analysis of the chemical composition and phased structure, the data obtained from tests of the blade material allowed the grade of the alloy used to construct the tested elements of the jet engine turbine to be determined. The structural stability of the material was found to be lower in comparison with the engine operating conditions, which was shown by a clear decrease in the resistance properties of the blade material. The results obtained may be used as a basis for analyzing the life span of an object or a selection of material replacements, which may enable the production of the analyzed engine element.
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Kozakiewicz, Adam, Stanisław Jóźwiak, Przemysław Jóźwiak, and Stanisław Kachel. "Material Origins of the Accelerated Operational Wear of RD-33 Engine Blades." Materials 14, no. 2 (January 11, 2021): 336. http://dx.doi.org/10.3390/ma14020336.

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The structural and strength analysis of the materials used to construct an important engine element such as the turbine is of great significance, at both the design stage and during tests and training relating to emergency situations. This paper presents the results of a study on the chemical composition, morphology, and phased structure of the metallic construction material used to produce the blades of the high- and low-pressure turbines of the RD-33 jet engine, which is the propulsion unit of the MiG-29 aircraft. On the basis of an analysis of the chemical composition and phased structure, the data obtained from tests of the blade material allowed the grade of the alloy used to construct the tested elements of the jet engine turbine to be determined. The structural stability of the material was found to be lower in comparison with the engine operating conditions, which was shown by a clear decrease in the resistance properties of the blade material. The results obtained may be used as a basis for analyzing the life span of an object or a selection of material replacements, which may enable the production of the analyzed engine element.
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Ghosh, S. J. "Failure Investigation of a Low-Pressure Turbine Blade." Journal of Failure Analysis & Prevention 4, no. 3 (June 1, 2004): 73–77. http://dx.doi.org/10.1361/15477020419866.

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Ghosh, S. J. "Failure investigation of a low-pressure turbine blade." Journal of Failure Analysis and Prevention 4, no. 3 (June 2004): 73–77. http://dx.doi.org/10.1007/s11668-996-0018-6.

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Dissertations / Theses on the topic "Low pressure turbine material"

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He, Binyan. "Fatigue crack growth behaviour in a shot peened low pressure steam turbine blade material." Thesis, University of Southampton, 2015. https://eprints.soton.ac.uk/388077/.

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Williams, Charles P. "Low Pressure Turbine Flow Control with Vortex Generator Jets." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1470741489.

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Verona, Claire L. "Stress corrosion cracking of low pressure steam turbine blade and rotor materials." Thesis, Loughborough University, 2012. https://dspace.lboro.ac.uk/2134/10165.

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Stress corrosion cracking of a 14 wt% Cr martensitic stainless steel, with commercial names PH-15Cr5Ni, FV520B or X4CrNiCuMo15-5, used for the manufacture of low pressure turbine blades, has been studied with the intention of gaining a better understanding of the processes involved, how they occur and why. Industrially this is very important as stress corrosion cracking is considered to be a delayed failure process, whereby microscopic cracks can potentially propagate through a metal undetected until catastrophic failure occurs. The aim of this work is to establish links between crack length and external factors, such as exposure time, in order to devise a method of dating stress corrosion cracks and therefore predicting their possible occurrence in-service.
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Seumangal, Nicole. "Influence of the heat treatment procedure on the stress corrosion cracking behaviour of low pressure turbine blade material FV566." Master's thesis, University of Cape Town, 2017. http://hdl.handle.net/11427/27427.

