Relevant bibliographies by topics / Blade root Joint

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Academic literature on the topic 'Blade root Joint'

Author: Grafiati
Published: 14 March 2023

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Journal articles on the topic "Blade root Joint"

1

Mishnaevsky, Leon. "Root Causes and Mechanisms of Failure of Wind Turbine Blades: Overview." Materials 15, no. 9 (April 19, 2022): 2959. http://dx.doi.org/10.3390/ma15092959.

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A review of the root causes and mechanisms of damage and failure to wind turbine blades is presented in this paper. In particular, the mechanisms of leading edge erosion, adhesive joint degradation, trailing edge failure, buckling and blade collapse phenomena are considered. Methods of investigation of different damage mechanisms are reviewed, including full scale testing, post-mortem analysis, incident reports, computational simulations and sub-component testing. The most endangered regions of blades include the protruding parts (tip, leading edges), tapered and transitional areas and bond lines/adhesives. Computational models of different blade damage mechanisms are discussed. The role of manufacturing defects (voids, debonding, waviness, other deviations) for the failure mechanisms of wind turbine blades is highlighted. It is concluded that the strength and durability of wind turbine blades is controlled to a large degree by the strength of adhesive joints, interfaces and thin layers (interlaminar layers, adhesives) in the blade. Possible solutions to mitigate various blade damage mechanisms are discussed.
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Allara, Marco, Stefano Zucca, and Muzio M. Gola. "Effect of Crowning of Dovetail Joints on Turbine Blade Root Damping." Key Engineering Materials 347 (September 2007): 317–22. http://dx.doi.org/10.4028/www.scientific.net/kem.347.317.

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Stresses due to resonant vibrations induce fatigue damage in turbomachinery blades jeopardizing their structural integrity. Damping plays a fundamental role in passive control of resonant stresses. In the present work the effect of ‘crowning’ of dovetail joints on blade-root friction damping is for the first time investigated. In detail, the damping of a simplified blade is measured under varying centrifugal load for two different joint geometries: a customary dovetail attachment and a ‘crowned’ one. A theoretical model is developed to quantify the damping generated at the contact surfaces. Experimental results and analytical predictions are compared.
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Ha, Kwangtae. "Reduction of Stress Concentration Factor (SCF) on the Bolted Joint Connection for a Large Wind Turbine Rotor Blade through Various Design Modifications." Applied Sciences 10, no. 18 (September 21, 2020): 6588. http://dx.doi.org/10.3390/app10186588.

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The importance of a reliable blade root connection has grown due to the higher-gravity-induced edgewise loads on the blade root that resulted from the recent increased size and weight of a wind turbine rotor blade. To avoid the loosening of a bolt joint connection or even consecutive blade failures, the stress concentration factor (SCF) at the bolt thread root that is sensitive to fatigue should be understood comprehensively. In this work, two-dimensional and three-dimensional finite element (FE) analysis methods were used to determine the SCF at the bolt threads both between an insert and a M42 bolt used for a large offshore blade, and between a M42 bolt and a nut. The effect of various geometric parameters on the SCF were also investigated, which included shank diameter, nut height, nut type, and relief cone. Results showed that the decreased diameter of a M42 bolt shank diameter was the dominant design driver in reducing the stress concentration factor by 40%, from 3.94 to 2.32. The round nut type was also a recommended factor to be implemented to connect bolts and inner pitch bearing with an additional 10% SCF reduction. The relief cones applied to bolt threads and insert threads also contributed to the reduction of SCF to 2.01, a 49% reduction in total. This work not only provides guidelines by which to choose the proper geometry of the bolt and nut for a large blade, but also could be beneficial in designing bolted joint connections of segment or modular blades.
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Yu Pechenina, Ekaterina, Vadim A. Pechenin, and Michael A. Bolotov. "Development of the compressor impeller configuration algorithm." Journal of Physics: Conference Series 2373, no. 6 (December 1, 2022): 062021. http://dx.doi.org/10.1088/1742-6596/2373/6/062021.

