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1
Yu, Maoyu, Jianfang Wang, Haijun Xuan, Wangjiao Xiong, Zekan He, and Mingmin Qu. "Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test." Aerospace 11, no. 8 (2024): 629. http://dx.doi.org/10.3390/aerospace11080629.
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This paper addresses the critical issue of turbine blade containment in aircraft engines, crucial for ensuring flight safety. Through a comprehensive approach integrating numerical simulations and experimental validations, the containment capabilities of gas turbine engine casings are thoroughly analyzed. The study investigates the impact dynamics, deformation characteristics, and energy absorption mechanisms during blade detachment events, shedding light on the containment process. Based on the multi-stage nature of gas turbines, two different blade structures were designed for turbine blades. Utilizing finite element simulation and the Johnson–Cook constitutive equation, this study accurately simulated single-blade and dual-blade containment scenarios. The simulation results of the single blade indicate that the process of a gas turbine blade impacting the casing primarily consists of three stages. The second stage, where the tenon root strikes the casing, is identified as the main cause of casing damage. Meanwhile, in the dual-blade simulation, the second blade, influenced by the first blade, directly impacts the casing after fracturing, resulting in greater damage. Then, eight corresponding containment tests were conducted based on the simulation results, validating the accuracy of the simulation parameters. Experimental verification of simulation results further confirms the validity of the proposed containment curves, providing essential insights for optimizing casing design and enhancing the safety and reliability of aircraft engines.
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Lazarevikj, M., and Z. Markov. "Automated hydraulic design procedure for a Francis turbine spiral casing." IOP Conference Series: Earth and Environmental Science 1079, no. 1 (2022): 012009. http://dx.doi.org/10.1088/1755-1315/1079/1/012009.
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Abstract The spiral casing of a Francis turbine distributes the water from the penstock to the stay and guide vanes circumferentially and uniformly, which is important for achieving the required flow conditions at the runner entrance. Moreover, the spiral casing is supposed to provide the required inlet velocity in front of the stay vanes and create minimal hydraulic losses. The dimensions and shape of the spiral casing depend on the hydraulic and energy parameters of the turbine. A calculation methodology for a Francis spiral casing hydraulic design is presented in this paper. The methodology developed is based on the main condition to achieve a uniform water flow rate into the stay vanes system and the wicket gate over the entire perimeter. The free vortex flow theory is implemented in this research, where the design is based on the law of constant velocity moment. The parametric definition of the spiral casing makes the geometries generated for certain input combinations suitable for numerical analysis using commercially available Computational Fluid Dynamics (CFD) software. The calculation procedure can be used for any set of energy and geometry turbine parameters, such as water discharge, angle of streamline departing from the spiral casing, and stay ring diameter and height. The automated approach integrating MATLAB and ANSYS Workbench capabilities is presented as a spiral casing design tool. The product is a design solution proposed on basis of the turbine parameters. The spiral casing geometry generation is followed by a CFD analysis. Considering input parameters of different existing Francis turbines, the spiral casing is redesigned accordingly. One of the obtained spiral casings geometry is numerically tested. The results show that the uniform discharge distribution is achieved. The automation of the design procedure allows further optimization based on chosen input parameters.
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K, Arunesh Muthiah. "Comparative Study of Gravitational Water Vortex Turbine(GWVT) with Fibonaccian and Conical Casing." International Journal for Research in Applied Science and Engineering Technology 13, no. 6 (2025): 1704–11. https://doi.org/10.22214/ijraset.2025.72492.
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A gravitational vortex turbine is an eco-friendly micro hydropower generation turbine that operates in ultra-low heads to provide energy in rural areas. Nowadays, the challenging aspects of conical casing vortex turbines are low efficiency and poor vortex dynamics. This paper focuses on a conceptual idea study that serves as a comparison of the results of a self-developed golden ratio spiral-based casing for an ultra-low head vortex turbine to a conical gravitational turbine using SolidWorks flow simulation. A six-blade rear turbine is used for the overall simulation. The turbine is placed at the outlet of the casing, and the values of force acting on the turbine blades are simulated. The torque at the turbine blade is also determined for the generic conical casing and the Fibonaccian casing, which are compared for the results. The relative pressure contour acting on the blades of the turbine is represented in a pictorial form. The torque is compared at each axis and plotted in a graphical format. The results encourage further development of GWVT, as there is an increase in the overall torque and efficiency.
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Komarudin, Udin, Iftika Philo, Nia Nuraeni, and Nissa Syifa Puspani. "Pipe Stress and Turbine Nozzle Load Analysis for HP Steam Inlet and MP Steam Extraction on Turbine Generator 51G201T Capacity 10MW." International Journal of Engineering & Technology 7, no. 4.33 (2018): 214. http://dx.doi.org/10.14419/ijet.v7i4.33.23562.
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Thermal pipe expansion on the turbine greatly affects the performance of the turbine, mainly produces misalignment in turbines. The stress analysis on the pipe and the load on the nozzle is very important to ensure that the stress that occurs is still safe and the load that occurs on the nozzle is still below the allowable load. Field information is known, Steam type of 51-G-201-T, capacity 10 MW, total weighs 58 tons, weight casing 37 tons, which has been operating since July 1989, has been occur misalignment on turbines. Stress pipe and load analysis of turbine nozzles on the turbine using software (Autopipe V8i Select Series 3 Edition by Bentley). In this perspective, calculation methodologies were developed in order to do quick analysis of the most common configurations, according to the codes ASME B31.1 (Piping Power). The results of the pipe stress analysis showed that the maximum sustained stress ratio occurred at point A39 (0.32), maximum displacement stress ratio at point A39 (0.97) and maximum hoop stress ratio at point A09 (0.44), all values below 1. This shows that the stress is still safe. The result of load analysis on the turbine casing is the direction x = -880 kg, y = 6246.4kg, z = -3697.7kg, smaller than the weight of the 37 tones turbine casing, so misalignment is not caused by shifting the turbine casing.
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Zhong, Wenyuan, Jiaqi Li, Zhongyu Yang, Yinli Feng, and Tao Sun. "A Numerical Study of Complex Impact Loads on Thin-Walled Casing of Aeroengine Considering Turbine Guide Vane Structure1." Journal of Physics: Conference Series 2557, no. 1 (2023): 012025. http://dx.doi.org/10.1088/1742-6596/2557/1/012025.
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Abstract As the main load-bearing component of the aero-engine system, the thin-walled casings have the characteristics of large size, complex structure, thin wall, and large area. In addition to the harsh working environment, it is necessary to study applicable preventive measures to contain high-energy fragments to ensure flight safety. The complex load formed by the axial impact and circumferential torsion exerted by the turbine rotor on the exhaust casing is studied, and the model includes the turbine rotor. By analyzing the deformation and energy dissipation of the exhaust casing in the calculation results, the dynamic response of the power turbine and the exhaust casing in the complex impact load is obtained, and it is verified that the initial speed of the power turbine has no obvious relationship with the dynamic response and energy dissipation of the exhaust casing. At the same time, it is concluded that the axial velocity and aerodynamic force of the power turbine have a strong positive correlation with the complex impact load and dynamic response of the exhaust casing. In the follow-up studies and equivalent experiments, these conclusions can be used as a reference for further experimental design.
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Marzec, Krzysztof. "Low-Pressure Turbine Cooling Systems." Encyclopedia 1, no. 3 (2021): 893–904. http://dx.doi.org/10.3390/encyclopedia1030068.