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Stress corrosion cracking is one of the leading damage mechanisms in low-pressure turbines in the power generation industry; in LP turbine blades it primarily occurs in the last stage blades. The research investigated the influence of tempering temperature on the microstructure, mechanical properties, and stress corrosion cracking properties of 12% chromium FV566 stainless steel, which is used to manufacture LP turbine blades. The standard heat treatment of the steel comprises of austenitising, quenching and double tempering. Austenitising is carried out at 1050°C for one hour - which is sufficiently long to generate a fully austenitic matrix and to dissolve carbon completely. Subsequently, the material is quenched in air. The high level of alloying elements ensures the complete martensitic transformation, with carbon atoms trapped in the matrix and distributed homogeneously. Thereafter, tempering of the material at 580-600°C enhances the ductility and toughness. Tempering replaces the solid solution strengthening of the dissolved carbon with precipitation strengthening by carbides. The final microstructure of the FV566 steel blades is referred to as tempered martensite. van Rooyen showed that for 12% chromium steel tempering at and above 600°C induces passivity of the material against SCC, while tempering of 12% chromium steels at 450-550°C causes sensitisation of the material and the material exhibits intergranular SCC. From such studies, the motivation arises to investigate the impact of heat-treatment parameters - specifically the impact of tempering temperature on the stress corrosion behaviour of the material. The testing methodology comprises heat treatment of FV566 samples at 1050°C for 1 hour, at 350°C for 1 hour, and thereafter tempering for 1 hour at various tempering temperatures. Each stage of heat treatment is followed by air cooling - followed by analysis of the microstructure, mechanical testing and stress corrosion cracking testing of the specimens at the different temper conditions. Stress corrosion testing was divided into two categories. The first set of tests was carried out with U-bend specimens to determine the susceptibility of materials at different heat treatments to SCC, the time taken for SCC to initiate, and the mode of cracking. The second set of tests was conducted to determine the threshold stress intensity, as a function of crack growth rate, for each heat treatment. The SCC failure mechanism observed was intergranular SCC (IGSCC) by anodic dissolution for the 550°C, 560°C, 570°C, 580°C, 590°C, 600°C and 620°C specimens. The material's resistance to SCC improved with increasing tempering temperature. Specimens tempered at 480°C and 550°C were most susceptible to SCC, while specimens tempered at 600°C The material's resistance to SCC improved with increasing tempering temperature. Specimens tempered at 480°C and 550°C were most susceptible to SCC, while specimens tempered at 600°C were immune to SCC in a 4000-hour period. A change in tempering temperature results in a change in the quantity and type of precipitates formed which results in changes in SCC properties of FV566.
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Von, Hagen William J. "Analysis of the L1A, L1M, L2A, and L2F Low-Pressure Turbine Blades Using Large-Eddy Simulation." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1470045392.

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Naicker, Leebashen. "Influence of heat treatment condition on the stress corrosion cracking properties of low pressure turbine blade steel FV520B." Master's thesis, University of Cape Town, 2017. http://hdl.handle.net/11427/25377.

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Stress corrosion cracking (SCC) is a corrosion phenomenon which continues to plague the power generating industry especially in low pressure (LP) steam turbine blades operating in the phase transition zone. An investigation has therefore been conducted to examine the effect of heat treatment condition on the microstructure, mechanical properties and SCC properties of one such LP turbine blade material, FV520B, used in the steam turbines of coal-fired power stations in South Africa. The three stage heat treatment cycle of the FV520B turbine blades consists of homogenisation at 1020°C for 30 minutes, solution treatment at 790°C for two hours and precipitation hardening at 545°C for six hours. In this study, the precipitation hardening temperature was varied in the range 430-600°C to investigate how this variation would affect the material and SCC properties. Hardness and tensile testing were performed to obtain mechanical properties while the investigative techniques used to characterise the microstructures were light microscopy, dilatometry, X-Ray Diffraction (XRD), Scanning Electron Microscopy (SEM) and Transmission Electron Microscopy (TEM). Stress corrosion susceptibility for the different heat treatment conditions was quantified using U-bend specimens while crack growth rates and threshold stress intensities for SCC (KISCC) were measured using fatigue precracked wedge open loaded (WOL) specimens. Both SCC tests were conducted in a 3.5% NaCl environment maintained at 90°C. XRD results revealed the presence of reverted austenite in the higher tempered specimens due to the precipitation hardening temperature being close to the Ac1 temperature for the material. The presence of reverted austenite was shown to adversely affect mechanical strength and hardness which decreased with increasing precipitation hardening temperature. Light and electron microscopy (SEM and TEM) revealed the presence of Cr-rich precipitates along the prior austenite grain boundaries in all tested heat treatment conditions. The propensity, quantity and size of the Cr-rich precipitates increased as the specimen temper temperature increased. SCC susceptibility was shown to be dependent upon yield strength and decreased as precipitation hardening temperature increased with specimens in the overaged condition showing no cracking after more than 5000 hours in the test environment. WOL testing only produced cracking in the three highest strength specimens after 2000 hours. Crack growth rates and threshold stress intensities were found to be dependent on yield strength and decreased with increasing precipitation hardening temperature. Analysis of fracture surfaces revealed crack propagation along prior austenite grain boundaries in all test heat treatment conditions indicating intergranular stress corrosion cracking (IGSCC) as the dominant cracking mechanism.
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Gompertz, Kyle Adler. "Separation Flow Control with Vortex Generator Jets Employed in an Aft-Loaded Low-Pressure Turbine Cascade with Simulated Upstream Wakes." The Ohio State University, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=osu1243990496.

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TERNER, MATHIEU. "Innovative materials for high temperature structural applications: 3rd Generation γ-TiAl fabricated by Electron Beam Melting." Doctoral thesis, Politecnico di Torino, 2014. http://hdl.handle.net/11583/2527509.