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Abstract The article addresses the improvement of compressor impeller configuration methods. One of the key parameters of compressor blade assembly quality is the uniform tension in the blade shroud joint. The authors have developed an algorithm for arranging the blades in the compressor impeller, which allows reducing the tension and ensures its uniform distribution. The algorithm kernel is based on a mathematical model developed for calculating shroud tension areas on the suction side and pressure side based on controlled deviations of the airfoil and shroud. The computed areas are used to sort the blades by the increasing tension area on the suction side and the decreasing one on the pressure side. At the final stage, the blades are arranged by their successive choice from among two rows and each next blade from the rows is installed in the casing, next to the pre-installed blades, with the change in the bypass direction. The algorithm is written in Python; 1,000 computing experiments were made to simulate the deviation of the parameters for 84 blades in the set. The algorithm function was compared to the arbitrary arrangement of the blades. As a result, the root-mean-square deviation of the originating tensions decreased from 0.54 mm2 to 132 mm2.
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Pechenina, Ekaterina, Mikhail Bolotov, and Vadim Pechenin. "DEVELOPMENT OF THE COMPRESSOR IMPELLER CONFIGURATION ALGORITHM." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 69 (2022): 14–22. http://dx.doi.org/10.15593/2224-9982/2022.69.02.

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The article addresses the improvement of compressor impeller configuration methods. One of the key parameters of compressor blade assembly quality is the uniform tension in the blade shroud joint. The authors have developed an algorithm for arranging the blades in the compressor impeller, which allows reducing the tension and ensures its uniform distribution. The algorithm kernel is based on a mathematical model developed for calculating shroud tension areas on the suction side and pressure side based on controlled deviations of the airfoil and shroud. The computed areas are used to sort the blades by the increasing tension area on the suction side and the decreasing one on the pressure side. At the final stage, the blades are ar-ranged by their successive choice from among two rows and each next blade from the rows is installed in the casing, next to the pre-installed blades, with the change in the bypass direction. The algorithm is written in Python; 1,000 computing experiments were made to simulate the deviation of the parameters for 84 blades in the set. The algorithm function was compared to the arbitrary arrangement of the blades. As a result, the root-mean-square deviation of the originating tensions decreased from 0.54 mm2 to 0.132 mm2.
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6

Zhang, Desheng, Dazhi Pan, Yan Xu, Peipei Shao, and Guotao Wang. "Numerical investigation of blade dynamic characteristics in an axial flow pump." Thermal Science 17, no. 5 (2013): 1511–14. http://dx.doi.org/10.2298/tsci1305511z.

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The unsteady numerical simulation of fluid field and structural transient dynamic analysis of axial flow pump were carried out at three operating conditions based on fluid-structure interaction method. Numerical results show that the maximum equivalent stress of impeller occurs at the joint region of the impeller blade root and the hub, and the maximum deformation of impeller occurs at the tips of blade leading edges. The frequency-domain of the maximum equivalent stress and outlet pressure fluctuation of impeller are mainly affected by the impeller blade passing frequency.
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Li, Chaofeng, Zengchuang Shen, Zilin Chen, and Houxin She. "A study on the vibration dissipation mechanism of the rotating blade with dovetail joint." Journal of Low Frequency Noise, Vibration and Active Control 40, no. 3 (January 12, 2021): 1271–92. http://dx.doi.org/10.1177/1461348420985339.

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The vibration dissipation mechanism of the rotating blade with a dovetail joint is studied in this paper. Dry friction damping plays an indispensable role in the direction of vibration reduction. The vibration level is reduced by consuming the total energy of the turbine blade with the dry friction device on the blade-root in the paper. The mechanism of the vibration reduction is revealed by the variation of the friction force and the energy dissipation ratio of dry friction. In this paper, the flexible blade with a dovetail interface feature is discretized by using the spatial beam element based on the finite element theory. Then the classical Coulomb-spring friction model is introduced to obtain the dry friction model on the contact interfaces of the tenon-mortise structure. What is more, the effects of the system parameters (such as the rotating speed, the friction coefficient, the installation angle of the tenon) and the excitation level on blade damping characteristics are discussed, respectively. The results show that the variation of the system parameters leads to a significant change of damping characteristics of the blade. The variation of the tangential stiffness and the position of the external excitation will affect the nonlinear characteristics and vibration damping characteristics.
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Hosseini-Toudeshky, H., M. Jahanmardi, and M. S. Goodarzi. "Progressive debonding analysis of composite blade root joint of wind turbines under fatigue loading." Composite Structures 120 (February 2015): 417–27. http://dx.doi.org/10.1016/j.compstruct.2014.10.025.

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9

Liu, Haoming, Suxiang Yang, Wei Tian, Min Zhao, Xiaoling Yuan, and Bofeng Xu. "Vibration Reduction Strategy for Offshore Wind Turbines." Applied Sciences 10, no. 17 (September 2, 2020): 6091. http://dx.doi.org/10.3390/app10176091.