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Modern low-pressure turbine engines are equipped with casings impingement cooling systems. Those systems (called Active Clearance Control) are composed of an array of air nozzles, which are directed to strike turbine casing to absorb generated heat. As a result, the casing starts to shrink, reducing the radial gap between the sealing and rotating tip of the blade. Cooling air is delivered to the nozzles through distribution channels and collector boxes, which are connected to the main air supply duct. The application of low-pressure turbine cooling systems increases its efficiency and reduces engine fuel consumption.
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Bakic, Gordana, Vera Sijacki-Zeravcic, Milos Djukic, Bratislav Rajicic, and Marko Tasic. "Remaining life assessment of a high pressure turbine casing in creep and low cycle service regime." Thermal Science 18, suppl.1 (2014): 127–38. http://dx.doi.org/10.2298/tsci121219179b.
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Thick walled components such as high pressure (HP) steam turbine casings operating under high parameter conditions are subjected to a complex stress state. As a result of that stress state, some parts of HP turbine casing undergo to the creep fatigue caused by the combination of thermal fatigue resulted from repeated start/stop operation and the creep which occurs during long-term operation at high temperature and high-pressure. It is well known that domestic thermal power plants have been in use over 100000 h which means that significant cost is required not only for maintenance, but often for renewal of equipment. Based on comprehensive investigation, the results of residual life assessment of one high pressure steam turbine casing, which belongs to the older turbine generation, taking into account simultaneous action of thermal fatigue and creep, are presented in this paper. Also, the critical flaw crack size of HP turbine casing is determined because this parameter has a strong influence on casing integrity and residual life. The results of residual life assessment provide not only a basis for further maintenance, but also estimated time for reparation or renewal.
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Matthias, Heinz-Bernd, Josef Prost, and Christian Rossegger. "Investigation of the Flow in Pelton Turbines and the Influence of the Casing." International Journal of Rotating Machinery 3, no. 4 (1997): 239–47. http://dx.doi.org/10.1155/s1023621x97000225.
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At the institute for waterpower and pumps at the University of Technology Vienna we do a lot of research work observing the flow in the casing and the buckets of Pelton turbines. One interest of our research is to find criteria to estimate the influence of the splash water distribution in the casing on the turbine efficiency. Knowing the splash water distribution it is further possible to develop methods to provide visual documentation of the flow in and around the buckets from the beginning to the end of interaction.Our measurements have been done on a single jet Pelton turbine with a runner pitch diameter of 420 mm. Our research shows that the casing has great influence to the operation of a Pelton turbine and so it is very important to include the casing as an important factor in all investigations. Aluminum honeycombs have been successful to bring the splashing water under control and to make good visual documentations of the flow.
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Tanino, Tadakazu, Ryo Yoshihara, and Takeshi Miyaguni. "A Study on a Casing Consisting of Three Flow Deflectors for Performance Improvement of Cross-Flow Wind Turbine." Energies 15, no. 16 (2022): 6093. http://dx.doi.org/10.3390/en15166093.
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We investigated the effective use of cross-flow wind turbines for small-scale wind power generation to increase the output power by using a casing, which is a kind of wind-collecting device, composed of three flow deflector plates having the shape of a circular-arc airfoil. Drag-type vertical-axis wind turbines have an undesirable part of about half of the swept area where the inflow of wind results in low output performance. To solve this problem, we devised a casing consisting of three flow deflector plates, two of which were to block the unwanted inflow of wind and the remaining flow deflector plate having an angle of attack with respect to the wind direction to increase the flow toward the rotor. In this study, output performance experiments using a wind tunnel and numerical fluid analysis were conducted on a cross-flow wind turbine with three flow deflector plates to evaluate the effectiveness of the casing on output performance improvement. As a result, it was confirmed that the casing could improve the output performance of the cross-flow wind turbine by approximately 60% at the maximum performance point and could also maintain the output performance about 50% higher compared to the bare cross-flow wind turbine without the casing within a deviation angle of ±10 degrees, even when the casing direction was inclined against the wind direction due to changes in wind direction.
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Salem, Hayder, Adel Mohammedredha, and Abdullah Alawadhi. "High Power Output Augmented Vertical Axis Wind Turbine." Fluids 8, no. 2 (2023): 70. http://dx.doi.org/10.3390/fluids8020070.
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Nowadays, wind energy is one of the most cost-effective and environmentally friendly energies in high demand due to shortages in fossil fuels and the necessity to reduce global carbon footprint. One of the main goals of wind turbine development is to increase the power output of the turbine either by increasing the turbine blade swept area or increasing the velocity of the wind. In this article, a proprietary augmentation system was introduced to increase the power output of vertical axis wind turbines (VAWT) by increasing the free stream velocity to more than two folds. The system comprises two identical airfoiled casings within which the turbine/turbines are seated. The results showed that the velocity slightly increases when decreasing the gap between the casing. It was also found that changing the angle of attack of the housing has more impact on the augmented airspeed. CFD technique was used to assess the velocity and flow of air around the system.
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M, Muas, Baso Nasrullah, Herdiman Herdiman, and Ahsan Muslimin. "Rancang Bangun Fixture Perakitan Runner dan Casing Turbin Cross Flow." Jurnal Sinergi Jurusan Teknik Mesin 17, no. 1 (2019): 70. http://dx.doi.org/10.31963/sinergi.v17i1.1595.
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One of the important turbine components to consider in its manufacture is the runner and turbine casing components. The large number of parts that must be welded and the use of tools that do not meet functional requirements causes some problems during the assembly process, the problem is due to the difficulty of obtaining straightness between the disc and runner shaft where both components occur run-out deviations that exceed the allowable tolerance, as well as casing component assembly where almost all of the joints undergo a simple welding process and use of aids causing a very large dimension deviation from the specified tolerance. The use of very simple tools will cause difficulties in controlling the dimensions or uniformity of the shape during the production process. For this reason, a fixture that is suitable for the runner and turbine casing is needed to get the assembly process that matches the specified geometry tolerance. This research makes the fixture design to be used in runner assembly and turbine casing assembly with the assembly method is carried out in stages. The design is done in five stages, namely the stage of problem statement, the stage of making needs analysis, the stage of gathering information and ideas, the stage of making temporary designs and the stage of making the final draft. Fixture manufacturing is done in two stages, namely ordering materials (purchasing materials) and making fixture components. The final result of making runners and casings using a fixture is able to reduce the aberration in the runner and turbine casing components by producing run-outs at runners of 2.0 mm and the straightness of the casing straightness of 1.6 mm, but have not been able to achieve deviations from the targeted one mm.
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Lian, Wenlei, Yunfei Jiang, Hao Chen, Yi Li, and Xianglei Liu. "Heat Transfer Characteristics of an Aeroengine Turbine Casing Based on CFD and the Surrogate Model." Energies 15, no. 18 (2022): 6743. http://dx.doi.org/10.3390/en15186743.
