Relevant bibliographies by topics / Turbine blade

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Academic literature on the topic 'Turbine blade'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 September 2023

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Journal articles on the topic "Turbine blade"

1

Xing, Zhitai, Yan Jia, Lei Zhang, Xiaowen Song, Yanfeng Zhang, Jianxin Wu, Zekun Wang, Jicai Guo, and Qingan Li. "Research on Wind Turbine Blade Damage Fault Diagnosis Based on GH Bladed." Journal of Marine Science and Engineering 11, no. 6 (May 26, 2023): 1126. http://dx.doi.org/10.3390/jmse11061126.

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With the increasing installed capacity of wind turbines, ensuring the safe operation of wind turbines is of great significance. However, the failure of wind turbines is still a severe problem, especially as blade damage can cause serious harm. To detect blade damage in time and prevent the accumulation of microdamage of blades evolving into severe injury, a damage dataset based on GH Bladed simulation of blade damage is proposed. Then, based on the wavelet packet analysis theory method, the MATLAB software can automatically analyze and extract the energy characteristics of the signal to identify the damage. Finally, the GH Bladed simulation software and MATLAB software are combined for fault diagnosis analysis. The results show that the proposed method based on GH Bladed to simulate blade damage and wavelet packet analysis can extract damage characteristics and identify single-unit damage, multiple-unit damage, and different degrees of damage. This method can quickly and effectively judge the damage to wind turbine blades; it provides a basis for further research on wind turbine blade damage fault diagnosis.
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Wijaya, Rudi Kusuma, and Iwan Kurniawan. "Study Experimental Darrieus Type-H Water Turbines Using NACA 2415 Standard Hydrofoil Blade." Jurnal Pendidikan Teknik Mesin Undiksha 9, no. 2 (August 31, 2021): 109–23. http://dx.doi.org/10.23887/jptm.v9i2.29257.

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Telah dilakukan kaji eksperimental turbin air Darrieus tipe-H menggunakan blade hydrofoil standar NACA 2415 untuk mengetahui nilai torsi statik dan dinamik yang dihasilkan turbin air Darrieus tipe-H 3 blade dan 6 blade, pengujian menggunakan water tunnel dimensi 6m x 0.6m x 1m. Variasi tiga blade dan enam blade, dengan diameter turbin 0.44 m x 0.15 m pada turbin luar dan 0.18 x 0.14 m pada turbin bagian dalam, panjang chord 0.10 m dengan variasi sudut serang 0º sampai dengan 360º, variasi kecepatan air pertama 0.3 m/s, variasi kecepatan aliran air kedua 0.65 m/s. Kecepatan air 0.3 m/s enam blade, torsi statik 0.3 Nm, torsi dinamik nya 0.384 Nm, kecepatan air 0,65 m/s torsi dinamik 0.432 Nm dan torsi statik nya 0.384 Nm, pengujian turbin Darrieus tiga blade kecepatan air 0,3 m/s nilai torsi dinamik 0.336 Nm dan dengan kecepatan yang sama torsi statik nya 0.264 Nm. Pada kecepatan air 0.65 m/s nilai torsi dinamik sebesar 0.384 Nm, dan nilai torsi statik 0.336 Nm. Dari data hasil pengukuran tersebut dapat disimpulkan bahwa variasi turbin enam blade memiliki nilai torsi statik dan torsi dinamik yang lebih tinggi dari pada turbin tiga blade, jumlah blade sangat berpengaruh terhadap daya serap energi kinetik air untuk di konversikan menjadi torsi statik maupun torsi dinamik.Kata kunci : Turbin Hydrokinetic, Darrieus, Torsi Statik,Torsi DinamikAn experimental study of the H-type Darrieus water turbine was carried out using a standard NACA 2415 hydrofoil blade to determine the value of static and dynamic torque generated by the 3-blade and 6-blade Darrieus H-type water turbine, testing using a water tunnel dimensions of 6m x 0.6m x 1m. Variation of three blades and six blades, with a turbine diameter of 0.44 mx 0.15 m on the outer turbine and 0.18 x 0.14 m on the inner turbine, chord length 0.10 m with variations in angle of attack 0º to 360º, variation of first water velocity 0.3 m / s second water flow velocity 0.65 m / s. Water velocity 0.3 m / s six blades, static torque 0.3 Nm, dynamic torque 0.384 Nm, water velocity 0.65 m / s dynamic torque 0.432 Nm and static torque 0.384 Nm, Darrieus three blade turbine test water speed 0.3 m / s dynamic torque value of 0.336 Nm and with the same speed its static torque is 0.264 Nm. At 0.65 m / s water velocity, the dynamic torque value is 0.384 Nm, and the static torque value is 0.336 Nm. From the measurement data, it can be concluded that the six-blade turbine variation has a higher value of static torque and dynamic torque than the three-blade turbine, the number of blades greatly influences the absorption of water kinetic energy to be converted into static torque and dynamic torque. Keywords: Hydrokinetic Turbine, Darrieus, static torque, dynamic torqueDAFTAR RUJUKANKirke, B.K. (2011). Tests on ducted and bare helical and straight blade Darrieus hydrokinetic turbines, 36, pp.3013-3022Dominy, R., Lunt, P., Bickerdyke A., Dominy, J. (2007). Self-starting capability of a Darrieus turbine. Proc Inst Mech Eng (IMechE) ePart A: J Power Energy ;221: 111-120Decoste, Josh. (2004). Self-Starting Darrieus Wind Turbine. Department of Mechanical Engineering, Dalhousie University.Febrianto, A., & Santoso, A. (2016). “Analisa Perbandingan Torsi Dan rpm Tipe Darrieus Terhadap Efisiensi Turbin”. Fakultas Teknologi Kelautan, Institut Teknologi Sepuluh Nopember (ITS)Febriyanto, N. (2014). “Studi Perbandingan Karakteristik Airfoil NACA 0012 Dengan NACA 2410 Terhadap Koefisien Lift dan Koefisien Drag Pada Berbagai Variasi Sudut Serang Dengan CFD” Fakultas teknik, Universitas Muhammadiyah SurakartaSaputra, G. (2016). Kaji Eksperimental Turbin Angin Darrieus-H Dengan Bilah Tipe NACA 2415. Universitas Riau, JOM Teknik Mesin vol. 3 No. 1.Hafied, B. (2018). Kaji Eksperimental Torsi Statik Dan Torsi Dinamik Hidrokinetik Turbin Savonius Single Stage Type Bach Tiga Sudu. Tugas Akhir Teknik Mesin. Fakultas Teknik Universitas Riau.Hau, E. (2005). Wind Turbines: Fundamentals, Technologies, Aplication, Economics. Springer. Berlin.Kaprawi. (2011), Pengaruh Geometri Blade Dari Turbin Air Darrieus Terhadap Kinerjany. Prosiding Seminar Nasional AVoER ke-3 PalembangKhan, M. J., Bhuyan, G., Iqbal M. T., & Quaicoe J.E. (2009). Hydrokinetic Energy Conversion Systems and Assessment of Horizontal and Vertical Axis Turbines for River and Tidal: Applications A Technology Status Review. Applied Energy, 86, 1823-1835.Lain, S., & Osario, C. (2010). Simulation and Evaluation of a Sraight Bladed Darrieus Type Cross Flow Marine Turbine. Journal of Scientific & Research, Vol. 69 p.906-912Marizka, L. D. (2010). Analisis Kinerja Turbin Hydrokinetic Poros Vertical Dengan Modifikasi Rotor Savonius L Untuk Optimasi Kinerja Turbin. Tugas Akhir Sains Fisika. FMIPA-Universitas Sebelas Maret.Malge, P. (2015).Analysis of Lift and Drag Forces at Different Azimuth Angle of Innovative Vertical Axis Wind Turbine.International Journal of Energy Engineering 4(5-8).Teja, P., D. (2017). Studi Numerik Turbin Angin Darrieus – Savonius Dengan Penambahan Stage Rotor Darrieus. Institut Teknologi Sepuluh Nopember, Surabaya.Zobaa, A. F., & Bansal, R. C. (2011). Handbook of Renewable Energy Technology. USA: World Scientific Publishing Co. Pte. Ltd.
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Jamal, Jamal. "Pengaruh Jumlah Sudu Terhadap Kinerja Turbin Savonius." INTEK: Jurnal Penelitian 6, no. 1 (May 25, 2019): 64. http://dx.doi.org/10.31963/intek.v6i1.1127.