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In the aeronautics industry, the propulsion systems stand among the most advanced and critical components. Over the last 50 years, gas turbine aeroengines were subjected to intensive research to increase efficiency and reduce weight, noise and harmful emissions. Together with design optimization, breakthrough in materials science for structural applications triggered the development of the most advanced gas turbine engines. For low temperatures, basically ahead of the combustion section, lightweight Ti alloys are preferred for their good mechanical properties. For high temperatures instead, Ni-based superalloys exhibit outstanding properties up to very high temperatures despite a rather high material’s density. Research have focused on enhancing to the maximum the potential of materials in gas turbine engines. According to the application, the components experience various mechanical and environmental constraints. Special designs, manufacturing process, material compositions and protective coatings have been developed to push the limits of advanced materials. Nowadays, the attention is focused on innovative materials to replace the existing Ti and Ni based alloys leading to substantial benefits. Light weight composite materials in particular were found very attractive to replace some components’ Ti alloys. At higher temperatures, it is of great interest to replace Ni-based superalloys by materials with lower density and/or higher temperatures applications, which in turn would lead to substantial weight reduction and increase efficiency. At the highest temperatures range, in particular in the combustion chamber and high pressure turbine sections, ceramic based materials offer promising balance of properties. Research are dedicated to overcome the drawbacks of ceramics for such structural applications, and in particular their brittle fracture behavior, by addition of reinforcing fibers. At lower temperatures range, TiAl based intermetallics emerged as very promising materials at half the density of Ni-based superalloys. Significant weight reduction could be achieved by the introduction of TiAl based alloys for rotating components of the compressor and low pressure turbine. 2nd generation γ-TiAl alloys were lately introduced in GE’s GEnx and CFM’s LEAP engines. The present work concerns the fabrication by the additive manufacturing technique Electron Beam Melting of 3rd generation γ-TiAl alloys for high temperatures application in gas turbine aeroengines. EBM, building parts layer by layer according to CAD, offers many advantages compared to other manufacturing processes like casting and forging. Reported by Avio, 2nd generation γ-TiAl alloys have been successfully fabricated by EBM. To increase the material’s potential, the production of 3rd generation γ-TiAl alloys Ti-(45-46)Al-2Cr-8Nb was therefore studied. The optimization of the EBM parameters led to high homogeneity and very low post-processing residual porosity ≤ 1%. The fine equiaxed microstructure after EBM could be tailored towards the desired mechanical properties by simple heat treatment, from equiaxed to duplex to fully lamellar. In particular, a duplex microstructure composed by about 80 % lamellar grains pinned at grain boundaries by fine equiaxed grains was obtained after heat treatment slightly over the α transus temperature. The study showed that addition of a higher amount of Nb significantly increased the oxidation resistance of the material, thus increasing the application temperature range of these γ-TiAl alloys.
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Flage, Alexander Paul. "Computational Investigation of Low-Pressure Turbine Aerodynamics." Thesis, North Dakota State University, 2015. https://hdl.handle.net/10365/27915.

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The design of today?s gas turbine engines is heavily reliant on accurate computational fluid flow models. Creating prototype designs is far more expensive than modeling the design on a computer; however, current turbulence and transitional flow models are not always accurate. Several turbulence and transition models were validated at North Dakota State University by analyzing the flow through a low pressure turbine of a gas turbine engine. Experimental data for these low pressure turbines was provided by the University of North Dakota. Two separate airfoil geometries are analyzed in this study. The first geometry is a first stage flow vane, and the second geometry is an incidence angle tolerant turbine blade. Pressure and heat transfer data were compared between computations and experiments on the turbine blade surfaces. Simulations were conducted with varying Reynolds numbers, Mach numbers, and free stream turbulence intensities and were then compared with experiments.
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Ssebabi, Brian. "Experimental evaluation of a low temperature and low pressure turbine." Thesis, Stellenbosch : Stellenbosch University, 2014. http://hdl.handle.net/10019.1/86563.