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A good turbine casing cooling design should control the thermal stress and maintain a reasonable tip clearance between the turbine blade and the casing. Since the turbine inlet temperature has been increased yearly, the influence of thermal radiation on the temperature of a turbine casing has become more significant. Therefore, the heat transfer characteristics of a turbine casing considering the radiation effect need to be precisely predicted. In this study, a theoretical model is established for describing the heat transfer characteristics of a turbofan casing, and the model’s effectiveness is verified by comparing the numerical and experimental results. Based on the validated model, the effects of single changes of the wall temperature, cooling air temperature, Reynolds number, and surface emissivity on the heat transfer of the casing are discussed. The results show that the increment of cooling air temperature and surface emissivity leads to the enhancement of the average radiative Nusselt number, and the average convective Nusselt number increases as the Reynolds number increases. The emissivity can improve the temperature distribution uniformity of the turbine casing. Finally, a Kriging surrogate model is fitted with 20 sample points to predict the joint effect of multiple parameters on the casing surface Nusselt number. It is found that the Reynolds number has a more significant influence on the average Nusselt number compared with the emissivity and the temperature ratio.
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Dambach, R., H. P. Hodson, and I. Huntsman. "1998 Turbomachinery Committee Best Paper Award: An Experimental Study of Tip Clearance Flow in a Radial Inflow Turbine." Journal of Turbomachinery 121, no. 4 (1999): 644–50. http://dx.doi.org/10.1115/1.2836716.
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This paper describes an experimental investigation of tip clearance flow in a radial inflow turbine. Flow visualization and static pressure measurements were performed. These were combined with hot-wire traverses into the tip gap. The experimental data indicate that the tip clearance flow in a radial turbine can be divided into three regions. The first region is located at the rotor inlet, where the influence of relative casing motion dominates the flow over the tip. The second region is located toward midchord, where the effect of relative casing motion is weakened. Finally, a third region exists in the exducer, where the effect of relative casing motion becomes small and the leakage flow resembles the tip flow behavior in an axial turbine. Integration of the velocity profiles showed that there is little tip leakage in the first part of the rotor because of the effect of scraping. It was found that the bulk of tip leakage flow in a radial turbine passes through the exducer. The mass flow rate, measured at four chordwise positions, was compared with a standard axial turbine tip leakage model. The result revealed the need for a model suited to radial turbines. The hot-wire measurements also indicated a higher tip gap loss in the exducer of the radial turbine. This explains why the stage efficiency of a radial inflow turbine is more affected by increasing the radial clearance than by increasing the axial clearance.
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Abbasi, Sarallah, and Afshin Gholamalipour. "Parametric study of injection from the casing in an axial turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 5 (2019): 582–93. http://dx.doi.org/10.1177/0957650919877276.
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Tip leakage flow reduces both efficiency and performance of axial turbines and damages turbine blades as well. Therefore, it is of great importance to identify and control tip leakage flow. This study investigated the effect of flow injection (from the casing), alongside flow structure, on turbine performance. Additionally, the effect of different injection parameters, including injection mass flow rate, angle, location, and diameter on the turbine performance are evaluated. A numerical analysis of the flow in a two-stage axial turbine was employed by using CFX software. To ensure the accuracy of the results, turbine performance curves were compared with the experimental results, which are in good agreement. Analyses revealed that active control method reduces tip leakage flow, improves turbine performance, and increases the efficiency by 1% to 5% as well. A parametric investigation of the tip injection has sought to identify how various parameters affect the turbine performance. The cross-section diameter and the angle of injection had no significant increase on efficiency. Additionally, results showed that at a point 9 mm further from the leading edge, the injection degree of effectiveness is optimum. Finally, analysis of the flow structure in the tip clearance region supported the tip leakage flow reduction.
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Gordon, J. L. "Hydraulic turbine efficiency." Canadian Journal of Civil Engineering 28, no. 2 (2001): 238–53. http://dx.doi.org/10.1139/l00-102.
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A set of empirical equations has been developed which defines the peak efficiency and shape of the efficiency curve for hydraulic turbines as a function of the commissioning date for the unit, rated head, rated flow, runner speed, and runner throat or impulse turbine jet diameter. The equations are based on an analysis of peak efficiency data from 56 Francis, 33 axial-flow, and eight impulse runners dating from 1908 to the present, with runner diameters ranging from just under 0.6 m to almost 9.5 m. The metric specific speeds (nq) ranged from 5.3 to 294. The root mean square error of the calculated peak efficiency for Francis and axial-flow runners was found to be 0.65%. The shape of the efficiency curves was derived from eight Francis, five Kaplan, three propeller, and four impulse turbines. Charts showing the relationship between calculated and actual efficiency curves for these 20 runners are provided. A good match between calculated and measured or guaranteed efficiency was obtained. The equations were also used to determine the relative increase in peak efficiency for new reaction runners installed in existing casings at 22 powerplants, with a root mean square accuracy of 1.0%. The equations can be used to (i) develop efficiency curves for new and old runners; (ii) compare the energy output of alternative types of turbines, where this choice is available; and (iii) calculate the approximate incremental energy benefit from installing a new runner in an existing reaction turbine casing, or onto the shaft of an impulse unit.Key words: hydraulic turbines, turbine renovation, turbine efficiency.
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Tang, Jin, Yong Zhang, Ge Wang, and Weidong Ma. "Outer casing structure design for the trisection turbine wheel burst of the air turbine starter." PLOS ONE 19, no. 9 (2024): e0310013. http://dx.doi.org/10.1371/journal.pone.0310013.
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The aviation regulations mandate that high-energy rotor components must possesses adequate containment capabilities. Ensuring the containment of the turbine wheel of the air turbine starter is of paramount importance. In this paper, the design thickness of the containment ring was determined and the containment ring deformation was given. Based on the design thickness and deformation of the containment ring, an outer casing structure design method was proposed by using FEM. Then, two containment tests were conducted for different distances between the containment ring and outer casing to validate the outer casing structure design method. The errors of the containment ring deformation are smaller than 7.5%, and the experimental results of the containment process are in accordance with the simulation, validating correctness of the outer casing structure design method. The containment ring deformation rate with the design thickness T = 10 mm is 115%. A safety margin of 1.05 is designed by considering the uniformity of containment ring deformation and the containment ring assembly error. The results illustrate that the deformed containment ring does not damage the outer casing, when the inner diameter of the outer casing is designed as 1.2 times the outer diameter of the containment ring.
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Poursaeidi, E., M. Taheri, and A. Farhangi. "Non-uniform temperature distribution of turbine casing and its effect on turbine casing distortion." Applied Thermal Engineering 71, no. 1 (2014): 433–44. http://dx.doi.org/10.1016/j.applthermaleng.2014.07.019.
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Febriansyah, Dwijaya, Barman Tambunan, Rudias Harmadi, and Budi Noviyantoro Fadjrin. "PENGARUH PEMUAIAN PANAS TERHADAP KELURUSAN POROS TURBIN UAP." Majalah Ilmiah Pengkajian Industri 14, no. 1 (2020): 71–76. http://dx.doi.org/10.29122/mipi.v14i1.3971.
