Relevant bibliographies by topics / Blade Loading

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Blade Loading'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "Blade Loading"

1

Etuk, E. M., A. E. Ikpe, and U. A. Adoh. "Design and analysis of displacement models for modular horizontal wind turbine blade structure." Nigerian Journal of Technology 39, no. 1 (April 3, 2020): 121–30. http://dx.doi.org/10.4314/njt.v39i1.13.

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This study examined the normal, radial, axial and tangential loading cycles undergone by wind turbine rotor blades and their effects on the displacement of the blade structure. The rotor blade was modelled using Q Blade finite element sub module, which evaluated the loading cycles in terms of the forces induced on the blade at various frequencies through several complete revolution cycles (360o each cycle). At frequencies of 5 HZ, 23 Hz, 60 Hz, 124 Hz and 200 Hz, maximum strain deformation of 0.004, 0.04, 0.08, 0.14 and 0.24 were obtained, and geometry of the deformed blades were characterized by twisting and bending configuration. Maximum deflections from tangential loading increased from -0.55-1.2 mm, -0.39-1.6 mm from axial loading, -0.28-1.8 mmfrom radial loading and -0.01-2.3 mm from normal loading. From these deflection values, normal loading cycle would cause the highest level of structural damage on the rotor blade followed by radial, axial and tangential loading. Moreover, the strain deformations and deflections of the blade structure increased as the cycles of frequency increased. Keywords: Loading cycle, Wind turbine, Rotor blade, Frequency, Strain deformations, Deflections.
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Hesse, Nicholas H., and J. H. G. Howard. "Experimental Investigation of Blade Loading Effects at Design Flow in Rotating Passages of Centrifugal Impellers." Journal of Fluids Engineering 121, no. 4 (December 1, 1999): 813–23. http://dx.doi.org/10.1115/1.2823542.

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Laser-Doppler Anemometry (LDA) was used to study the effect of blade loading on the relative velocity field in a rotating passage of a centrifugal-pump impeller. Two variations of the impeller, 8-bladed and 16-bladed, were investigated. The measured primary and secondary velocities and turbulence show that the effect of blade loading is not that previously predicted. The 16-blade impeller with high blade loading has a rapidly thickening suction side boundary layer, suggesting the onset of transient separation near the exit. However, for the 8-blade impeller with even higher blade loading, the onset of separation is not indicated at any measured location in the impeller. At the design flow, it is concluded that the stronger potential eddy and lower solidity associated with the very high blade loading caused a change in the secondary flow pattern, retarding the growth and the likelihood of transitory separation of the suction side boundary layer.
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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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Tripp, Nicolás G., Aníbal E. Mirasso, and Sergio Preidikman. "Numerical analysis of the influence of inertial loading over morphing trailing edge devices." Journal of Intelligent Material Systems and Structures 29, no. 18 (June 28, 2018): 3533–49. http://dx.doi.org/10.1177/1045389x18783867.

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Larger and more flexible wind turbine blades are currently being manufactured. Those highly flexible blades suffer from loading of aeroelastic nature which increases the fatigue damage. Smart blade concepts are being developed to reduce the aerodynamic loading. The state of the art favors the discrete deformable trailing edge concept. Many authors have reported adequate performance of this type of actuators in reducing the blade vibrations. However, the question of whether the actuator can maintain its authority under strong external loading remains still answered. To solve this question, actuator models that include the loading produced by the blade vibration are required. In this article, a smart morphing trailing edge model is presented that includes the inertial forces produced by the blade dynamics. The model is applied to a commercial actuator and the influence of its parameters is analyzed. Finally, a simple estimation of the inertial loading produced by a 35-m wind turbine blade at the flutter instability condition is analyzed to understand the design requirements of this type of systems.
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Zalkind, Daniel S., Gavin K. Ananda, Mayank Chetan, Dana P. Martin, Christopher J. Bay, Kathryn E. Johnson, Eric Loth, D. Todd Griffith, Michael S. Selig, and Lucy Y. Pao. "System-level design studies for large rotors." Wind Energy Science 4, no. 4 (November 11, 2019): 595–618. http://dx.doi.org/10.5194/wes-4-595-2019.