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Thesis (MEng)--Stellenbosch University, 2014.
ENGLISH ABSTRACT: The potential benefits from saving energy have driven most industrial processing facilities to pay more attention to reducing energy wastage. Because the industrial sector is the largest user of electricity in South Africa (37.7% of the generated electricity capacity), the application of waste heat recovery and utilisation (WHR&U) systems in this sector could lead to significant energy savings, a reduction in production costs and an increase in the efficiency of industrial processes. Turbines are critical components of WHR&U systems, and the choice of an efficient and low cost turbine is crucial for their successful implementation. The aim of this thesis project is therefore to validate the use of a turbine for application in a low grade energy WHR&U system. An experimental turbine kit (Infinity Turbine ITmini) was acquired, assembled and tested in a specially designed and built air test bench. The test data was used to characterise the turbine for low temperature (less than 120 Celsius) and pressure (less than 10 bar) conditions. A radial inflow turbine rotor was designed, manufactured and then tested with the same test bench, and its performance characteristics determined. In comparison with the ITmini rotor, the as-designed and manufactured rotor achieved a marginally better performance for the same test pressure ratio range. The as-designed turbine rotor performance characteristics for air were then used to scale the turbine for a refrigerant-123 application. Future work should entail integrating the turbine with a WHR&U system, and experimentally determining the system’s performance characteristics.
AFRIKAANSE OPSOMMING: Die potensiële voordele wat gepaard gaan met energiebesparing het die fokus van industrie laat val op die bekamping van energievermorsing. Die industriële sektor is die grootse verbruiker van elektrisiteit in Suid-Afrika (37.7% van die totale gegenereerde kapasiteit). Energiebesparing in die sektor deur die toepassing van afval-energie-herwinning en benutting (AEH&B) sisteme kan lei tot drastiese vermindering van energievermorsing, ‘n afname in produksie koste en ‘n toename in die doeltreffendheid van industriële prosesse. Turbines is kritiese komponente in AEH&B sisteme en die keuse van ‘n doeltreffende lae koste turbine is noodsaaklik in die suksesvolle implementering van dié sisteme. Die doelwit van hierdie tesisprojek is dus om die toepassing van ‘n turbine in ‘n lae graad energie AEH&B sisteem op die proef te stel. ‘n Eksperimentele turbine stel (“Infinity Turbine ITmini”) is aangeskaf, aanmekaargesit en getoets op ‘n pasgemaakte lugtoetsbank. Die toetsdata is gebruik om die turbine te karakteriseer by lae temperatuur (minder as 120 Celsius) en druk (minder as 10 bar) kondisies. ‘n Radiaalinvloeiturbinerotor is ook ontwerp, vervaardig en getoets op die lugtoetsbank om die rotor se karakteristieke te bepaal. In vergelyking met die ITmini-rotor het die radiaalinvloeiturbinerotor effens beter werkverrigting gelewer by diselfde toetsdruk verhoudings. Die werksverrigtingkarakteristieke met lug as vloeimedium van die radiaalinvloeiturbinerotor is gebruik om die rotor te skaleer vir ‘n R123 verkoelmiddel toepassing. Toekomstige werk sluit in om die turbine met ‘n AEH&B sisteem te integreer en die sisteem se werksverrigtingkarakteristieke te bepaal.
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Books on the topic "Low pressure turbine material"

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Center, NASA Glenn Research, ed. Low-pressure turbine separation control: Comparison with experimental data. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

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Center, NASA Glenn Research, ed. Low-pressure turbine separation control: Comparison with experimental data. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2002.

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J, Dorney Daniel, and NASA Glenn Research Center, eds. Experimental and numerical investigation of losses in low-pressure turbine blade rows. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Center, Lewis Research, ed. Experimental study of boundary layer behavior in a simulated low pressure turbine. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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J, Dorney Daniel, and Lewis Research Center, eds. Study of boundary layer development in a two-stage low-pressure turbine. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1999.

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Center, Lewis Research, ed. Experimental study of boundary layer behavior in a simulated low pressure turbine. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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United States. National Aeronautics and Space Administration., ed. Reynolds-averaged Navier-Stokes studies of low Reynolds number effects on the losses in a low pressure turbine. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Book chapters on the topic "Low pressure turbine material"

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Denk, Josef. "Low Pressure Steam Turbine Integrity." In Materials for Advanced Power Engineering 1994, 157–70. Dordrecht: Springer Netherlands, 1994. http://dx.doi.org/10.1007/978-94-011-1048-8_9.

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Ko, Eui-Seok, Chi-Won Kim, Seong-Jun Park, and Hyun-Uk Hong. "Characterization of Low-Cycle Fatigue Deformation Behavior at RT/200 °C of FeMnAlC Lightweight Steel for Low-Pressure Turbine Blade." In The Minerals, Metals & Materials Series, 987–91. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-22524-6_91.

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Kim, Chul Su, Jung Kyu Kim, and Tae Seong Kim. "An Evaluation of Appropriate Probabilistic ­S-­N Curve for the Turbine Blade Steel in the Low Pressure Steam." In Key Engineering Materials, 1751–57. Stafa: Trans Tech Publications Ltd., 2005. http://dx.doi.org/10.4028/0-87849-978-4.1751.

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Zou, Zhengping, Songtao Wang, Huoxing Liu, and Weihao Zhang. "Flow Mechanisms in Low-Pressure Turbines." In Axial Turbine Aerodynamics for Aero-engines, 143–257. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-5750-2_4.

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Dischler, Bernhard. "CVD Diamond: A New and Promising Material." In Low-Pressure Synthetic Diamond, 3–7. Berlin, Heidelberg: Springer Berlin Heidelberg, 1998. http://dx.doi.org/10.1007/978-3-642-71992-9_1.