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The operational environment of offshore wind turbines is much more complex than that of onshore wind turbines. Facing the persistent wind and wave forces, offshore wind turbines are prone to vibration problems, which are not conducive to their long-term operation. Under this background, first, how the wave affects the vibration characteristics of offshore wind turbines is analyzed. Based on the existing wave and wave load models, we analytically show that there exist fluctuating components related to the hydrodynamic frequency in the aerodynamic load and aerodynamic torque of offshore wind turbines. Simulation results based on a GH Bladed platform further validates the analysis. Second, in order to reduce the joint impacts of the wave, wind shear and tower shadow on the wind turbine, a variable pitch control method is proposed. The integrated tower top vibration acceleration signal is superimposed on the collective pitch reference signal, then the triple frequency (3P) fluctuating component of the wind turbine output power and the azimuth angle of each blade are converted into the pitch angle adjustment signal of each blade, which is superimposed on the collective pitch signal for individual pitch control. The simulation results show that the proposed pitch control strategy can effectively smooth the fluctuation of blade root flap-wise load caused by wind and wave, and significantly reduce the fluctuation of aerodynamic torque and output power of offshore wind turbines.
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Salimi-Majd, Davood, Vahid Azimzadeh, and Bijan Mohammadi. "Loading Analysis of Composite Wind Turbine Blade for Fatigue Life Prediction of Adhesively Bonded Root Joint." Applied Composite Materials 22, no. 3 (July 6, 2014): 269–87. http://dx.doi.org/10.1007/s10443-014-9405-4.

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Book chapters on the topic "Blade root Joint"

1

Allara, Marco, Stefano Zucca, and Muzio M. Gola. "Effect of Crowning of Dovetail Joints on Turbine Blade Root Damping." In Damage Assessment of Structures VII, 317–22. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-444-8.317.

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Alarcón Cabana, Daniel J., Jie Yuan, and Christoph W. Schwingshackl. "A Novel Test Rig for the Validation of Non-linear Friction Contact Parameters of Turbine Blade Root Joints." In Nonlinear Structures & Systems, Volume 1, 215–26. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-031-04086-3_29.

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Conference papers on the topic "Blade root Joint"

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Koscso, Adam, and E. P. Petrov. "Blade Root Joint Modelling and Analysis of Effects of Their Geometry Variability on the Nonlinear Forced Response of Tuned and Mistuned Bladed Disks." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15225.

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Abstract One of the major sources of the damping of the forced vibration for bladed disk structures is the micro-slip motion at the contact interfaces of blade-disk joints. In this paper, the modeling strategies of nonlinear contact interactions at blade roots are examined using high-fidelity modelling of bladed disk assemblies and the nonlinear contact interactions at blade-disk contact patches. The analysis is performed in the frequency domain using multiharmonic harmonic balance method and analytically formulated node-to-node contact elements modelling frictional and gap nonlinear interactions. The effect of the number, location and distribution of nonlinear contact elements are analyzed using cyclically symmetric bladed disks. The possibility of using the number of the contact elements noticeably smaller than the total number of nodes in the finite element mesh created at the contact interface for the high-fidelity bladed disk model is demonstrated. The parameters for the modeling of the root damping are analysed for tuned and mistuned bladed disks. The geometric shapes of blade roots and corresponding slots in disks cannot be manufactured perfectly and there is inevitable root joint geometry variability within the manufacturing tolerances. Based on these tolerances, the extreme cases of the geometry variation are defined and the assessment of the possible effects of the root geometry variation on the nonlinear forced response are performed based on a set of these extreme cases.
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Chen, Junjie, Chaoping Zang, Biao Zhou, and E. P. Petrov. "Analysis of Nonlinear Modal Damping due to Friction at Blade Roots in Mistuned Bladed Discs." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16029.

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Abstract A method is proposed to analyse the modal damping in mistuned bladed-disc with root joints using large finite element models and the detailed description of frictional interactions at contact interfaces. The influence of mistuning on the dissipated energy for different blades on a bladed-disc and the modal damping factors for different vibration levels for any family of modes can be investigated. The dissipated energy and damping factors due to micro-slip are simulated by multitude of surface-to-surface elements modelling the friction contact interactions at root joints. The analysis is performed in the time domain and an original reduction method is developed to obtain the results with acceptable computational times. The model reduction method allows the calculation of the modal damping of the mistuned assembly by evaluation of the energy dissipated at root joint of each individual blade using small parts of bladed disc sectors. The dependency of modal damping factor on blade mode shapes, engine-order excitation numbers, nodal diameter numbers and vibration amplitudes are studied and the distributions of amplitude and dissipated energy on the mistuned bladed-disc are investigated using a realistic blade disc model.
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Kubiak S., J., G. Gonzalez R., D. Jua´rez R., J. Nebradt G., and F. Sierra E. "Failure Analysis of the L-0 Steam Turbine Blade." In International Joint Power Generation Conference collocated with TurboExpo 2003. ASMEDC, 2003. http://dx.doi.org/10.1115/ijpgc2003-40056.