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Sebagian besar penyebab kegagalan pada mesin-mesin rotasi termasuk turbin uap adalah poros yang berputar dalam kondisi misalignment. Pada turbin uap, panas yang merambat pada casing dapat merubah dimensi turbin uap karena adanya pemuaian (thermal growth) sehingga mempengaruhi kelurusan poros saat berputar. Nilai thermal growth ini perlu diketahui sebagai salah satu spesifikasi dalam penyetelan poros sebelum turbin beroperasi. Dalam studi ini, Â thermal growth pada turbin uap 3 MW diinvestigasi dengan mengukur kelurusan poros dalam kondisi panas setelah berhenti berputar dan dingin menggunakan metode laser alignment. Hasil pengukuran menunjukkan bahwa thermal growth memberikan pengaruh terhadap kelurusan poros karena adanya selisih nilai kelurusan poros saat kondisi panas dan dingin yaitu 1.0 thous (gap) dan 2.8 thous (offset) pada bidang vertikal kemudian -1.0 thous (gap) dan -2.7 thous (offset) pada bidang horisontal.Kata kunci : Turbin uap, Thermal growth, Kelurusan porosMost of the causes of rotating machines failure including steam turbine is shaft misalignment. In the steam turbine, heat that travels to the casing can change steam turbine dimension due to thermal growth which affects the shaft alignment. Thermal growth values needs to be known as one of the specifications in shaft alignment setup. In this study, thermal growth on 3 MW steam turbine was investigated by measuring the shaft alignment in hot after shut down and cold condition using laser alignment method. Results show that thermal growth has an influence on shaft alignment due to difference of alignment values when hot and cold conditions, namely 1.0 thous (gap) and 2.8 thous (offset.) in vertical plane then -1.0 thous (gap) and -2.7 thous (offset.) in horizontal plane.Key Words : Steam Turbine, Thermal growth, Shaft alignmentÂ
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Fei, Cheng-Wei, Guang-Chen Bai, Wen-Zhong Tang, and Yatsze Choy. "Optimum Control for Nonlinear Dynamic Radial Deformation of Turbine Casing with Time-Varying LSSVM." Advances in Materials Science and Engineering 2015 (2015): 1–9. http://dx.doi.org/10.1155/2015/680406.
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With the development of the high performance and high reliability of aeroengine, the blade-tip radial running clearance (BTRRC) of high pressure turbine seriously influences the reliability and performance of aeroengine, wherein the radial deformation control of turbine casing has to be concerned in BTRRC design. To improve BTRRC design, the optimum control-based probabilistic optimization of turbine casing radial deformation was implemented using time-varying least square support vector machine (T-LSSVM) by considering nonlinear material properties and dynamic thermal load. First the T-LSSVM method was proposed and its mathematical model was established. And then the nonlinear dynamic optimal control model of casing radial deformation was constructed with T-LSSVM. Thirdly, through the numerical experiments, the T-LSSVM method is demonstrated to be a promising approach in reducing additional design samples and improving computational efficiency with acceptable computational precision. Through the optimum control-based probabilistic optimization for nonlinear dynamic radial turbine casing deformation, the optimum radial deformation is 7.865 × 10−4 m with acceptable reliability degree 0.995 6, which is reduced by 7.86 × 10−5 m relative to that before optimization. These results validate the effectiveness and feasibility of the proposed T-LSSVM method, which provides a useful insight into casing radial deformation, BTRRC control, and the development of gas turbine with high performance and high reliability.
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Cwiek, Janusz, Jerzy Łabanowski, Santina Topolska, and Maria Sozańska. "Determination of Failure Causes of a Steam Turbine Casing." Solid State Phenomena 183 (December 2011): 37–42. http://dx.doi.org/10.4028/www.scientific.net/ssp.183.37.
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The paper presents results of research and failure analysis undertaken to determine failure causes of a steam turbine casing. After 130,000 hours of service the crack in a outer shell of the turbine casing was found. The inner shell of the casing was made of cast steel grade G21CrMoV5-7, and the outer shell of grade G20CrMo4-5. Following research were performed in order to determine causes of the casing failure: chemical analysis; microstructure examinations with the use of light microscope, scanning electron microscope (SEM); mechanical properties examinations using the Charpy impact test, and Vickers hardness test; fracture mode evaluation with SEM.
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Chernousenko, Olga, Dmitriy Ryndyuk, and Vitaliy Peshko. "Re-Extension of 200 MW Turbine Cast Casing Service." Journal of Mechanical Engineering 22, no. 2 (2019): 14–20. http://dx.doi.org/10.15407/pmach2019.02.014.
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Shrestha, Ujjwal, and Young-Do Choi. "A CFD-Based Shape Design Optimization Process of Fixed Flow Passages in a Francis Hydro Turbine." Processes 8, no. 11 (2020): 1392. http://dx.doi.org/10.3390/pr8111392.
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In recent times, optimization began to be popular in the turbomachinery field. The development of computational fluid dynamics (CFD) analysis and optimization technology provides the opportunity to maximize the performance of hydro turbines. The optimization techniques are focused mainly on the rotating components (runner and guide vane) of the hydro turbines. Meanwhile, fixed flow passages (stay vane, casing, and draft tube) are essential parts for the proper flow uniformity in the hydro turbines. The suppression of flow instabilities in the fixed flow passages is an inevitable process to ensure the power plant safety by the reduction of vortex-induced vibration and pressure pulsation in the hydro turbines. In this study, a CFD-based shape design optimization process is proposed with response surface methodology (RSM) to improve the flow uniformity in the fixed flow passages of a Francis hydro turbine model. The internal flow behaviors were compared between the initial and optimal shapes of the stay vane, casing, and the draft tube with J-Groove. The optimal shape design process for the fixed flow passages proved its remarkable effects on the improvement of flow uniformity in the Francis hydro turbine.
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Irasari, Pudji, Priyono Sutikno, Puji Widiyanto, and Qidun Maulana. "Performance Measurement of a Compact Generator - Hydro Turbine System." International Journal of Electrical and Computer Engineering (IJECE) 5, no. 6 (2015): 1252. http://dx.doi.org/10.11591/ijece.v5i6.pp1252-1261.
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<p>This study aims to investigate the characteristic of a compact generator – hydro turbine system. The generator is of permanent magnet type and the turbine operates in a very low head. The integration of the two components is conducted in such a way that simplifies the construction of the conventional turbine generator. The method is by mounting the generator stator to the turbine casing and the permanent magnets are assembled in the perimeter of the turbine blade rotor. This simple construction is approached by making the stator from individual teeth and yoke. The permanent magnet generator (PMG) is designed to produce the nominal power of 300 Watt 50 Hz at 83 rpm of turbine shaft. All components of the integrated turbine- generator are totally immersed in the water stream. The stator has to be hermitic to avoid water entering the spool. Another issue investigated is the influence of the type of the stator inner casing material to the generator performance. The results show, the PVC material for inner casing has a good influence to the generator performance compared with the mild steel material.</p>
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Olga, Chernousenko, Rindyuk Dmitro, Peshko Vitaliy, and Goryazhenko Vladyslav. "DEVELOPMENT OF A TECHNOLOGICAL APPROACH TO THE CONTROL OF TURBINE CASINGS RESOURCE FOR SUPERCRITICAL STEAM PARAMETERS." Eastern-European Journal of Enterprise Technologies 2, no. 1 (92) (2018): 51–56. https://doi.org/10.15587/1729-4061.2018.126042.
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A comprehensive model for evaluation of the resource of HPC of the turbine K-800-240-2, which includes calculation of thermal, stressed-strained state, cyclic and static damageability, is presented here. The numerical studies conducted with the use of modern methods of mathematical modeling showed a high impact of forces of pins’ tightening on the stressed-strained state of the casing elements (the stress level increased by 17.7 %). A technological approach to resource control, aimed at a change in pins’ tightening efforts, was proposed. It was established that this method decreases static damageability of basic metal of casings (by 9.7 %), improving its long-term strength. When taking into account tightening forces, the maximum stress intensity decreased by 9.3 %, while the stress level in the flange joint decreased by 11–41 %. These positive moments are accompanied by an increase in individual resource of the casing by 10 %. The developed concept and recommendations have significant importance for ensuring long-term operation of steam turbines with the initial pressure of hot steam at 24 MPa
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Witek, Lucjan, Marek Orkisz, Piotr Wygonik, Daniel N. Musili, and Tadeusz Kowalski. "Fracture analysis of a turbine casing." Engineering Failure Analysis 18, no. 3 (2011): 914–23. http://dx.doi.org/10.1016/j.engfailanal.2010.11.005.