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Yan, L., S. Inagaki, and M. Arimura. "Corrosion Fatigue Evaluation on Low-pressure Steam Turbine." In Challenges of Power Engineering and Environment, 1019–24. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-76694-0_188.

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Gonzalo, Oscar, Jose Mari Seara, Eneko Olabarrieta, Mikel Esparta, Iker Zamakona, Manu Gomez-Korraletxe, and José Alberto de Dios. "Case Study 1.2: Turning of Low Pressure Turbine Casing." In Lecture Notes in Production Engineering, 25–38. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-45291-3_2.

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Sharma, Atul S., Nadir Abdessemed, Spencer Sherwin, and Vassilis Theofilis. "Optimal Growth of Linear Perturbations in Low Pressure Turbine Flows." In IUTAM Symposium on Flow Control and MEMS, 339–43. Dordrecht: Springer Netherlands, 2008. http://dx.doi.org/10.1007/978-1-4020-6858-4_39.

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Sayma, A. I., M. Vahdati, J. S. Green, and M. Imregun. "Whole-Assembly Flutter Analysis of a Low Pressure Turbine Blade." In Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 347–59. Dordrecht: Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_23.

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Raverdy, B., I. Mary, P. Sagaut, and J. M. Roux. "LES of Wake-Blade Interference in a Low-Pressure Turbine." In Direct and Large-Eddy Simulation V, 627–34. Dordrecht: Springer Netherlands, 2004. http://dx.doi.org/10.1007/978-1-4020-2313-2_66.

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Conference papers on the topic "Low pressure turbine material"

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Jennions, Ian K., Thomas Sommer, Bernhard Weigand, and Manfred Aigner. "The GT24/26 Low Pressure Turbine." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-029.

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The GT24 and GT26 are the latest in a series of gas turbines from ABB. The GT24 is a 60 Hz, 183 MW turbine, while the GT26 is its (scaled) 50 Hz equivalent, producing 265 MW. They feature a 22 stage controlled diffusion aerofoil compressor, two combustors separated by a single stage high pressure turbine with a four stage low pressure (LP) turbine following the second combustor. This arrangement permits very high efficiencies while avoiding high temperatures and the need to use new, expensive materials. The first GT24 was delivered to Jersey Central Power and Light, Gilbert, New Jersey, USA, at the end of 1995 and achieved baseload operation in May 1996. The engine was highly instrumented with some 1200 measurement points to evaluate component performance. Subsequently, a through-flow datamatch to the design point data was made for the LP turbine and is compared to a full 3D multistage analysis in this paper. The 3D analysis accounts for all the cooling and leakage flows that enter the turbine flowpath and maintains a steady flow calculation by means of interface planes between each blade row that remove any circumferential non-uniformity from the computational flow field. To complement this aerodynamic analysis, some heat transfer results from the ABB GT26 test facility in Birr, Switzerland are also shown. The paper demonstrates how component technology for the first stage was verified at four universities and research centers concurrently with the design process. This experimental data supplemented the existing databases and engendered confidence in the overall aero/thermal design approach.
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Mehta, Jayesh M., and James Askew. "Future Material Needs for Low Emissions Gas Turbines." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-262.

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The modern low emissions gas turbines operate under some of the most challenging operating conditions as more demands are exercised on their performance. For example, the future engines will have higher thrust-to-weight ratio, improved fuel efficiencies, and high overall pressure ratios. Furthermore, the environmental safety needs will dictate many of the future low emissions combustor designs to be either Lean-Premixed (LP), Lean Direct Injection (LDi), Rich-burn-Quick quench-Lean burn (RQL) or catalytic. These will impose additional demands on developing unique high temperature materials that can survive in oxidizing and reducing environments, under high temperature and pressure conditions, and have other material properties such as superior strength and stiffness. In this paper, first we discuss the salient features of advanced low-emissions gas turbines and their needs for unique material technology development. Next, we discuss the state-of-the-art material technology development as it is applied to current gas turbines. And, finally we review the material developments that will be needed for the future gas turbine engines.
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CONLON, SUSAN. "Structural analysis and investigation of gas turbine low pressure turbine vane cluster." In 32nd Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1195.

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Schuerhoff, Joerg, Andrei Ghicov, and Karsten Sattler. "Advanced Water Droplet Erosion Protection for Modern Low Pressure Steam Turbine Steel Blades." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43140.