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Abstract. We examine the effect of rotor design choices on the power capture and structural loading of each major wind turbine component. A harmonic model for structural loading is derived from simulations using the National Renewable Energy Laboratory (NREL) aeroelastic code FAST to reduce computational expense while evaluating design trade-offs for rotors with radii greater than 100 m. Design studies are performed, which focus on blade aerodynamic and structural parameters as well as different hub configurations and nacelle placements atop the tower. The effects of tower design and closed-loop control are also analyzed. Design loads are calculated according to the IEC design standards and used to create a mapping from the harmonic model of the loads and quantify the uncertainty of the transformation. Our design studies highlight both industry trends and innovative designs: we progress from a conventional, upwind, three-bladed rotor to a rotor with longer, more slender blades that is downwind and two-bladed. For a 13 MW design, we show that increasing the blade length by 25 m, while decreasing the induction factor of the rotor, increases annual energy capture by 11 % while constraining peak blade loads. A downwind, two-bladed rotor design is analyzed, with a focus on its ability to reduce peak blade loads by 10 % per 5∘ of cone angle and also reduce total blade mass. However, when compared to conventional, three-bladed, upwind designs, the peak main-bearing load of the upscaled, downwind, two-bladed rotor is increased by 280 %. Optimized teeter configurations and individual pitch control can reduce non-rotating damage equivalent loads by 45 % and 22 %, respectively, compared with fixed-hub designs.
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Leian, Zhang, Huang Xuemei, and Yuan Guangming. "Fatigue Life Evaluation For Wind Turbine Blade Based on Multistage Loading Accumulative Damage Theory." Open Mechanical Engineering Journal 9, no. 1 (June 26, 2015): 422–27. http://dx.doi.org/10.2174/1874155x01509010422.

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The fatigue life of MW wind turbine blade was assessed by applying theoretical calculation and test verification. Firstly, the fatigue characteristic curve of FRP material was obtained based on Palmgren-Miner damage theory. Furthermore, The fatigue life of Aeroblade1.5-40.3 wind turbine blade using multistage loading accumulative damage theory could be evaluated over 20 years accordingly. Then the coordinate system of wind turbine blade and its Bladed simulation model were set. By calculating fatigue loading, the moment distribution of fatigue test was obtained. Finally, the blade’s fatigue loading system driven by an eccentric mass was built and the multi-level amplitude resonant mode was adopted to carry on the test. Almost three months’ test results showed that the blade vibrating amplitude was constant, which illustrate the little variation of stiffness of loading point. The stable of stiffness could testify the fatigue life of blade was over 20 years. The results of in-site experiment were basically consistent with the theoretical calculation.
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Parry, A. B. "The effect of blade sweep on the reduction and enhancement of supersonic propeller noise." Journal of Fluid Mechanics 293 (June 25, 1995): 181–206. http://dx.doi.org/10.1017/s0022112095001686.

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An asymptotic frequency-domain approach is used to describe the radiation from a supersonic swept propeller within the framework of linear acoustics. With this approach the radiation of singularities, their points of origin on the blades, and their relation to blade geometry and loading are easily obtained. In particular, it is shown that a swept propeller with a completely subsonic leading edge can still radiate singularities, if the leading edge is blunt, due to a supersonic edge effect at the blade tips. In addition, the radiation from a family of ‘critical’ swept-blade designs is shown to be more singular than that from a straight-bladed design. Numerical and asymptotic results for such designs show that the peak radiation is, typically, increased by 5–10 dB.
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Zhou, Fang, Hassan Mahfuz, Gabriel M. Alsenas, and Howard P. Hanson. "Static and Fatigue Analysis of Composite Turbine Blades Under Random Ocean Current Loading." Marine Technology Society Journal 47, no. 2 (March 1, 2013): 59–69. http://dx.doi.org/10.4031/mtsj.47.2.6.