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Dunn, M. G., R. M. Adams, and V. S. Oxford. "Response of Large Turbofan and Turbojet Engines to a Short-Duration Overpressure." Journal of Engineering for Gas Turbines and Power 111, no. 4 (1989): 740–47. http://dx.doi.org/10.1115/1.3240321.
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The influences of thrust setting and overpressure level on engine operating characteristics have been obtained for two different high-thrust engines. The thrust setting was varied from engine-off to take-off rated thrust (TRT) and the overpressure was varied from 6.9 kPa (1.0 psi) to 19.4 kPa (2.8 psi). The specific engines under consideration were the Pratt/Whitney TF33 low bypass ratio turbofan and the Pratt/Whitney J57 turbojet. The experimental results suggest that overpressure has little influence on either the HP compressor speed or the exhaust gas total temperature. However, the magnitude of the overpressure has a large influence on turbine exhaust total pressure and on the inlet casing and the diffuser casing radial displacements. The J57 turbine casing was significantly influenced by the overpressure, whereas the TF33 turbine casing was relatively insensitive. The J57 inlet casing radial displacement was noticeably greater than the corresponding turbofan displacement. Even though the component radial displacements for the TF33 exceeded the steady-state red-line limit by more than 300 percent, the engine did not sustain any permanent damage. The J57 did, however, experience an internal rub at an overpressure of about 14.5 kPa (2.1 psi).
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Simmons, H. R., A. J. Smalley, R. W. Frischmuth, G. Lapini, and G. Robinson. "Tools for Diagnosing Case Deflections and Alignment on a Power Utility Combustion Turbine." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 190–97. http://dx.doi.org/10.1115/1.2906791.
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This paper discusses development, installation, and analysis of instrumentation systems for reliably measuring casing, thermal distortion, and alignment deviation on a large combustion turbine in power utility service. A variety of redundant measurement systems were installed to document casing distortion during the cooldown period after firing. The operating principles of each measurement system are described and presented with the rationale developed for installing and locating sensors. A vertical deflection sensor used for casing bow and bearing misalignment measurement is highlighted in the paper to illustrate its potential for use in other investigations. Additional sensors used include an array of shaft proximity probes, blade tip proximity probes, thermocouples, and axial growth probes. A measurement system for casing ovalization was developed using LVDTs mounted from a thermally stabilized ring. An automated data acquisition system was developed and installed to facilitate the recording of turbine cool-down events over the complete operating season without the need for constant on-site attention. Preliminary results define the turbine cylinder bow and ovalization response during the cool-down event following normal unit operation and correlated casing distortions with thermal gradients.
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Becker, B., and B. Schetter. "Gas Turbines Above 150 MW for Integrated Coal Gasification Combined Cycles (IGCC)." Journal of Engineering for Gas Turbines and Power 114, no. 4 (1992): 660–64. http://dx.doi.org/10.1115/1.2906639.
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Commercial IGCC power plants need gas turbines with high efficiency and high power output in order to reduce specific installation costs and fuel consumption. Therefore the well-proven 154 MW V94.2 and the new 211 MW V94.3 high-temperature gas turbines are well suited for this kind of application. A high degree of integration of the gas turbine, steam turbine, oxygen production, gasifier, and raw gas heat recovery improves the cycle efficiency. The air use for oxygen production is taken from the gas turbine compressor. The N2 fraction is recompressed and mixed with the cleaned gas prior to combustion. Both features require modifications of the gas turbine casing and the burners. Newly designed burners using the coal gas with its very low heating value and a mixture of natural gas and steam as a second fuel are developed for low NOx and CO emissions. These special design features are described and burner test results presented.
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Bajic´, Branko, and Andreas Keller. "Spectrum Normalization Method in Vibro-Acoustical Diagnostic Measurements of Hydroturbine Cavitation." Journal of Fluids Engineering 118, no. 4 (1996): 756–61. http://dx.doi.org/10.1115/1.2835506.
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Full-scale vibro-acoustical diagnostic measurements of cavitation in four Francis 6 MW double runner turbines were performed. Two types of sensors were used—a hydrophone sensing waterborne noise at the pressure side of a runner and an accelerometer mounted at various points at the outer turbine casing, facing the runner’s pressure side. The correlation of noise and acceleration intensity with suction-side pressure fluctuations and runner position was checked. A simple but efficient method of spectrum normalization, which rejects the influence of the measurement set characteristics and vibro-acoustical characteristics of a turbine, was developed. The resulting spectra reveal the dependence of cavitation source strength on the turbine power as a function of noise or acceleration frequency.
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Ao, Liang Bo, Yuan Sheng Li, Zhi Xun Wen, Lei Li, and Zhu Feng Yue. "Multidisciplinary Design Optimization Framework for Aeroengine Turbine Based on Life and Reliability." Advanced Materials Research 538-541 (June 2012): 2690–93. http://dx.doi.org/10.4028/www.scientific.net/amr.538-541.2690.
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The multidisciplinary design optimization(MDO) framework for aeroengine turbine based on life and reliability which covers the total process is developed. The framework consists of three parts: design module of parts, subsystem and system. The parametric model and optimization of turbine components such as rotor, stator, disk, casing and axle, can be created in parts design module. The interaction in subsystems, such as rotor-stator interaction, blade-casing gap and tenon-mortise contact problem can be solved in subsystem design module. The system design module can give out the global optimal solution of the whole turbine. The MDO for an aeroengine turbine using this framework has been taken, the results show that the framework is available.
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Danieli, Piero, Massimo Masi, Andrea Lazzaretto, and Gianluca Carraro. "An engineering approach for the fast simulation of radial inflow turbines with vaneless spiral casing by single-channel CFD models." E3S Web of Conferences 312 (2021): 11003. http://dx.doi.org/10.1051/e3sconf/202131211003.
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The basic RANS-CFD analysis of the simplest radial-inflow turbine configuration is the subject of this paper. An original technique is here proposed to model the effect of the vaneless spiral casing using single-channel CFD calculations and providing an effective alternative to the more complex simulation of the 360-degree domain otherwise required to simulate this turbine configuration. The aim of the paper is to verify the effectiveness of the proposed modelling technique as a reliable engineering approach conceived to support the preliminary design phase of radial-inflow turbines with time-effective CFD calculations. To this end, the open-source CFD code MULTALL has been used to predict the aerodynamic performance of optimal designs of radial-inflow turbines with different specific speed and diameter and working with air as ideal gas. The MULTALL predictions are compared with the corresponding steady-state results obtained by calculations suited to the preliminary assessment of radial turbines designs performed on fully 360-degree turbine domains using the commercial code Star CCM+®. The investigation is conducted on two turbines that are designed in accordance with a widely validated method. The results show that the proposed CFD approach predicts well the trends and values of the aerodynamic performance of both the turbine designs: a 5% overestimation of the performance predicted by the fully 360-degree CFD models was never exceeded. The suggested turbine modelling approach implemented in MULTALL requires a three times lower computation time than the corresponding traditional 360-degree model.