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Savonius wind turbines are wind turbines that canoperate at low wind speeds, this type of turbine is very suitable tobe used in several places in Indonesia. The research aims toimprove the performance of the Savonius wind turbine withvariations in the number of turbine blades as well as variations inthe velocity of wind speed. The research method wasexperimental where wind turbine testing was carried out withvariations in the number of turbine blades with number of 2, 3and 4 blades, other variations carried out were wind speed at 3.5;4,5; 5.5 and 6.5 m/s. The study results show that the 2-bladeturbine produces greater rotation, but the torque moment islower than the 3 and 4 blade turbines, this can be seen in the lowefficiency of the 2 blade turbine at low wind speeds with highloading. At 3.5 m / s wind turbines 2 blade turbines haveefficiency that tends to be the same as 3 and 4 blade turbines upto 0.5 N but at loads of 0.6 - 1.2 N 2 blade turbines have lowerefficiency, while at wind speeds of 4.5 - 6.5 m / s 2 blade turbineshave greater efficiency than turbines 3 and 4 blades up to a loadof 1.2 N but if the load is added then the efficiency of 2-bladeturbines can be smaller than efficiency 3 and 4-blade.
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Cao, Kathy, Kelsey Shaler, and Nick Johnson. "Comparing wind turbine aeroelastic response predictions for turbines with increasingly flexible blades." Journal of Physics: Conference Series 2265, no. 3 (May 1, 2022): 032025. http://dx.doi.org/10.1088/1742-6596/2265/3/032025.

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Abstract Highly flexible blades are becoming more prevalent designs as a potential solution to the transportation challenges associated with large-scale wind turbine rotors. However, there is currently no quantitative definition of “highly flexible” blades. To further develop turbines with highly flexible blades, a precise definition of the term and accurate simulations of turbines with such blades are required. Assumptions made in the traditional aerodynamic model, Blade Element Momentum (BEM) theory, are violated in turbines with flexible blades. However, Free Vortex Wake (FVW) methods can more accurately model these turbine designs. Though more computationally expensive than BEM, FVW methods are still computationally tractable for use in iterative turbine design. The purpose of this work was to determine the blade flexibility at which BEM and FVW methods begin to produce diverging aeroelastic response results. This was accomplished by simulating the BAR-DRC reference turbine with increasingly flexible blades in a range of steady, uniform inflow conditions using OpenFAST, the National Renewable Energy Laboratory’s physics-based turbine engineering tool. Blade-tip deflections confirmed that BEM and FVW results diverge as blade flexibility increases. For the 212 m rotor diameter turbine used in this study, the two methods largely agreed for smaller blade deflections. But their results differed by an average of 5% when the out-of-plane blade-tip deflections exceeded 5% of the blade length and in-plane blade-tip deflections exceeded 1.25% of the blade length, with percent differences approaching 25% at the largest deflections.
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Alipour, Ramin, Roozbeh Alipour, Seyed Saeid Rahimian Koloor, Michal Petrů, and Seyed Alireza Ghazanfari. "On the Performance of Small-Scale Horizontal Axis Tidal Current Turbines. Part 1: One Single Turbine." Sustainability 12, no. 15 (July 24, 2020): 5985. http://dx.doi.org/10.3390/su12155985.

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The blade number of a current tidal turbine is one of the essential parameters to increase the stability, performance and efficiency for converting tidal current energy into rotational energy to generate electricity. This research attempts to investigate the effect of blade number on the performance of a small-scale horizontal tidal current turbine in the case of torque, thrust coefficient and power coefficient. Towards this end and according to the blade element momentum theory, three different turbines, i.e., two, three and four-bladed, were modeled using Solidworks software based on S-814 airfoil and then exported to the ANSYS-FLUENT for computational flow dynamics (CFD) analysis. SST-K-ω turbulence model was used to predict the turbulence behavior and several simulations were conducted at 2 ≤ tip speed ratio ≤ 7. Pressure contours, turbulence kinetic energy contours, cut-in-speed-curves, and streamlines around the blades and rotors were extracted and compared to provide an ability for a deep discussion on the turbine performance. The results show that in the case of obtainable power, the optimal value of tip speed ratio is around 5, so that the maximum power was achieved for the four-bladed turbine. Out of optimal condition, higher blade number and lower blade number turbines should be used at less than and greater than the optimal values of tip speed ratio, respectively. The results of simulations for the three-bladed turbine were validated against the experimental data with good agreement.
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McNerney, G. M., C. P. van Dam, and D. T. Yen-Nakafuji. "Blade-Wake Interaction Noise for Turbines With Downwind Rotors." Journal of Solar Energy Engineering 125, no. 4 (November 1, 2003): 497–505. http://dx.doi.org/10.1115/1.1627830.

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The interaction between the rotor and the tower wake is an important source of noise for wind turbines with downwind rotors. The tower wake modifies the dynamic pressure and the local flow incidence angle as seen by the blades and, hence, modifies the aerodynamic loading of the blade during blade passage. The resulting n per revolution fluctuation in the blade loading (where n is the number of blades) is the source of low frequency but potentially high amplitude sound levels. The Wind Turbine Company (WTC) Proof of Concept 250 kW (POC) wind turbine has been observed by field personnel to produce low-frequency emissions at the National Wind Technology Center (NWTC) site during specific atmospheric conditions. Consequently, WTC is conducting a three-phase program to characterize the low frequency emissions of its two-bladed wind turbines and to develop noise mitigation techniques if needed. This paper summarizes the first phase of this program including recent low-frequency noise measurements conducted on the WTC POC250 kW wind turbine, a review of the wake characteristics of circular towers as they pertain to the blade-wake interaction problem, and techniques to attenuate the sound pressure levels caused by the blade-wake interaction.
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Peczkis, Grzegorz, Piotr Wiśniewski, and Andriy Zahorulko. "Experimental and Numerical Studies on the Influence of Blade Number in a Small Water Turbine." Energies 14, no. 9 (May 2, 2021): 2604. http://dx.doi.org/10.3390/en14092604.