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The main objective of the paper is to present an analysis that leads to detect the most possible cause of the L-0 blade fracture. Recently, several L-0 blades 28.5 inches long of a steam turbine have fractured. The fracture appeared 5 inches from the blade root platform, Fig. 1-“C”, causing the forced outage of the turbine. Previously, in the beginning of the last decade a finite element analysis of the blade was carried out calculating the natural frequencies and the vibratory stresses, and also, a telemetry test was carried out on these blades. These were published several years ago [1]. The analysis results gathered then were very precious to find a root cause of the present failure. To find out the causes of the blade fracture the following activities were carried out: analysis of the operational data during the last two years, analysis of the previous investigations, metallurgical investigations, identification of the mechanical and metallurgical modes of the failure. Apart from that, the turbine was overloaded by certain period of time. In this paper the results of the investigations indicated a miswelding process of the stubs as a principal cause of the blade fracture.
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Maeda, Takao, Yasunari Kamada, Keita Naito, Yuu Ouchi, and Masayoshi Kozawa. "Measurement of Unsteady Aerodynamics Load on the Blade of Field Horizontal Axis Wind Turbine." In ASME/JSME 2007 5th Joint Fluids Engineering Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/fedsm2007-37448.

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This paper describes an experimental field study of the rotor aerodynamics of wind turbines. The test wind turbine is a horizontal axis wind turbine, or: HAWT with a diameter of 10m. The pressure distributions on the rotating blade are measured with multi point pressure transducers. Sectional aerodynamic forces are analyzed from pressure distribution. Blade root moments are measured simultaneously by a pair of strain gauges. The inflow wind is measured by a three component sonic anemometer, the local inflow of the blade section are measured by a pair of 7 hole Pitot tubes. The relation between the aerodynamic moments on the blade root from pressure distribution and the mechanical moment from strain gauges is discussed. The aerodynamic moments are estimated from the sectional aerodynamic forces and show oscillation caused by local wind speed and direction change. The mechanical moment shows similar oscillation to the aerodynamic excepting the short period oscillation of the blade first mode frequency. The fluctuation of the sectional aerodynamic force triggers resonant blade oscillations. Where stall is present along the blade section, the blade’s first mode frequency is dominant. Without stall, the rotating frequency is dominant in the blade root moment.
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Gonza´lez, Jon Plaza, Francisco Javier Echarte Casquero, Javier Va´zquez Mato, and Miguel A´ngel Gonza´lez-Posada. "Blade Bearing Friction and Fatigue Mathematical Mode." In STLE/ASME 2008 International Joint Tribology Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/ijtc2008-71147.

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Modern Wind Turbines adjust their blades orientation at different wind speeds for power control and optimum energy production. A big slewing ring about 2 metres diameter placed at each blade root, allows the blade orientation withstanding highly variable heavy loads, vibrations, continuous rotating oscillations and severe ambient conditions. The blade pitch system design and control strategy in a WTG is strongly conditioned by the load dependant friction of the bearing that shall be accurately defined for cost-effective designs. The pitch system is also the main brake of the rotor requiring high reliability for their components under fatigue loads, and in particular for the slewing rings due to its inherent difficulties for maintenance or replacement. The present methodology allows the fatigue and friction estimation of slewing rings, based on rolling bearing models and classical theories like Hertz, Lundberg-Palmgren, and Miner fatigue cumulative damage. This approach simulates the stress supported by each ball in the contact with the raceways, estimates the bearing friction due to these contact stresses, and the fatigue life of the overall bearing.
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Liu, Guangmao, Donghai Jin, Mengyu Wang, and Xingmin Gui. "Numerical and Experimental Investigation on the Influence of Blades Gap Flow on Axial Blood Pump Performance." In ASME-JSME-KSME 2019 8th Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ajkfluids2019-5665.

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Abstract The axial blood pump body primarily contains the Inlet Guide Vane (IGV), Rotor Impeller (RI), Outlet Guide Vane (OGV) and pump casing. There must be gaps between rotor blade tip and pump casing or between OGV blade root and rotor hub for the impeller rotating in the pump. The flow characteristics inside an axial blood pump with different blade gaps were numerically simulated and analyzed. Hydraulics experiments were conducted to verify the numerical results. The results show that the pump efficiency decreased slowly when the OGV blade gap increased from 0.1 mm to 0.3 mm, but quickly when the rotor blade gap increased from 0.1 mm to 0.3 mm. The hydraulics characteristic results indicate that the pressure rise and efficiency are mainly influenced by the rotor blade gap. The OGV blade root gaps have little influence on the decrease of pressure rise and efficiency. The novel configuration with uneven blade gaps inside the pump result in improved hydraulics and hemolytic performance compared with the similarly sized configuration with even blade gaps.
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Chang, Yin-han, Kazuyuki Toda, and Makoto Yamamoto. "Computation of Turbulent Flow Around Blade With Local Surface Roughness." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45523.