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Blades for low pressure steam turbines operate in flows of saturated steam containing water droplets. The water droplets can impact rotating last stage blades mainly on the leading edge suction sides with relative velocities up to several hundred meters per second. Especially on large blades the high impact energy of the droplets can lead to a material loss particularly at the inlet edges close to the blade tips. This effect is well known as “water droplet erosion”. The steam turbine manufacturer use several techniques, like welding or brazing of inlays made of erosion resistant materials to reduce the material loss. Selective, local hardening of the blade leading edges is the preferred solution for new apparatus Siemens steam turbines. A high protection effect combined with high process stability can be ensured with this Siemens hardening technique. Furthermore the heat input and therewith the geometrical change potential is relatively low. The process is flexible and can be adapted to different blade sizes and the required size of the hardened zones. Siemens collected many years of positive operational experience with this protection measure. State of the art turbine blades often have to be developed with precipitation hardening steels and/or a shroud design to fulfill the high operational requirements. A controlled hardening of the inlet edges of such steam turbine blades is difficult if not impossible with conventional methods like flame hardening. The Siemens steam turbine factory in Muelheim, Germany installed a fully automated laser treatment facility equipped with two co-operating robots and two 6 kW high power diode laser to enable the in-house hardening of such blades. Several blade designs from power generation and industrial turbines were successfully laser treated within the first year in operation. This paper describes generally the setup of the laser treatment facility and the application for low pressure steam turbine blades made of precipitation hardening steels and blades with shroud design, including the post laser heat treatments.
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Fondelli, Tommaso, Tommaso Diurno, Lorenzo Palanti, Antonio Andreini, Bruno Facchini, Leonardo Nettis, Lorenzo Arcangeli, and Nicola Maceli. "Investigation on low-pressure steam turbine exhaust hood modelling through computational fluid dynamic simulations." In SECOND INTERNATIONAL CONFERENCE ON MATERIAL SCIENCE, SMART STRUCTURES AND APPLICATIONS: ICMSS-2019. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5138809.

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Lottini, Fabrizio, Francesco Poli, Lorenzo Pinelli, Federico Vanti, and Roberto Pacciani. "Flutter stability assessment of a low pressure turbine rotor: A comparison between cantilever and interlocked configurations." In SECOND INTERNATIONAL CONFERENCE ON MATERIAL SCIENCE, SMART STRUCTURES AND APPLICATIONS: ICMSS-2019. AIP Publishing, 2019. http://dx.doi.org/10.1063/1.5138835.

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Wang, K. D., and R. S. Amano. "Turbulent Instability Prediction in Low-Pressure Last Stage Steam Turbine Blades." In ASME 1998 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/imece1998-0587.

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Abstract The last stage blades of a low-pressure (LP) steam turbine were reported to have been experiencing flow instability associated with higher than normal back pressure level. The phenomenon is identified as one of the serious potential causes of last stage blade failures and, therefore, can be one of the major factors that limit the operational flexibility of steam turbines. Thus, for failure prevention, it becomes necessary to determine the operating conditions under which turbulent instability is likely to occur. This paper presents a novel approach that can quantitatively predict turbulent flow instability by comparing aerodynamic damping and structural damping. To assess its applicability, turbulent flow instability was investigated in conjunction with three fundamental vibration modes of last stage blades of a LP steam turbine. The stability considerations were based on a quasi-steady power-per-vibration-cycle approach. The aerodynamic work per cycle of vibration mode of a bladed disk was calculated from the time integral of the product of the periodic time varying force and the specified harmonic vibration amplitude. A finite element based blade model was constructed to obtain modal characteristics at an operating speed. The aerodynamic forces were obtained from a two-dimensional cascade analysis for viscous compressible flow with a second-order Reynolds-stress model. The computational nodes were generated by employing a body-fitted algebraic grid generation technique. The unsteady compressible Navier-Stokes equations were solved for the flows around the blade airfoil region to determine aerodynamic damping. The nonlinear material damping energy of the bladed disk was calculated as a function of the vibration amplitude by using the Lazan’s power law. The turbulent instability was determined by the net power flow to die bladed disk at various amplitudes of vibration. Some computed results for die last stage of a LP steam turbine are presented in this paper.
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Waite, Joshua J., Robert E. Kielb, and Simon L. Bittner. "The Influence of Steady Loading Parameters on Low-Pressure Turbine Flutter." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1417.

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Ogata, Takashi. "Void Growth Simulation of a Steam Turbine Casing Material Under Creep and Creep-Fatigue Loading." In ASME 2007 Pressure Vessels and Piping Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/creep2007-26304.