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This paper demonstrates the procedure of blade adjustment in a Kaplan-type water turbine, based on calculations of the flow system. The geometrical adjustment of a twisted blade with varying chord length is described in the study. Computational fluid dynamics (CFD) analysis was used to characterise aerofoil and turbine performance. Furthermore, two turbines, with a different number of blades, were designed, manufactured, and tested experimentally. The numerical model results were then compared with the experimental data. The studies were carried out with different rotational velocities and different stator blade incidence angles. The paper shows a comparison of the turbine efficiencies that were assessed, using numerical and experimental methods, of a flow system with four- and five-bladed rotors. The numerical model results matched up well with those of the experimental study. The efficiency of the proposed turbines reached up to 72% and 84% for four-bladed and five-bladed designs, respectively. These efficiencies, when considered with the turbine’s simplicity, low production and maintenance costs, as well as their potential for harvesting energy from low energy flows, mean that Kaplan turbines provide a promising technology for processing renewable energy.
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Sahin, M., and T. Farsadi. "Effects of Atmospheric Icing on Performance of Controlled Wind Turbine." IOP Conference Series: Earth and Environmental Science 1121, no. 1 (December 1, 2022): 012011. http://dx.doi.org/10.1088/1755-1315/1121/1/012011.

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Abstract Icing deteriorates the performance of wind turbine rotors by changing the blade airfoils’ shapes. It decreases the lift, increases the drag, and subsequently causes power production losses and load increase on turbines’ structures. In the present study, the effects of atmospheric icing on the performance of a controlled large-scale wind turbine is estimated through simulations. To achieve the target, the MS (Mustafa Sahin) Bladed Wind Turbine Simulation Model is used for the analyses of the National Renewable Energy Laboratory (NREL) 5 MW turbine with and without iced blades. Icing modeling is realized based on its main characteristics and its effects on blade aerodynamics. Turbine performance estimations are carried out at various uniform wind speeds between cut-in and cut-out wind speeds and are presented in terms of various turbine parameters such as power, thrust force, blade pitch angle, and rotor speed. Simulation evaluations show that even a light ice accretion along the blades varies the turbine characteristics and dynamics, changes the cut-in and rated wind speeds, and affects the aforementioned turbine parameters differently in the below and above rated regions.
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Zhang, Xiao, and Maosheng Zheng. "Numerical Simulation of Fluid-Structure Coupling for a Multi-Blade Vertical-Axis Wind Turbine." Applied Sciences 13, no. 15 (July 26, 2023): 8612. http://dx.doi.org/10.3390/app13158612.

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The aerodynamic characteristics of the vertical-axis wind turbine with three, four, five, and six blades are studied numerically. A coupling model of fluid flow and solid turbine blade is established to model the interactions between air and wind turbine. The pressure distribution and blade deformation affected by air are obtained and discussed. For the four wind turbines with different numbers of blades, the maximum pressure in the entire machine structure occurs at the variable angle position of the blades in the windward region under the same wind speed. Mainly due to the rapid airflow variation, complex turbulence, and significant influence of the wind field on the blades in this position, this part of the blades is prone to bending or damage. Under identical external wind field conditions, wind turbines with four and six blades exhibit significantly higher equivalent pressures on their surfaces compared to those with five and three blades. The maximum equivalent pressure of six blades can reach 3.161 × 106 Pa. The maximum deformation of the blade basically occurs at the tip and four sides of the blade. The six-blade wind turbines withstand higher and non-uniform surface pressures on their blades, resulting in the largest deformation of up to 11.658 mm. On the other hand, the four-blade wind turbine exhibits the smallest deformation. The above conclusions provide theoretical guidance for the design and optimization of vertical-axis wind turbines.
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Chen, Kun Nan, and Wei Hsin Gau. "Structural Optimization on Composite Blades of Large-Scale Wind Turbines." Applied Mechanics and Materials 284-287 (January 2013): 958–62. http://dx.doi.org/10.4028/www.scientific.net/amm.284-287.958.

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Turbine blades used in large-scale, horizontal-axis wind turbines are usually made from composite materials to reduce the weight while attaining a reasonable strength to weight ratio. The design of large wind turbine blades must consider both their aerodynamic efficiency and structural robustness. This paper presents an optimum design scheme for composite wind turbine blades. The first optimization phase produces the aerodynamic outer shape of a blade framed by airfoils with optimum cord lengths and twist angles along the blade spanwise direction. The second phase provides optimal material distribution for the composite blade. Loadings on the blade are simulated using wind field and wind turbine dynamics codes. The maximum loads on the turbine blade are then extracted and applied to a parameterized finite element model. A design example of a 3 MW wind turbine blade considering one critical load case with a mean wind speed of 25 m/s is demonstrated. The optimization result shows that although the initial blade model is an infeasible design, the optimization process eventually converges to a feasible solution with an optimized mass of 8750.2 kg.
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Dissertations / Theses on the topic "Turbine blade"

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Choi, Jungho. "An experimental investigation of turbine blade heat transfer and turbine blade trailing edge cooling." Texas A&M University, 2004. http://hdl.handle.net/1969.1/1377.

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This experimental study contains two points; part1 – turbine blade heat transfer under low Reynolds number flow conditions, and part 2 – trailing edge cooling and heat transfer. The effect of unsteady wake and free stream turbulence on heat transfer and pressure coefficients of a turbine blade was investigated in low Reynolds number flows. The experiments were performed on a five blade linear cascade in a low speed wind tunnel. A spoked wheel type wake generator and two different turbulence grids were employed to generate different levels of the Strouhal number and turbulence intensity, respectively. The cascade inlet Reynolds number based on blade chord length was varied from 15,700 to 105,000, and the Strouhal number was varied from 0 to 2.96 by changing the rotating wake passing frequency (rod speed) and cascade inlet velocity. A thin foil thermocouple instrumented blade was used to determine the surface heat transfer coefficient. A liquid crystal technique based on hue value detection was used to measure the heat transfer coefficient on a trailing edge film cooling model and internal model of a gas turbine blade. It was also used to determine the film effectiveness on the trailing edge. For the internal model, Reynolds numbers based on the hydraulic diameter of the exit slot and exit velocity were 5,000, 10,000, 20,000, and 30,000 and corresponding coolant – to – mainstream velocity ratios were 0.3, 0.6, 1.2, and 1.8 for the external models, respectively. The experiments were performed at two different designs and each design has several different models such as staggered / inline exit, straight / tapered entrance, and smooth / rib entrance. The compressed air was used in coolant air. A circular turbulence grid was employed to upstream in the wind tunnel and square ribs were employed in the inlet chamber to generate turbulence intensity externally and internally, respectively.
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Guerra, Mario. "Turbomachinery turbine blade vibratory stress prediction." Mémoire, École de technologie supérieure, 2006. http://espace.etsmtl.ca/535/1/GUERRA_Mario.pdf.