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Gao, Jie, Xuezheng Liu, Xudong Zhao, Weiliang Fu, Guoqiang Yue, and Qun Zheng. "Steady and unsteady numerical investigation of flow interaction between low-pressure turbine blade, intermediate turbine duct and power turbine vane." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 232, no. 23 (2018): 4312–31. http://dx.doi.org/10.1177/0954406217751819.
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Flows in an intermediate turbine duct connecting low-pressure turbines and power turbines are very complex, affected by the upstream low-pressure turbine flow structures. Non-uniformities originating from the duct with struts also affect the power turbine inflow conditions, resulting in reduced efficiency. The present investigation is done to clarify the flow and loss mechanisms within the intermediate turbine duct and the power turbine. Steady and unsteady numerical investigations of the flow interaction between low-pressure turbine blade, intermediate turbine duct and power turbine vane were conducted. Effects of upstream low-pressure turbine blade on intermediate turbine duct flow fields and loss characteristics, and that of intermediate turbine duct with big and small struts on power turbine aerodynamics are explored. The generation and propagation of wake and secondary flows through the whole configuration are described. The fast Fourier transformation analyses of the flow in the low-pressure turbine blade, intermediate turbine duct and power turbine vane are also presented. Results from the steady and unsteady investigations show complex flow patterns resulted from blade–strut–vane flow interactions, which are not obtainable from intermediate turbine duct-only or power turbine-only simulations. The intermediate turbine duct has a great amplifying influence on the distorted inflow, and the inlet flow with upstream wakes and secondary flows introduces a high-loss area along the casing at intermediate turbine duct exit. Detailed results are presented and discussed for the flow physics and loss mechanisms as well as the unsteady flow evolution through the low-pressure turbine blade, intermediate turbine duct and power turbine vane.
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Mathioudakis, K., E. Loukis, and K. D. Papailiou. "Casing Vibration and Gas Turbine Operating Conditions." Journal of Engineering for Gas Turbines and Power 112, no. 4 (1990): 478–85. http://dx.doi.org/10.1115/1.2906192.
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The results from an experimental investigation of the compressor casing vibration of an industrial gas turbine are presented. It is demonstrated that statistical properties of acceleration signals can be linked with engine operating conditions. The power content of such signals is dominated by contributions originating from the stages of the compressor, while the contribution of the shaft excitation is secondary. Using nonparametric identification methods, accelerometer outputs are correlated to unsteady pressure measurements taken by fast response transducers at the inner surface of the compressor casing. The transfer functions allow reconstruction of unsteady pressure signal features from the accelerometer readings. A possibility is thus provided for “seeing” the unsteady pressure field of the rotor blades without actually penetrating through the casing, but by simply observing its external surface vibrations.
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Adhikari, Pradhumna, Umesh Budhathoki, Shiva Raj Timilsina, Saurav Manandhar, and Tri Ratna Bajracharya. "A Study on Developing Pico Propeller Turbine for Low Head Micro Hydropower Plants in Nepal." Journal of the Institute of Engineering 9, no. 1 (2014): 36–53. http://dx.doi.org/10.3126/jie.v9i1.10669.
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Most of the turbines used in Nepal are medium or high head turbines. These types of turbines are efficient but limited for rivers and streams in the mountain and hilly region which have considerably high head. Low head turbines should be used in the plain region if energy is to be extracted from the water sources there. This helps in the rural electrification and decentralized units in community, reducing the cost of construction of national grid and also to its dependency, in already aggravated crisis situation. There are good turbine designs for medium to high heads but traditional designs for heads under about 5m (i.e. cross flow turbine and waterwheel) are slow running, requiring substantial speed increase to drive an AC generator. Propeller turbines have a higher running speed but the airfoil blades are normally too complicated for micro hydro installations. Therefore, the open volute propeller turbine with constant thickness blades was ventured as possible solution. Such type of propeller turbine is designed to operate at low inlet head and high suction head. This enables the exclusion of closed spiral casing. Also, the constant thickness blades enable the use of forging process instead of casting of complex airfoil blades. This leads to considerable reduction in manufacturing cost and complexity. A 1kW prototype was designed and scale down model of 185W was fabricated and tested. The runner consisted of five blades of 4mm thickness with camber and twist. The runaway speed of 1058 rpm was attained at design flow rate of 25 l/s. At full load the efficiency of model was found to be about 57%. Applying scaling effects the expected efficiency of the prototype was estimated to be about 60%. DOI: http://dx.doi.org/10.3126/jie.v9i1.10669 Journal of the Institute of Engineering, Vol. 9, No. 1, pp. 36–53
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Kudinov, V. A., E. V. Kotova, O. Yu Kurganova, and V. K. Tkachev. "Experimental and Theoretical Research of a Hot Condition of High Pressure Cylinder of the T-100-130 Steam Turbine." ENERGETIKA. Proceedings of CIS higher education institutions and power engineering associations 62, no. 5 (2019): 459–68. http://dx.doi.org/10.21122/1029-7448-2019-62-5-459-468.
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The results of experimental and theoretical studies of the temperature state of the high- pressure cylinder (HPC) of the T-100-130 steam turbine for one of the start modes are presented. Taking into account the dependence of the coefficient of linear expansion on the temperature, the elongations of the individual sections of the casing under different temperatures and its total elongation after the turbine operation starts to correspond to the stationary operation mode have been found. The studies have shown that in the process of actuation the turbine there is a significant difference in temperature along the length of the HPC casing. In this case, the most intense heating occurs in the area from the second to the sixth section. The greatest temperature difference was observed in stationary operation at maximum temperature in the fifth section. Using the orthogonal method of L. V. Kantorovich, an approximate analytical solution of the thermal conductivity problem for a two-layer wall (turbine casing – thermal insulation) under inhomogeneous boundary conditions of the third kind is obtained. With the use of experimental data on the temperature state of the outer surface of the casing of the HPC by solving the inverse problem of thermal conductivity, the average heat transfer coefficients for the actuation period characterizing the intensity of heat transfer from steam to the casing have been found. On the basis of experimental data on the temperature change of any of the controlled parameters of the turbine over time, a theoretical method for predicting its change in a certain time range from the time of the its last measurement has been developed. The use of this method to predict the change in the temperature difference between the top and bottom of the HPC casing during the actuation showed that for a period of time equal to 3–5 minutes the forecast is fulfilled with high reliability.
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Zhang, Zongwei, Hao Chen, Cong Liu, and Qingkun Meng. "Effect of inlet conditions on the thermal insulation performance of marine gas turbine exhaust systems." Thermal Science, no. 00 (2024): 160. http://dx.doi.org/10.2298/tsci240206160z.
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A marine gas turbine insulation solution was designed to reduce exhaust system temperatures. The effects of cooling gas temperature (45?C, 55?C, 65?C), cooling air velocity (2 m/s - 10 m/s), and a range of classic aerodynamic conditions ranging on the thermal insulation performance of the gas turbine exhaust system were investigated using numerical simulations. The results indicate that the use of aerogel insulation material effectively reduces the average temperature of the exterior volute casing to 71?C from 315?C under rated turbine conditions. The exterior volute casing temperature increases with higher cooling gas inlet temperatures but decreases with increasing cooling gas inlet velocities. Additionally, alterations in the aerodynamic conditions at the gas inlet will induce changes in the thermal insulation performance of the exhaust system, and excessive circumferential flow velocities can cause localized overheating in the exhaust volute casing.