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High temperature components in thermal power plants are subjected to creep and creep-fatigue loading where creep voids initiate and grow on grain boundaries. Development of a quantitative evaluation method of the void growth is important for reliable maintenance of these components. In this study, creep and creep-fatigue tests were carried out at 600 °C on a 1Cr-Mo-V casting steel. Creep damaged materials were produced by interrupting the creep tests and microstructure of the damaged materials were observed carefully by a scanning microscope. The creep-fatigue tests were also conducted in a scanning electron microscope, and continuous observation of void growth behavior during the tests was made. From the observations, spherical shape voids initiate and grow up to their length of 2μm on grain boundaries at initial stage of damage, and then these voids change their shape to crack-like to grow until their length reaches around 10μm under both the creep and the creep-fatigue conditions. Under the same stress level, the void growth rate in the creep-fatigue condition was faster than that in the creep condition indicating acceleration of void growth rate by cyclic loading. Previously proposed void growth simulation model, in which the void growth was controlled by diffusion and power law creep, was modified to express acceleration of the void growth by the cyclic loading. Void growth behavior within a certain area under both the creep and the creep-fatigue condition were simulated by the modified program. Predicted void growth behaviors agreed with observed ones. The void growth behavior of an actual turbine casing was also simulated and void growth behavior was discussed based on the result.
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Burton, Scott, Chander Prakash, and Joseph Machnaim. "Multistage Low Pressure Turbine Airfoil Shape Optimization Using the C3 Process." In 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1914.

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Reports on the topic "Low pressure turbine material"

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Tampe, L. A., R. G. Frenkel, D. J. Kowalick, H. M. Nahatis, S. M. Silverstein, and D. G. Wilson. Low-pressure-ratio regenerative exhaust-heated gas turbine. Office of Scientific and Technical Information (OSTI), January 1991. http://dx.doi.org/10.2172/5086383.

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Theofilis, Vassilios, Nadir Abdessemed, and Spencer J. Sherwin. Global Instability and Control of Low-Pressure Turbine Flows. Fort Belvoir, VA: Defense Technical Information Center, March 2006. http://dx.doi.org/10.21236/ada450947.

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EMC ENGINEERS INC DENVER CO. Limited Energy Study, Low Pressure Turbine Fort Wainwright, Alaska. Fort Belvoir, VA: Defense Technical Information Center, February 1995. http://dx.doi.org/10.21236/ada330244.

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Tampe, L. A., R. G. Frenkel, D. J. Kowalick, H. M. Nahatis, S. M. Silverstein, and D. G. Wilson. Low-pressure-ratio regenerative exhaust-heated gas turbine. Final report. Office of Scientific and Technical Information (OSTI), January 1991. http://dx.doi.org/10.2172/10153458.

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Fasel, Hermann F., Andreas Gross, and Wolfgang Balzer. Numerical Investigations of Active Flow Control for Low-Pressure Turbine Blades. Fort Belvoir, VA: Defense Technical Information Center, March 2008. http://dx.doi.org/10.21236/ada480712.

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Bons, Jeffrey P. Visualization of Flow Control Devices (VGJs) for Low Pressure Turbine Separation Control Using Stero PIV. Fort Belvoir, VA: Defense Technical Information Center, August 2004. http://dx.doi.org/10.21236/ada426129.

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Claus, Ana, Borzooye Jafarizadeh, Azmal Huda Chowdhury, Neziah Pala, and Chunlei Wang. Testbed for Pressure Sensors. Florida International University, October 2021. http://dx.doi.org/10.25148/mmeurs.009771.

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Currently, several studies and experiments are being done to create a new generation of ultra-low-power wearable sensors. For instance, our group is currently working towards the development of a high-performance flexible pressure sensor. However, with the creation of new sensors, a need for a standard test method is necessary. Therefore, we opted to create a standardized testbed to evaluate the pressure applied to sensors. A pulse wave is generated when the heart pumps blood causing a change in the volume of the blood vessel. In order to eliminate the need of human subjects when testing pressure sensors, we utilized polymeric material, which mimics human flesh. The goal is to simulate human pulse by pumping air into a polymeric pocket which s deformed. The project is realized by stepper motor and controlled with an Arduino board. Furthermore, this device has the ability to simulate pulse wave form with different frequencies. This in turn allows us to simulate conditions such as bradycardia, tachycardia, systolic pressure, and diastolic pressure.
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Thembeka Ncube, Ayanda, and Antonio Bobet. Use of Recycled Asphalt. Purdue University, 2021. http://dx.doi.org/10.5703/1288284317316.

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The term Reclaimed Asphalt Pavement (RAP) is used to designate a material obtained from the removal of pavement materials. RAP is used across the US in multiple applications, largely on asphalt pavement layers. RAP can be described as a uniform granular non-plastic material, with a very low percentage of fines. It is formed by aggregate coated with a thin layer of asphalt. It is often used mixed with other granular materials. The addition of RAP to aggregates decreases the maximum dry unit weight of the mixture and decreases the optimum water content. It also increases the Resilient Modulus of the blend but decreases permeability. RAP can be used safely, as it does not pose any environmental concerns. The most important disadvantage of RAP is that it displays significant creep. It seems that this is caused by the presence of the asphaltic layer coating the aggregate. Creep increases with pressure and with temperature and decreases with the degree of compaction. Creep can be mitigated by either blending RAP with aggregate or by stabilization with chemical compounds. Fly ash and cement have shown to decrease, albeit not eliminate, the amount of creep. Mechanical stabilizing agents such as geotextiles may also be used.
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Padget, C. D. W., D. R. M. Pattison, D. P. Moynihan, and O. Beyssac. Pyrite and pyrrhotite in a prograde metamorphic sequence, Hyland River region, SE Yukon: implications for orogenic gold. Natural Resources Canada/CMSS/Information Management, 2021. http://dx.doi.org/10.4095/328987.