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Ce mémoire comportera quatre parties principales. Premièrement, une analyse des résultats expérimentaux de tests moteurs pour en retirer l'amortissement total des aubes ainsi que les contraintes vibratoires associées à chacune des résonances sera présentée. Deuxièmement, une méthode d'analyse par éléments finis avec des éléments de contact pour déterminer les fréquences naturelles et les modes sera présentée. Troisièmement, une analyse modale expérimentale en situation contrôlée sera effectuée sur une aube pour en déterminer la déformée modale ainsi que la valeur de l'amortissement pour chacun des modes. Ces résultats seront comparés avec les résultats obtenus lors des tests moteurs ainsi que les résultats obtenus par les modèles analytiques. Finalement, la méthode de prédiction des contraintes de la réponse forcée de l'aube ainsi que la comparaison entre les résultats analytiques et expérimentaux seront présentées.
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Song, Wenbin. "Shape optimization of turbine blade firtrees." Thesis, University of Southampton, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.268934.

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Kountras, Apostolos 1970. "Probabilistic analysis of turbine blade durability." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/28893.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.
Includes bibliographical references (leaves 71-72).
The effect of variability on turbine blade durability was assessed for seven design/operating parameters in three blade designs. The parameters included gas path and cooling convective parameters, metal and coating thermal conductivity and coating thickness. The durability life was modelled as limited by thermo-mechanical low cycle fatigue and creep. A nominal blade design as well as two additional variants were examined using deterministic and probabilistic approaches. External thermal and pressure boundary conditions were generated by three-dimensional CFD calculations. The location of expected failure was the bottom of the trailing edge cooling slot and was the same for all three designs examined. The nominal design had higher life and less variability for the ranges of design parameters examined. For the temperature range studied fatigue was the primary damage mechanism. The variation in cooling air bulk temperature was most important in setting the variation in blade durability life. This life variation was also affected by main gas bulk temperature and heat transfer coefficient, and cooling heat transfer coefficient, but to a lesser extent.
by Apostolos Kountras.
S.M.
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Barry, Pamela S. (Pamela Sue). "Rotational effects on turbine blade cooling." Thesis, Massachusetts Institute of Technology, 1994. http://hdl.handle.net/1721.1/12114.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1994.
Title as it appears in the June 1994 MIT Graduate List: Rotational effects of turbine cooling.
Includes bibliographical references (leaves 102-103).
by Pamela S. Barry.
M.S.
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Ryley, Joshua Claydon. "Turbine blade mid-chord internal cooling." Thesis, University of Oxford, 2014. http://ora.ox.ac.uk/objects/uuid:14469a51-517c-400c-b477-4fb432c8b648.

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Modern gas turbine engines operate at temperatures well above the melting point of the metal components. This has driven manufactures to develop sophisticated cooling methods which minimise the use of coolant to maximise engine efficiency by enabling further increases in operating temperature. This thesis investigates the cooling performance of engine representative mid-chord internal cooling passages for turbine blades. The work forms part of a larger E.C. FP7 project ERICKA (Engine Representative Internal Cooling Knowledge Applications).This thesis provides detailed maps of heat transfer coefficient (HTC) under a number of conditions, new experimental techniques, and has lead to a better understanding of the impact HTC distributions have on the thermal performance of a turbine blade at engine conditions. Transient liquid crystal experiments have been conducted on a large scale model of an engine representative internal cooling passage at three aspect ratios (width:height (chord length:spanwise length), 1:2, 1:3 and 1:4). Spatially resolved maps of Nusselt number have been produced for the full surface of the internal cooling passages. Little information exists in the literature for more engine representative geometries, and it is rare for spatial measurements to be presented over the full surface. The detailed maps provide validation data for CFD within the ERICKA programme. A novel method which produces spatially resolved maps in areas with highly non-one-dimensional heat transfer has been developed and validated. This method couples transient finite element analysis and data from transient liquid crystal experiments. Applied to the ribbed passage geometry, this produced spatially resolved maps of HTC over the rib surface. To the author’s best knowledge this is the first time spatial HTC maps have been presented for an engine representative rib. Industry best practice methods for internal cooling passage design typically apply averaged values of HTC, in part due to lack of spatially resolved data. To determine the significance of this approximation on blade design and life, experimental measurements have been applied to finite element (FEA) models at typical engine conditions. Application of a 3D HTC distribution to a FEA model of a section of ribbed wall demonstrated a significant under prediction (up to 58%) of localised thermal gradients when an average value is applied compared to a spatially resolved profile. This work demonstrated good agreement between distributions taken from experimental data and CFD predictions, indicating that CFD distributions may be more appropriate than bulk values in the design process. A 2D FEA study was undertaken to quantify the impact of HTC distribution approximations and aspect ratio on cooling of a generic turbine section. This study considered multiple adjacent internal cooling passages. It was confirmed that multi-pass arrangements offer greater heat removal for a given mass flow rate. Also a symmetric heat transfer profile with a higher HTC on the ribbed wall is the most desirable distribution. Use of average values significantly impacted the metal temperature, causing an underprediction up to 13◦C and 8◦C in the maximum and average values respectively. Based on the experimental HTC data, the 1:3 aspect ratio passage offered the lowest metal temperatures. Applying HTC distributions from CFD data (calculated with using the centreline temperature) showed, in general, good agreement, with the lowest metal temperatures (by up to 8◦C) in the 1:4 aspect ratio passage. Use of and HTC distribution provided by CFD prediction based on the mixed bulk temperature, produced average and peak metal temperatures 16◦C and 17◦C, respectively, lower in the 1:4 aspect ratio passage than the next best design. This highlights the need for appropriate and consistent method to be used in the analysis. As expected, reducing the passage aspect ratio led to increases in both thermal gradient and total pressure loss.
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Wu, Daniel. "The Effect of Blade Aeroelasticity and Turbine Parameters on Wind Turbine Noise." Thesis, Virginia Tech, 2017. http://hdl.handle.net/10919/78714.

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In recent years, the demand for wind energy has dramatically increased as well as the number and size of commercial wind turbines. These large turbines are loud and can cause annoyance to nearby communities. Therefore, the prediction of large wind turbine noise over long distances is critical. The wind turbine noise prediction is a very complex problem since it has to account for atmospheric conditions (wind and temperature), ground absorption, un-even terrain, turbine wake, and blade deformation. In these large turbines, the blade deflection is significant and it can potentially influence the noise emissions. However, the effects of blade flexibility on turbine noise predictions have not been addressed yet, i.e. all previous research efforts have assumed rigid blades. To address this shortcoming, the present work merges a wind turbine aeroelastic code, FAST (Fatigue, Aerodynamics, Structures, and Turbulence) to a wind turbine noise code, WTNoise, to compute turbine noise accounting for blade aeroelasticity. Using the newly developed simulation tool, the effects flexible blades on wind turbine noise are investigated, as well as the effects of turbine parameters, e.g. wind conditions, rotor size, tilt, yaw, and pre-cone angles. The acoustic results are shown as long term average overall sound power level distribution over the rotor, ground noise map over a large flat terrain, and noise spectrum at selected locations downwind. To this end, two large wind turbines are modeled. The first one is the NREL 5MW turbine that has a rotor diameter of 126 m. The second wind turbine, the Sandia 13.2MW, has a rotor diameter of 206 m. The results show that the wind condition has strong effects on the noise propagation over long distances, primarily in the upwind direction. In general, the turbine parameters have no significant effects on the average noise level. However, the turbine yaw impacts significantly the turbine noise footprint by affecting the noise propagation paths. The rotor size is also a dominating factor in the turbine noise level. Finally, the blade aeroelasticity has minor effects on the turbine noise. In summary, a comprehensive tool for wind turbine noise prediction including blade aeroelasticity was developed and it was used to address its impact on modern large turbine noise emissions.
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Hettasch, Georg. "Optimization of fir-tree-type turbine blade roots using photoelasticity." Thesis, Stellenbosch : University of Stellenbosch, 1992. http://hdl.handle.net/10019.1/993.