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Putra, Fajri Dwi, Nota Effiandi, and Desmarita Leni. "Pengoperasian dan Perawatan PLTMH pada Pembangkit Listrik Mikro Hidro (PLTMH) di Sungai Batang Geringging Kota Padang." Jurnal Teknik Mesin 10, no. 2 (2019): 25–30. http://dx.doi.org/10.30630/jtm.10.2.183.
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Water turbine is a tool to convert the potential energy of water into mechanical energy, this mechanical energy is then converted into electrical energy by a generator. Crossflow turbines are radial, small pressurized turbines with tangential injection from fan rotation with a horizontal shaft. The flow of water flows through the pipe entrance, and is arranged by a propeller and into the turbine fan rotation. After the water passes through the turbine fan rotation, the water is at the opposite fan rotation, thus providing additional efficiency. Finally, water flows from the casing either freely or through a tube under the turbine so that it rotates and turns the generator so it can produce electricity. Maintenance of PLTMH is carried out namely preventive maintenance such as; cleaning, lubrication and periodic checks. Maintenance corrections are carried out with the aim of being able to maintain the PLTMH component. Predictive maintenance of a treatment carried out in accordance with the conditions of the PLTMH and predicting damage that will occur in PLTMH
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Hamzah, Mohd Herzwan, and Azri Alias. "Heat Propagation Across Turbocharger Unit with Variable Turbine Inlet Temperature." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 122, no. 2 (2024): 102–17. http://dx.doi.org/10.37934/arfmts.122.2.102117.
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Currently, issues about emission gains serious attention among the lawmakers and governments. Multiple regulation and enforcements have been applied to reduce the level of emission that released to the environment. Vehicle emissions have been identified as one of the major polluters thus forcing the carmakers to explore new technology to reduce the vehicle emissions. One of the technologies that have been preferred by the carmakers is the applications of forced induction system to the internal combustion engine. By using the forced induction system where currently turbocharger system is more often used compared to supercharger, two benefits can be achieved which are improvements of engine efficiency and engine size reduction. However, the ability of turbocharger unit to deliver compressed air can be affected by the amount of heat that travels along the turbocharger unit itself. In this paper, the effect of heat that originated from the exhaust gas that enters the turbine inlet towards the turbocharger performance was measured and analysed. An automotive turbocharger unit manufactured by Garrett Turbocharger model GT2056 was used in the study. The rotational speed is set between 20 000 rpm to 70 000 rpm and the temperature at turbine inlet is set between 40℃ to 100℃. The parameters that measured are the temperature difference at internal turbine, internal bearing temperature difference, internal compressor temperature difference, turbine casing temperature difference, bearing housing temperature difference and compressor housing temperature difference. From the results obtained, it can be observed that the heat travels from turbine towards the compressor side through the conduction between the contacting parts between the turbine casing, bearing housing and lastly at compressor casing. The heat that arrives at the compressor side through the casing will give small effect to the air mass flow that delivered by the compressor.
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Gordon, J. L. "Hydroelectric turbine setting – a rational approach." Canadian Journal of Civil Engineering 18, no. 1 (1991): 27–35. http://dx.doi.org/10.1139/l91-004.
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There are no standards for the setting of a hydraulic turbine with respect to the tailwater level. Manufacturers rely on hydraulic model data to determine the required protection against cavitation, and never publish these data. Utilities and consultants must then rely on the interpretation of published statistical data relating submergence to various turbine parameters. In this paper, an alternative approach is proposed wherein a general equation is developed relating the submergence of a stainless steel or cast steel runner to the number of runner blades, the plant capacity factor, the turbine throat velocity, the tailwater level above sea level, the water temperature, and the acceptable amount of cavitation. The equations have been tested on 39 different power plants having either horizontal or vertical axis Kaplan, propeller, or Francis turbines, both large and small. The equations are particularly useful for establishing the turbine diameter and setting during feasibility assessment, and for comparing manufacturer's suggested turbine parameters in the final design stage. The equations can also be used to determine the capacity of a new runner in an existing casing. Key words: hydroelectric, turbines, cavitation, design.
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Price, John W. H. "The failure of the Dartmouth turbine casing." International Journal of Pressure Vessels and Piping 75, no. 7 (1998): 559–66. http://dx.doi.org/10.1016/s0308-0161(98)00048-9.
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Antar, E., and M. Elkhoury. "Casing optimization of a Savonius wind turbine." Energy Reports 6 (February 2020): 184–89. http://dx.doi.org/10.1016/j.egyr.2019.08.040.
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CHOI, WOOSUNG, and JUNGSEOB HYUN. "A LIFE ASSESSMENT FOR STEAM TURBINE CASING USING INELASTIC ANALYSIS." Modern Physics Letters B 22, no. 11 (2008): 1141–46. http://dx.doi.org/10.1142/s0217984908015978.
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An important characteristic of a fossil power plant is its ability to maintain reliability and safety of the plant against frequent start-ups and load changes. Unstable states arising during start-ups, shutdowns and load changes give rise to unsteady temperature distribution with time in steam turbine innercasing (HP/IP), which results in non-uniform strain and stress distribution. The rapid increase of temperature during starts-ups, especially, causes susceptible to failure and reduction of expected life for steam turbine components. Thus accurate knowledge of thermal stresses is required for the integrity and lifetime assessment for the turbine components. In this paper, the fatigue damage is calculated of steam turbine inner casing was calculated by combining the stress analysis based procedure and Neuber's rule. By substituting the material cyclic stress-strain relationship into the Neuber equation, the inelastic total strain range was obtained. Using this study, life consumption of steam turbine inner-casing can be obtained and a guideline for effective maintenance was proposed.
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Kalashnikov, D. A., A. S. Pugachuk, E. O. Kalashnikova, and A. V. Chernyshev. "Analysis of Methods for Reducing Power Losses in the Compressor Impeller when Balancing the Turbine Generator Rotor at the Operating Speed." Proceedings of Higher Educational Institutions. Маchine Building, no. 2 (731) (February 2021): 26–33. http://dx.doi.org/10.18698/0536-1044-2021-2-26-33.
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The article considers the problems of performing full-scale tests, including balancing the rotors of the gas turbine engines together with body parts. Since during balancing it is necessary to distance the natural frequency of the oscillatory system as much as possible from the test imbalance frequency, it is recommended to balance at the operating frequencies of the rotor without stator parts forming the flow path of the compressor and turbine stages. Therefore, when testing or balancing, large power is required for performing the work of air ventilation, as well as the work against viscous friction forces. One of the most significant problems is the need to provide significant driving power for a gas dynamic or balancing stand, which imposes strict requirements and complicates its design. Methods of power reduction for balancing the rotor of a gas turbine unit with body parts are proposed. One method, balancing in the technological casing, is considered in more detail. Several variants of such casings have been developed and investigated, for each of them the values of the required power draw have been obtained. The studies were carried out by the mathematical simulation of gas flow processes in the computational domain formed by the impeller and the inner surface of each particular variant of the casing. As a result of the calculated data analysis recommendations significantly speeding up balancing the rotor of a gas turbine unit and reducing the cost have been developed.