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To improve aerodynamic performance of a blade and to maintain its designed performance, many study have been focused on this point. The factors for aerodynamic performances of a blade are its geometry and operating conditions, which are almost fixed during its lifetime. On the other hand, the factor such as surface roughness generated by impure sand grain or oil droplet is variable one. The surface roughness on the blade affects the flow past it by its aerodynamic nature. The blade design can be improved by revealing this change in aerodynamic performance due to surface roughness. In this study, three-dimensional computations are carried out on the blade root with local surface roughness to investigate how the roughness will change the aerodynamic performance. The locality of the surface roughness distribution is simulated with particle tracks in three-dimensional flow. The model replacing the effect of roughness elements with virtual force is used to simulate turbulent flow around blade with local surface roughness.
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Joosse, P. A., D. R. V. van Delft, Chr Kensche, D. Soendergaard, R. M. van den Berg, and F. Hagg. "Cost Effective Large Blade Components by Using Carbon Fibres." In ASME 2002 Wind Energy Symposium. ASMEDC, 2002. http://dx.doi.org/10.1115/wind2002-27.

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Due to the increasing size of wind turbine rotors, especially for offshore wind turbines, the power output and the blade mass are becoming more important. A new type of cheaper carbon fibres is expected to result in a lower blade mass and marginally cheaper blades. In a Joule-funded project, the possibilities for economic use of carbon fibres is determined by establishing material design data, analysing production methods, developing cost-effective blade root joints and assessing blade and turbine costs. The R&D project will be finalised by the end of 2001. Up to now, production processes and promising material combinations have been reviewed, tested and ranked. Basic material design data have been established for the two most-promising material combinations. Due to disappointing fatigue results on Panex/VE, additional testing on four large-tow laminates was performed. The fatigue properties of these showed to be consistent. Later testing on a similar Panex/epoxy laminate, however, revealed much better fatigue behaviour. Joint development and cost assessment are underway and show promising results.
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Lampart, Piotr. "Numerical Optimization of Stator Blade Sweep and Lean in an LP Turbine Stage." In 2002 International Joint Power Generation Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/ijpgc2002-26161.

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The paper describes results of direct constrained optimization of stator blade axial sweep and circumferential lean for the exit stage of a large power steam turbine, using Nelder-Mead’s method of deformed polyhedron. Values of the minimised objective function, that is stage losses with the exit energy are found from 3D viscous compressible computations. Turbulence effects are taken into account using Menter’s SST model. Among the optimized parameters are stator and rotor stagger angles, stator straight sweep and straight lean, stator compound sweep at the tip and compound lean at the root, giving the total number of 8 optimized parameters. The blade sections (profiles) are assumed not to change during the optimization. There are constraints imposed on the mass flow rate, exit swirl angle and reactions. A number of optimization runs is reported. First, optimization of the exit stage with stator blade circumferential lean, second, optimization of the stage with stator blade axial sweep, then, the stage is optimized with both sweep and lean of stator blades. In the above tasks, the process of optimization is carried out for a nominal load, however, due to the fact that exit stages of steam turbines operate over a wide range of flow rates away from the nominal conditions, the original and final geometries are also checked for low and high loads. Optimization gives designs with new 3D stacking lines of stator blades, and with significantly increased efficiencies, over large part of the assumed range of load, compared to the original design.
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Wang, Z. Q., L. Q. An, and Z. Z. Peng. "A Probabilistic Analysis for Static and Dynamic Frequency of Blade With Uncertain Boundary Conditions." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84185.

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A probabilistic analysis method is developed for frequencies analysis of turbine blade with uncertain boundary condition at the root of blade. The Ritz method is used to derive the eigenvalues equation of the rotating blade with uncertain root boundary condition. The matrix perturbation technique is employed for the probabilistic analysis to obtain the deterministic part of natural frequencies and vibration modes, the sensitivity matrix, the covariance matrix and the coefficient of variance (COV) for the natural frequencies. The effects of variations in the expectation and the variance of joint stiffness on the expectation and the variance of the natural frequencies are investigated.
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