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Thesis (MEng.)-- University of Stellenbosch, 1992. 140 leaves on single pages, preliminary pages i-xi and numbered pages 1-113. Includes bibliography. Digitized at 600 dpi grayscale to pdf format (OCR),using an Bizhub 250 Konica Minolta Scanner and at 300 dpi grayscale to pdf format (OCR), using a Hp Scanjet 8250 Scanner.
Thesis (MEng (Mechanical and Mechatronic Engineering))--University of Stellenbosch, 1992
ENGLISH ABSTRACT: The large variety of turbo-machinery blade root geometries in use in industry prompted the question if a optimum geometry could be found. An optimum blade root was defined as a root with a practical geometry which, when loaded, returns the minimum fillet stress concentration factor. A literature survey on the subject provided guidelines but very little real data to work from. An initial optimization was carried out using a formula developed by Heywood to determine loaded projection fillet stresses. The method was found to produce unsatisfactory results, prompting a photoelastic investigation. This experimental optimization was conducted in two stages. A single tang defined load stage and a single tang in-rotor stage which modeled the practical situation. The defined load stage was undertaken in three phases. The first phase was a preliminary investigation, the second phase was a parameter optimization and the third phase was a geometric optimization based on a material utilization optimization. This material optimization approach produced good results. From these experiments a practical optimum geometry was defined. A mathematical model which predicts the fillet stress concentration factor for a given root geometry is presented. The effect of expanding the single tang optimum to a three tang root was examined.
AFRIKAANSE OPSOMMING: Die groot verskeidenheid lemwortelgeometrieë wat in turbomasjiene gebruik word het die vraag na 'n optimum geometrie laat ontstaan. Vir hierdie ondersoek is 'n optimum geometrie gedefineer as 'n praktiese geometrie wat, as dit belas word, die mimimum vloeistukspanningskonsentrasiefaktor laat ontstaan. 'n Literatuur studie het riglyne aan die navorsing gegee maar het wynig spesifieke en bruikbare data opgelewer. Die eerste optimering is met die Heywood formule, wat vloeistukspannings in belaste projeksies bepaal, aangepak. Die metode het nie bevredigende resultate opgelewer nie. 'n Fotoelastiese ondersoek het die basis vir verdere optimeering gevorm. Hierdie eksperimentele optimering is in twee stappe onderneem. 'n Enkelhaak gedefineerde lasgedeelte en 'n enkelhaak in-rotor gedeelte het die praktiese situasie gemodeleer. Die gedefineerde lasgedeelte is in drie fases opgedeel. Die eerste fase was n voorlopige ondersoek. Die tweede fase was 'n parameter optimering. 'n Geometrie optimering gebasseer op 'n materiaal benuttings minimering het die derde fase uitgemaak. Die materiaal optimerings benadering het goeie resultate opgelewer. Vanuit hierdie eksperimente is 'n optimum praktiese geometrie bepaal. 'n Wiskundige model is ontwikkel, wat die vloeistukspanningskonsentrasiefaktor vir 'n gegewe wortelgeometrie voorspel. Die resultaat van 'n geometriese uitbreiding van die enkelhaaklemwortel na 'n driehaaklemwortel op die spanningsverdeling is ondersoek.
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Walker, Peter John. "Blade lean in axial turbines : model turbine measurements and simulation by a novel numerical method." Thesis, University of Cambridge, 1988. https://www.repository.cam.ac.uk/handle/1810/250922.

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Janse, van Vuuren Gregory. "Extracting blade condition information from the pressure field around a turbine blade." Diss., University of Pretoria, 2019. http://hdl.handle.net/2263/73187.

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Turbine stages are exposed to a variety of excitation sources in the power industry. The resulting forced vibration excitation of the blades may occur near a blade’s natural frequency. Blade vibration is an inevitable, inherent characteristic of turbines as the rotor blades travel through the trailing wakes of the upstream stator blades. Blade vibration can be worsened by other mechanisms such as pitting, corrosion fatigue and stress corrosion cracking commonly experienced in the power industry. Measuring turbine blade vibration allows for condition monitoring of the blades for damage. This is often coupled with finite element models of the blades or with computational fluid dynamic models of the flow field around the blades. These numerical methods, although well-established, lack the complexity of the true multiphysics phenomena within a turbine. As the blade vibration measurement techniques essentially capture blade vibration that is the result of fluid-structure interaction (FSI), blade vibration should be modelled as a coupled problem, but this is usually computationally expensive. A rudimentary yet fundamentally correct numerical model of a turbine stage is thus required to model the fluid-structure interaction while minimising computational costs and retaining accuracy. If this can be achieved and blade health information can be detected in the flow field within the model, further analyses can then be put forth to predict blade health over time. The main objective of this study is to investigate the extent to which blade condition information can be extracted from a transient three-dimensional two-way FSI model of a blade passage containing a single rotor and stator blade. An experimental single-stage test turbine with five stator and five rotor blades is used to gather experimental data. The experimental data is used to validate the FSI model in the time and frequency domains. Two rotor blade assemblies were tested with the first configuration consisting of five healthy blades, and the second configuration consisting of four healthy blades and one damaged blade. All simulations are performed at constant rotational speeds for one single revolution of the rotor. Structural damping of the rotor blades is not considered. All numerical simulations are carried out using the commercial multiphysics software package of Ansys R2 2019 and the explicit use of CFX for the CFD simulations. The results of the FSI model compare well to the experimental results when considering the simplifying assumptions made for the development of the numerical model. The first natural frequency and blade passing frequencies of the healthy and damaged blades can be extracted from the pressure field of the FSI model at critical speeds. Similar findings were observed in the fluid mesh deformation time profiles around the blade tips. Blade excitation is strongly coupled to engine-ordered vibration frequencies, specifically the blade passing frequencies and its first harmonic. Challenges are realised when modelling a single damaged blade that is part of a larger, healthy assembly of rotor blades. The compromise of reducing computational effort is highlighted here. However, very promising results pertaining to blade condition information extraction from the two-way FSI model pressure field are obtained. These results have established a foundation on which a more complex FSI model can be built and coupled with a fatigue or remaining useful life study. It is suggested that future work should include structural damping of the rotor blades, a larger computational domain, and investigation of longer simulation times.
Dissertation (MEng)--University of Pretoria, 2019.
ESKOM
Centre for Asset Integrity Management (C-AIM)
Mechanical and Aeronautical Engineering
MEng
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Books on the topic "Turbine blade"

1

Ghodke, Chaitanya D. Gas Turbine Blade Cooling. Warrendale, PA: SAE International, 2018. http://dx.doi.org/10.4271/0768095069.

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Ghodke, Chaitanya. Gas Turbine Blade Cooling. Warrendale, PA: SAE International, 2018. http://dx.doi.org/10.4271/pt-196.