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The distribution of pyrite and pyrrhotite is documented within an andalusite-sillimanite type (high-temperature, low-pressure) metasedimentary succession exposed in the Hyland River region of southeastern Yukon, Canada. The following metamorphic zones are recognized: chlorite, biotite, cordierite/staurolite (porphyroblast-in), andalusite, sillimanite, and K-feldspar + sillimanite. Pyrite occurs in the chlorite zone through the biotite zone, while pyrrhotite occurs from the chlorite zone to K-feldspar + sillimanite zone. The pyrite-pyrrhotite transition, therefore, occupies an interval in the chlorite and lower biotite zones that is terminated upgrade by a pyrite-out isograd in the upper part of the biotite zone or lowest grade part of the cordierite/staurolite zone. Pressure and temperature conditions of the rocks were estimated from phase equilibrium modelling and from Raman spectroscopy of carbonaceous material (RSCM) thermometry. Modelling indicates pressures of 3.7-4.1 kbar with temperatures of ~425 °C at the biotite isograd, 560-570 °C for chlorite-out/porphyroblast-in, ~575 °C for andalusite-in, 575-600 °C for the sillimanite isograd, and 645-660 °C at the K-feldspar + sillimanite isograd. RSCM temperatures are greater than or equal to 420 °C in the Chl zone, 500 °C at the Bt isograd, 525-550 °C for porphyroblast-in isograd, ~550 °C at the And isograd, and 580 °C at the Sil isograd. These results suggest the pyrite-pyrrhotite transition occurs from less than or equal to 420°C to ~560 °C. Thermodynamic modelling shows 0.6 wt. % H2O is released during metamorphism over the ~140 °C interval of the pyrite-pyrrhotite transition. The gradual release of fluid in the biotite zone is interpreted to have broadened the pyrite-pyrrhotite transition compared to other studies that predict a small interval of vigorous fluid release associated with volumetric chlorite consumption. Samples from the pyrite-pyrrhotite transition zone contain lower whole rock and pyrite Au values than samples from unmetamorphosed/lower rocks, suggesting that Au was removed from the rock at conditions below the pyrite-pyrrhotite transition (<420 °C). The chlorite zone and higher-grade metamorphic rocks of the Hyland River area do not appear to be a plausible source region for orogenic gold.
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Johra, Hicham. Performance overview of caloric heat pumps: magnetocaloric, elastocaloric, electrocaloric and barocaloric systems. Department of the Built Environment, Aalborg University, January 2022. http://dx.doi.org/10.54337/aau467469997.

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Heat pumps are an excellent solution to supply heating and cooling for indoor space conditioning and domestic hot water production. Conventional heat pumps are typically electrically driven and operate with a vapour-compression thermodynamic cycle of refrigerant fluid to transfer heat from a cold source to a warmer sink. This mature technology is cost-effective and achieves appreciable coefficients of performance (COP). The heat pump market demand is driven up by the urge to improve the energy efficiency of building heating systems coupled with the increase of global cooling needs for air-conditioning. Unfortunately, the refrigerants used in current conventional heat pumps can have a large greenhouse or ozone-depletion effect. Alternative gaseous refrigerants have been identified but they present some issues regarding toxicity, flammability, explosivity, low energy efficiency or high cost. However, several non-vapour-compression heat pump technologies have been invented and could be promising alternatives to conventional systems, with potential for higher COP and without the aforementioned refrigerant drawbacks. Among those, the systems based on the so-called “caloric effects” of solid-state refrigerants are gaining large attention. These caloric effects are characterized by a phase transition varying entropy in the material, resulting in a large adiabatic temperature change. This phase transition is induced by a variation of a specific external field applied to the solid refrigerant. Therefore, the magnetocaloric, elastocaloric, electrocaloric and barocaloric effects are adiabatic temperature changes in specific materials when varying the magnetic field, uniaxial mechanical stress, electrical field or hydrostatic pressure, respectively. Heat pump cycle can be built from these caloric effects and several heating/cooling prototypes were developed and tested over the last few decades. Although not a mature technology yet, some of these caloric systems are well suited to become new efficient and sustainable solutions for indoor space conditioning and domestic hot water production. This technical report (and the paper to which this report is supplementary materials) aims to raise awareness in the building community about these innovative caloric systems. It sheds some light on the recent progress in that field and compares the performance of caloric systems with that of conventional vapour-compression heat pumps for building applications.
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