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Kim, Jae Hoon, Duck Hoi Kim, Kyoung Joo Kim, Woo Sung Sim, Young Shin Lee, and Won Shik Park. "The Study on Failure Behavior and Low Cycle Fatigue Life of Hot Gas Casing for Gas Turbine." Key Engineering Materials 353-358 (September 2007): 499–502. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.499.
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In this study, failure behavior of hot gas casing for gas turbine was investigated. The microstructure and damage mechanism of serviced hot gas casing were examined. Also low cycle fatigue tests of the Inconel 617 super alloy is used for structural material of hot gas casing were performed. To predict the low cycle fatigue life, Coffin-Manson and strain energy density methods were used.
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Chana, Kam S., and Terry V. Jones. "An Investigation on Turbine Tip and Shroud Heat Transfer." Journal of Turbomachinery 125, no. 3 (2003): 513–20. http://dx.doi.org/10.1115/1.1575253.
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Detailed experimental investigations have been performed to measure the heat transfer and static pressure distributions on the rotor tip and rotor casing of a gas turbine stage with a shroudless rotor blade. The turbine stage was a modern high pressure Rolls-Royce aero-engine design with stage pressure ratio of 3.2 and nozzle guide vane (ngv) Reynolds number of 2.54E6. Measurements have been taken with and without inlet temperature distortion to the stage. The measurements were taken in the QinetiQ Isentropic Light Piston Facility and aerodynamic and heat transfer measurements are presented from the rotor tip and casing region. A simple two-dimensional model is presented to estimate the heat transfer rate to the rotor tip and casing region as a function of Reynolds number along the gap.
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Turner, M. G. "Multistage Turbine Simulations With Vortex–Blade Interaction." Journal of Turbomachinery 118, no. 4 (1996): 643–53. http://dx.doi.org/10.1115/1.2840920.
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The average passage approach of Adamczyk et al. (1990) has been used to simulate the multistage environment of the General Electric E3 low-pressure turbine. Four configurations have been analyzed and compared to test data. These include the nozzle only, the first stage, the first stage and a half, and the first two stages. A high casing slope on the first-stage nozzle causes the secondary flow vortex to separate off the casing and enter the downstream rotor. The detrimental effect on performance due to this vortex interaction has been predicted by the above approach, whereas isolated blade row calculations cannot simulate this interaction. The unsteady analysis developed by Chen et al. (1994) has also been run to understand the unsteady flow field in the first-stage rotor and compare with the average passage model and test data. Comparisons of both the steady and unsteady analyses with data are generally good, although in the region near the casing of the shrouded rotors, the predicted loss is lower than that shown by the data.
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Todorov, Georgi, Ivan Kralov, Konstantin Kamberov, Evtim Zahariev, Yavor Sofronov, and Blagovest Zlatev. "An Assessment of the Embedding of Francis Turbines for Pumped Hydraulic Energy Storage." Water 16, no. 16 (2024): 2252. http://dx.doi.org/10.3390/w16162252.
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In this paper, analyses of Francis turbine failures for powerful Pumped Hydraulic Energy Storage (PHES) are conducted. The structure is part of PHES Chaira, Bulgaria (HA4—Hydro-Aggregate 4). The aim of the study is to assess the structure-to-concrete embedding to determine the possible causes of damage and destruction of the HA4 Francis spiral casing units. The embedding methods that have been applied in practice for decades are discussed and compared to those used for HA4. A virtual prototype is built based on the finite-element method to clarify the influence of workloads under the generator mode. The stages of the simulation include structural analysis of the spiral casing and concrete under load in generator mode, as well as structural analysis of the spiral casing under loads in generator mode without concrete. Both simulations are of major importance. Since the failure of the surface between the turbine, the spiral casing, and the concrete is observed, the effect of the growing contact gap (no contact) is analyzed. The stresses, strains, and displacements of the turbine units are simulated, followed by an analysis for reliability. The conclusions reveal the possible reasons for cracks and destruction in the main elements of the structure.
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Choi, Young Jin, Young Shin Lee, Jae Hoon Kim, Won Shik Park, and Hyun Soo Kim. "A Study on the Flow and Thermal Stress Analysis of the Hot Gas Casing of the Gas Turbine." Key Engineering Materials 306-308 (March 2006): 169–74. http://dx.doi.org/10.4028/www.scientific.net/kem.306-308.169.
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The hot gas casing of the gas turbine has operated in high temperatures and thermal gradients. The structure safety of hot gas casing will be highly depend on the thermal stress. In this paper, flow and thermal stress analysis of the hot gas casing is carried out using ANSYS program. The obtained temperature data by flow analysis of hot gas casing is applied to the load condition of the thermal analysis. The thermal stress analysis is carried out the elastic-plasticity analysis. The pressure, temperature and velocity of the flow and thermal stress of the hot gas casing are presented
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Mahto, Navin, and Satyanarayanan R. Chakravarthy. "Comparison of Response Surface Based Preliminary Design Methodologies for a Gas Turbine Combustor." Defence Science Journal 74, no. 2 (2024): 216–24. http://dx.doi.org/10.14429/dsj.74.19624.
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Preliminary design of gas turbine combustor is a multi-objective optimization problem. The methodology to be used at the preliminary design stage depends on the freedom of design choices available. In this article, we explore three preliminary design methodologies for gas turbine combustor - M1: combustion liner design for a given casing; M2: combustion liner design without the casing and M3: coupled design of combustion liner and casing. A workflow for the automated design space exploration of gas turbine combustor using response surface methodology is presented. Computational fluid dynamics studies along with central composite design for design of experiments and genetic aggregation for response surface generation are used to quantify the combustor performance in design space. Comparison of three different design methodologies (M1, M2 and M3) is made to show how the choice of design methodology changes the available design space and limits/expands combustor performance. Candidate optimal designs and associated trade-offs from the optimization study are also presented. This study can aid combustor design engineers choose the most suitable preliminary design methodology for their specific use case.
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Balakumar., C., Chandrasekhar U., and Chandra Mohana Reddy B. "Assessment of Mechanical Design Parameters for an Aero Gas Turbine Engine Jet Pipe Casing using Finite Element Analysis." International Journal of Engineering and Advanced Technology (IJEAT) 9, no. 5 (2020): 1197–201. https://doi.org/10.35940/ijeat.E1072.069520.
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Aero Gas Turbine engines power aircrafts for civil transport application as well as for military fighter jets. Jet pipe casing assembly is one of the critical components of such an Aero Gas Turbine engine. The objective of the casing is to carry out the required aerodynamic performance with a simultaneous structural performance. The Jet pipe casing assembly located in the rear end of the engine would, in case of fighter jet, consist of an After Burner also called as reheater which is used for thrust augmentation to meet the critical additional thrust requirement as demanded by the combat environment in the war field. The combustion volume for the After burner operation together with the aerodynamic conditions in terms of pressure, temperature and optimum air velocity is provided by the Jet pipe casing. While meeting the aerodynamic requirements, the casing is also expected to meet the structural requirements. The casing carries a Convergent-Divergent Nozzle in the downstream side (at the rear end) and in the upstream side the casing is attached with a rear mount ring which is an interface between engine and the airframe. The mechanical design parameters involving Strength reserve factors, Fatigue Life, Natural Frequencies along with buckling strength margins are assessed while the Jet pipe casing delivers the aerodynamic outputs during the engine operation. A three dimensional non linear Finite Element analysis of the Jet pipe casing assembly is carried out, considering the up & down stream aerodynamics together with the mechanical boundary conditions in order to assess the Mechanical design parameters.