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Shea, Daniel. Ceramic barrier turbine blade demonstration. Watertown, Massachusetts: U.S.Army Materials Technology Laboratory, 1986.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. Turbine Blade Investment Casting Die Technology. Berlin, Heidelberg: Springer Berlin Heidelberg, 2018. http://dx.doi.org/10.1007/978-3-662-54188-3.

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P, Camperchioli William, López Freyle Isaac, United States. Army Aviation Systems Command., and United States. National Aeronautics and Space Administration., eds. Transonic turbine blade cascade testing facility. [Washington, DC: National Aeronautics and Space Administration, 1992.

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6

Noot, Marc. Numerical analysis of turbine blade cooling ducts. Eindhoven: Eindhoven University, 1997.

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Baumeister, Kenneth J. Unsteady heat transfer in turbine blade ducts. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Martinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.

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Martinez-Sanchez, Manuel. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.

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M, Greitzer Edward, George C. Marshall Space Flight Center., and Massachusetts Institute of Technology, eds. Turbine blade-tip clearance excitation forces: Final report on Contract number NAS8-35018. Cambridge, Mass: Massachusetts Institute of Technology, 1985.

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Book chapters on the topic "Turbine blade"

1

Glocker, Christoph. "Turbine Blade Damper." In Set-Valued Force Laws, 195–203. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-44479-4_14.

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Abo-Serie, Essam, and Elif Oran. "Flow Simulation of a New Horizontal Axis Wind Turbine with Multiple Blades for Low Wind Speed." In Springer Proceedings in Energy, 93–106. Cham: Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-30960-1_10.

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AbstractIn this paper, a new design of a small horizontal-axis wind turbine is introduced. The design is based on the authors’ patent, which uses permanent magnets impeded into a shroud that holds the rotor blades. The generator coils are installed on a fixed diffuser that houses the rotor and acts as a wind concentrator. Therefore, the new design has no hub and is based on direct coupling for electricity generation. The main features of the design have been explored to highlight the advantages with a focus on how the new design can be integrated with the recent development of green buildings. The effect of increasing the number of blades and blade chord distribution on turbine performance has been investigated for the new turbine. Initial design and analysis were carried out using the Blade Element Momentum method and CFD simulations to identify the turbine performance and examine the flow characteristics. The results showed that further energy can be extracted from the turbine if the blade chord size increases at the shroud location and reduces at the turbine hub for a low Tip Speed Ratio TSR within the range of 1.5–3. Furthermore, having more blades can significantly increase the power coefficient and extend the range of operation with a high power coefficient. The number of blades, however, has to be optimised to achieve maximum power relative to the cost. Adding a diffuser and flanges surrounding the turbine can further increase the energy extracted from the wind at low speed.
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Schobeiri, Meinhard T. "Blade Design." In Gas Turbine Design, Components and System Design Integration, 249–76. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-58378-5_9.

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Schobeiri, Meinhard T. "Blade Design." In Gas Turbine Design, Components and System Design Integration, 249–75. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-23973-2_9.

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Malik, Lohit, Gurtej Singh Saini, Mayand Malik, and Abhishek Tevatia. "Sustainability of Wind Turbine Blade." In Handbook of Sustainable Materials: Modelling, Characterization, and Optimization, 399–430. Boca Raton: CRC Press, 2023. http://dx.doi.org/10.1201/9781003297772-20.

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Zhang, Dinghua, Wenhu Wang, Kun Bu, and Yunyong Cheng. "Digitized Modeling Technology of Turbine Blade." In Turbine Blade Investment Casting Die Technology, 21–62. Berlin, Heidelberg: Springer Berlin Heidelberg, 2017. http://dx.doi.org/10.1007/978-3-662-54188-3_2.

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Sirojuddin, Alya Awanis Zahara, and Ragil Sukarno. "Investigation of the Runner Blade Arrangements on a 3-Blade Kaplan Turbine Against Turbine Power." In Recent Advances in Renewable Energy Systems, 97–104. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1581-9_11.

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Bunker, Ronald S. "Blade Tip Aerodynamics and Heat Transfer." In Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics, 351–88. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0351.0388.

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Adiwibowo, Priyo Heru, Soeryanto Soeryanto, Wahyu Dwi Kurniawan, and I. Made Arsana. "Crossflow Hydro Turbine with the Interference Blade Improve Turbine Performance." In Proceedings of the International Joint Conference on Science and Engineering 2022 (IJCSE 2022), 196–202. Dordrecht: Atlantis Press International BV, 2022. http://dx.doi.org/10.2991/978-94-6463-100-5_20.

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Zhang, Dinghua, Yunyong Cheng, Ruisong Jiang, and Neng Wan. "Introduction." In Turbine Blade Investment Casting Die Technology, 1–20. Berlin, Heidelberg: Springer Berlin Heidelberg, 2017. http://dx.doi.org/10.1007/978-3-662-54188-3_1.

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Conference papers on the topic "Turbine blade"

1

Tamai, Ryoji, Ryozo Tanaka, Yoshichika Sato, Karsten Kusterer, Gang Lin, Martin Kemper, and Lars Panning-von Scheidt. "Vibration Analysis of Shrouded Turbine Blades for a 30 MW Gas Turbine." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2014.

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Turbine blades are subjected to high static and dynamic loads. In order to reduce the vibration amplitude means of friction damping devices have been developed, e.g. damping wires, interblade friction dampers and shrouds. This paper presents both numerical and experimental results for investigating the dynamical behavior of shrouded turbine blades. The studies are focused on the lowest family of the bladed disk. The aspect of experimental studies, the effect of the shroud contact force on the resonance frequency of the blade was examined by using the simplified blade test stand. Based on the result of the simplified blade studies, the shroud contact force of the real blade was determined in order to stabilize the resonance frequencies of the bladed disk system. The resonance frequencies and mode shapes of the real bladed disk assembly were measured in no rotation and room temperature condition. Finally, the dynamic strains were measured in the actual engine operations by using a telemetry system. The aspect of analytical studies, a non-linear vibration analysis code named DATES was applied to predict vibration behavior of a shrouded blade model which includes contact friction surfaces. The DATES code is a forced response analysis code that employs a 3-dimensional friction contact model. The Harmonic Balance Method (HBM) is applied to solve resulting nonlinear equations of motion in frequency domain. The simulated results show a good agreement with the experimental results.
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Murthy, Raghavendra, and Marc P. Mignolet. "Decreasing Bladed Disk Response With Dampers on a Few Blades: Part II—Nonlinear and Blade-Blade Dampers Applications." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-69797.

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This two part paper focuses on the optimum placement of a limited number of dampers, i.e. fewer than the number of blades, on a bladed disk to induce the smallest possible amplitude of blade response with or without involuntary, random mistuning. Intentional mistuning is also considered as an option to reduce the amplitude of blade response and the pattern of two blade types (referred to as A and B blades) is then part of the optimization effort in addition to the location of the dampers on the disk. This second part of the investigation focuses on the application of the optimization algorithms developed in Part I to nonlinear dampers, more specifically friction dampers, as well as to the consideration of blade-blade dampers, linear or nonlinear (underplatform dampers). Additionally, the optimization of blade-only and blade-blade linear dampers will be extended to include uncertainty/variability in the damper properties that arise during the manufacturing and/or inservice. It is found that the optimum achieved without considering such uncertainty/variability is robust with respect to it.
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Granovskiy, Andrey, Igor Manaev, Vladimir Vassiliev, and Harald Kissel. "Effects of Blade Degradation on Turbine Performance." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2039.

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The degradation of gas turbine parts due to aging leads to changes in airfoil shape and often causes performance loss. Although the degradation mechanisms and their effects on performance are understood in general (e.g. it is well known that fouling of compressor airfoils reduces mass flow and efficiency), the first quantitative relationships between specific types of part degradation and performance characteristics have only recently been published. In this paper the degradation of turbine blades with aft-loaded airfoils is considered. The typical deviations of shape were identified based on field experience. The effects of these deviations on turbine performance were assessed using different calculation methods, including 3D Navier-Stokes calculations and methods based on empirical correlations. The effect of blades-length reduction, chord-length reduction, changes in trailing-edge thickness and shape, and variation of stagger angle were analysed. The analysis showed that for aft-loaded airfoils without shrouds, the major influence on turbine performance is the degradation of radial clearances. A simplified engineering procedure allowing estimation of turbine performance loss due to degradation has been developed. This paper demonstrates how this simplified procedure, can be applied to the estimation of turbine recovery potential during a typical engine overhaul.
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Széchényi, Edmond. "Fan Blade Flutter: Single Blade Instability or Blade to Blade Coupling?" In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-216.

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Different types of fan blade flutter occur at the various compressor flow regimes. Sub/transonic stall flutter and two forms of supersonic started flow flutter have been studied in a straight cascade wind tunnel. Results show clearly that these three common forms of flutter can exist as single-degree-of-freedom (single-blade instabilities). Cascade effects, though at times important, are never the only flutter mechanism: flutter limits are essentially controlled by single-blade aeroelastic coefficients, though blade-to-blade coupling arising from cascade effects can modify these limits according to the mode order. Thus, contrary to widespread practice, the fundamental approach to flutter problems should lie at least as much in the study of single blade flutter as in that of unsteady cascade effects. The two should anyhow best be considered separately when searching for a better physical insight.
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"ASME Conference Presenter Attendance Policy and Archival Proceedings." In ASME 2013 Turbine Blade Tip Symposium. ASME, 2013. http://dx.doi.org/10.1115/tbts2013-ns.

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Tikhonov, Aleksei S., Andrey A. Shvyrev, and Nikolay Yu Samokhvalov. "Turbine Split Rings Thermal Design Using Conjugate Numerical Simulation." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2003.

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One of the key factors ensuring gas turbine engines (GTE) competitiveness is improvement of life, reliability and fuel efficiency. However fuel efficiency improvement and the required increase of turbine inlet gas temperature (T*g) can result in gas turbine engine life reduction because of hot path components structural properties deterioration. Considering circumferential nonuniformity, local gas temperature T*g can reach 2500 K. Under these conditions the largest attention at designing is paid to reliable cooling of turbine vanes and blades. At present in design practice and scientific publications comparatively little attention is paid to detailed study of turbine split rings thermal condition. At the same time the experience of modern GTE operation shows high possibility of defects occurrence in turbine 1st stage split ring. This work objective is to perform conjugate numerical simulation (gas dynamics + heat transfer) of thermal condition for the turbine 1st stage split ring in a modern GTE. This research main task is to determine the split ring thermal condition by defining the conjugate gas dynamics and heat transfer result in ANSYS CFX 13.0 package. The research subject is the turbine 1st stage split ring. The split ring was simulated together with the cavity of cooling air supply from vanes through the case. Besides turbine 1st stage vanes and blades have been simulated. Patterns of total temperature (T*Max = 2000 °C) and pressure and turbulence level at vanes inlet (19.2 %) have been defined based on results of calculating the 1st stage vanes together with the combustor. The obtained results of numerical simulation are well coherent with various experimental studies (measurements of static pressure and temperature in supply cavity, metallography). Based on the obtained performance of the split ring cooling system and its thermal condition, the split ring design has been considerably modified (one supply cavity has been split into separate cavities, the number and arrangement of perforation holes have been changed etc.). All these made it possible to reduce considerably (by 40…50 °C) the split ring temperature comparing with the initial design. The design practice has been added with the methods which make it possible to define thermal condition of GTE turbine components by conjugating gas dynamics and heat transfer problems and this fact will allow to improve the designing level substantially and to consider the influence of different factors on aerodynamics and thermal state of turbine components in an integrated programming and computing suite.
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7

Mamaev, B. I., M. M. Petukhovsky, and A. V. Pozdnyakov. "Shrouding the First Blade of High Temperature Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2001.

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Blade shrouding gives an opportunity to increase the HPT (high pressure turbine) first stage efficiency by 2–3 %. However, if high gas temperature and high circumferential velocity are at the stage, shrouding can be problematic due to load increasing at blade/disk attachment and high temperature of the shroud itself. To make blade/disk attachment more reliable the shroud axial width has to be decreased by increasing a relative pitch of airfoil cascades t (t = t / b, where t – pitch, b – chord) at the blade tip span. According to experience for a flow with β1 = 50 – 85°, M2 = 0.8 – 1, and Re = (0.8 – 1)•106 high efficient cascades with t = 0.93 – 1.05 can be designed. Application of such a profiling for GTE (gas turbine engine) turbine is demonstrated here. In the turbine meridian flow path the blade was drastically tapered to the tip (tip width was 53 % of the mean width and 46 % of the hub width). To lighten the blade a partial shrouding can be also applied. Model turbine tests showed that local cuts at the front shroud area and the aft shroud area at the airfoil pressure side influenced the efficiency weakly. Required shroud temperature is provided with a cooling. The aircraft turbine with a governed cooling system and a radial clearance control is an example here. In this case the shroud had 3 labyrinth ribs. The shrouding decreased radial clearance by 0.8 mm at main design modes that increased efficiency by ∼ 1.5 %. To cool down the shroud the air downstream the compressor was fed into the cavity behind the front labyrinth rib. At maximal mode with full cooling the relative coolant mass flow (to the compressor mass flow) was mc = 1.3 % and gas leakages through the labyrinth were 0.2 %. It gave acceptable mixed temperature of 530°C in the cavity over the shroud. At cruise high altitude mode and a lower gas temperature and partial cooling with mc = 0.4 % and gas leakages of 0.1 % the mixed temperature also did not exceed 530°C over the shroud. The assessment with taking into account changes of the clearance, the coolant mass flow, and gas leakages showed that the shrouding provided the engine economy improvement by 0.7 – 0.9 % for both modes. For GTPU (gas turbine power unit) the first blade shrouding can be more complicated. However, even the slight turbine efficiency increase provides considerable profits due to GTPU huge power output and long term running. So, when GTE and GTPU designing starts, it is reasonable to consider the turbine first blade shrouding. Here the integral evaluation criterion, which includes the assessment of a possible income from the unit full life cycle running, has to be applied.
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8

Ledezma, G. A., J. Allen, and R. S. Bunker. "An Experimental and Numerical Investigation Into the Effects of Squealer Blade Tip Modifications on Aerodynamic Performance." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2004.

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Gas turbine blades using the so-called squealer tip configuration represent a majority of the high-pressure first stage blades in service. The squealer tip in its most basic format is simply a two-tooth labyrinth seal projecting from the blade tip towards the stationary shroud or casing. As with all blade tip configurations, the geometry is a compromise between aerodynamics, cooling, mechanical stress, durability, and repair. While many proposed blade tip innovations involve more complex geometries, this study seeks to determine if a simpler geometry, other than a flat tip, can provide equivalent aerodynamic performance with a reasonable chance of satisfying all other design factors. Using an annular sector blade cascade, total pressure loss surveys are measured with three blade tip geometries, the standard squealer tip, a single-sided suction side seal strip, and the single-sided strip with a pressure side winglet added. The same cascade is modeled numerically as a periodic passage for each of the geometries tested. Experiment and simulation both utilize all blade tip cooling flow injection locations and nominal magnitudes, as well as a constant tip clearance above the suction side seal strip. Experimental data show that the removal of the pressure side seal strip reduces the area-averaged total pressure loss slightly, while the addition of a winglet returns the performance to the baseline result. Numerical predictions indicate essentially equal performance for all geometries. The numerical results provide insight into the loss mechanisms of both the tip leakage flows and the coolant injection flows. This study, when combined with literature data on heat transfer and cooling, concludes that the simpler single-sided suction seal strip is better overall than the commonly employed squealer tip.
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Bachschmid, Nicolò, Emanuel Pesatori, Simone Bistolfi, and Massimiliano Sanvito. "Building Up Suitable Contact Forces in Integrally Shrouded Blade Rows for Reducing Vibration Amplitudes." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2005.

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The beneficial effects of the contact between shrouds are described extensively in recent literature: natural blade frequencies are increased and additional damping is available. Different models are proposed for analyzing its linear and nonlinear behavior, selection of optimum contact forces are proposed for reducing vibration amplitudes to a minimum. Results from different non linear analyses that use different models all based generally on a reduced modal model of the blade row and on the harmonic balance approach for modeling the non linear contact forces, are sometimes contradictory: some claim e.g. that increasing excitation amplitude leads to a reduction of the dynamic magnification factor (due to friction damping increase) some other claim the opposite. The contribution to this topic of the present paper is the analysis of the effect of a “contact shim” which can be inserted in a cavity between adjacent shrouds. The shim generates suitable contact forces between the shrouds of the blades of a row, which without shim would vibrate as free standing blades.
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Yan, Xin, Lijie Lei, Jun Li, and Zhenping Feng. "Effect of Bending and Mushrooming Damages on Heat Transfer Characteristic in Labyrinth Seals." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2012.

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Using conjugate heat transfer calculations, the heat transfer in straight-through labyrinth seals with and without rub damages (bending and mushrooming damages) were numerically investigated. Firstly, the numerical methods were carefully validated on the basis of obtained experimental data. At two different sealing clearances and a range of Reynolds numbers, Nu distributions on the seal rotor and stator surfaces for the original design cases were numerically computed and compared to the experimental data. The temperature fields in the fluid and inside the solid domains were obtained to account for the heat transfers between fluid and adjacent solids. Then, a range of bending angles, wear-off ratios and mushrooming radiuses were selected to investigate the influence of rub damages on heat transfer characteristic in the labyrinth seals, and the numerical results were also compared to that of original design cases. The results show that the calculated Nu distributions are in good agreement with the experimental data at a range of Re numbers and different sealing clearances. The turbulence model has pronounced effect on the heat transfer computations for the labyrinth seal. Among the selected eddy viscosity turbulence models, the low-Re k-ω and SST turbulence models show superior accuracy to the standard k-ε and RNG k-ε turbulence models, which over-predict Nu by about 70%. Bending damage reduces Nu on the labyrinth fin whereas enhances heat transfer on the opposite smooth stator. The effect of bending angle on Nu distribution on the seal stator surface is larger than on the rotor surface. The mushrooming damage has pronounced effect on Nu distributions on both rotor and stator surfaces for the labyrinth seal. It shows that Nu distributions on the rotor and stator surfaces decreases with the increase of mushrooming radius, but increases with the increase of wear-off ratio and Re.
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Reports on the topic "Turbine blade"

1

Bernstein. L51797 Life Management of the RB211-24C Gas Turbine. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), December 1998. http://dx.doi.org/10.55274/r0010427.

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Gas turbine engines are in common use in the Gas Pipeline industry to drive gas compressors in compression facilities. One of the major cost factors in the operation of these turbines is the repair or replacement of the hot section components. Technology that can extend the operational life of these components, or increase the ability to repair these components, is of immediate financial and operational benefit to members of PRCI. The RB211 gas turbine engine is commonly used in compression facilities. The life of the model 24C HP turbine blades is currently inadequate, leading to early replacement at a cost of approximately $300,000 per set. Actual life is not known by the users (or the OEM) and existing estimates are unreliable. Since users do not have adequate means to predict the point at which the blades must be retired, this study of the RB211-24C HP blade life factors was initiated to provide users with guidance for blade maintenance. The objectives of the project were to define the life factors affecting the repair and replacement decisions for the RB211-24C HP turbine blades. This includes determining the operative degradation modes of these turbine blades; the expected life of these blades as a function of engine operation; the potential to repair these blades, and the potential to obtain additional life and durability of the blades by the use of more protective coatings.
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2

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

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3

Smith, Kevin J., and Dayton A. Griffin. Supersized Wind Turbine Blade Study: R&D Pathways for Supersized Wind Turbine Blades. Office of Scientific and Technical Information (OSTI), March 2019. http://dx.doi.org/10.2172/1498695.

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4

Cao, Yiding. An Innovative Turbine Blade Cooling Technology and Micro/Miniature Heat Pipes for Turbine Blades. Fort Belvoir, VA: Defense Technical Information Center, July 2000. http://dx.doi.org/10.21236/ada381455.

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5

Korjack, T. A. A Twisted Turbine Blade Analysis for a Gas Turbine Engine. Fort Belvoir, VA: Defense Technical Information Center, August 1997. http://dx.doi.org/10.21236/ada329581.

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6

Gage, Bill, Ryan Beach, and Scott Hughes. Laboratory Wind Turbine Blade Static Testing of the Sandia National Rotor Testbed 13-Meter Wind Turbine Blade. Office of Scientific and Technical Information (OSTI), September 2021. http://dx.doi.org/10.2172/1823763.

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7

ASHWILL, THOMAS D. Parametric Study for Large Wind Turbine Blades: WindPACT Blade System Design Studies. Office of Scientific and Technical Information (OSTI), August 2002. http://dx.doi.org/10.2172/801402.

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8

Bortolotti, Pietro, Derek S. Berry, Robynne Murray, Evan Gaertner, Dale S. Jenne, Rick R. Damiani, Garrett E. Barter, and Katherine L. Dykes. A Detailed Wind Turbine Blade Cost Model. Office of Scientific and Technical Information (OSTI), June 2019. http://dx.doi.org/10.2172/1529217.

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9

Gutman, M. J. Turbine Blade Data Acquisition System Technical Reference. Fort Belvoir, VA: Defense Technical Information Center, May 1989. http://dx.doi.org/10.21236/ada215135.

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10

Luttges, Marvin W., Mark S. Miller, Michael C. Robinson, Derek E. Shipley, and Teresa S. Young. Wind Turbine Blade Aerodynamics: The Combined Experiment. Office of Scientific and Technical Information (OSTI), August 1994. http://dx.doi.org/10.2172/10177824.

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