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AbstractThe objective of this paper is to investigate how U.S. National Renewable Energy Laboratory (NREL)‐designed modeling tools commonly used for wind turbine blade design and analysis can be applied to the design of ocean current turbines (OCT). Design, static analysis, and fatigue life predictions of a horizontal-axis, ocean current turbine composite blade were investigated using NREL’s PreCom, BModes, AeroDyn, FAST with seawater conditions. PreComp was used to compute section properties of this OCT blade. BModes calculated mode shapes and frequencies of the blade. Loading on a turbine blade in the Gulf Stream at a South Florida location (26o4.3’N 79o50.5’W, 25-m depth) was calculated with AeroDyn. FAST was then used to obtain the dynamic response of the blade, including flap and edge bending moment distribution with respect to blade rotation. Static analysis was performed by using a combination of Sandia’s NuMAD and ANSYS. Palmgren-Miner’s cumulative fatigue damage model was employed with damage estimation based on the material fatigue property data in DOE/MSU Composite Material Fatigue Database. During service life, OCT blades are subjected to cyclic loads and random ocean current loading. Hence, the blades experience repeated and alternating stresses, which can lead to fatigue failure. These loads were weighted by rate of occurrence from a histogram analysis of in situ measurements conducted by the Southeast National Marine Renewable Energy Center (SNMREC).
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Liu, Zheng, Xin Liu, Kan Wang, Zhongwei Liang, José A. F. O. Correia, and Abílio De Jesus. "GA-BP Neural Network-Based Strain Prediction in Full-Scale Static Testing of Wind Turbine Blades." Energies 12, no. 6 (March 15, 2019): 1026. http://dx.doi.org/10.3390/en12061026.

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This paper proposes a strain prediction method for wind turbine blades using genetic algorithm back propagation neural networks (GA-BPNNs) with applied loads, loading positions, and displacement as inputs, and the study can be used to provide more data for the wind turbine blades’ health assessment and life prediction. Among all parameters to be tested in full-scale static testing of wind turbine blades, strain is very important. The correlation between the blade strain and the applied loads, loading position, displacement, etc., is non-linear, and the number of input variables is too much, thus the calculation and prediction of the blade strain are very complex and difficult. Moreover, the number of measuring points on the blade is limited, so the full-scale blade static test cannot usually provide enough data and information for the improvement of the blade design. As a result of these concerns, this paper studies strain prediction methods for full-scale blade static testing by introducing GA-BPNN. The accuracy and usability of the GA-BPNN prediction model was verified by the comparison with BPNN model and the FEA results. The results show that BPNN can be effectively used to predict the strain of unmeasured points of wind turbine blades.
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Sjolander, S. A., and K. K. Amrud. "Effects of Tip Clearance on Blade Loading in a Planar Cascade of Turbine Blades." Journal of Turbomachinery 109, no. 2 (April 1, 1987): 237–44. http://dx.doi.org/10.1115/1.3262090.

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The paper examines in detail the structure of the tip leakage flow and its effect on the blade loading in a large-scale planar cascade of turbine blades. The tip clearance was varied from 0.0 to 2.86 percent of the blade chord. One of the blades is instrumented with 14 rows of 73 static taps which allowed a very detailed picture of the loading near the tip to be obtained. In addition to the measurements, extensive flow visualization was conducted using both smoke and surface oil flow. A new feature found in the present experiment was the formation of multiple, discrete tip-leakage vortices as the clearance was increased. Their presence is clearly evident from the surface oil flow and they account for the multiple suction peaks found in the blade pressure distributions. Integration of the pressure distributions showed that for larger values of the clearance the blade loading increases as the tip is approached and only begins to decline very near the tip. The increase was found to occur primarily in the axial component of the force.
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Dissertations / Theses on the topic "Blade Loading"

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Knapke, Clint J. "Aerodynamics of Fan Blade Blending." Wright State University / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=wright1567517259599736.

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Turner, Kevin E. "Stiffness Characteristics of Airfoils Under Pulse Loading." The Ohio State University, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=osu1259113516.

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Tiralap, Aniwat. "Effects of rotor tip blade loading variation on compressor stage performance." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/97857.

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Thesis: S.M., Massachusetts Institute of Technology, Department of Mechanical Engineering, 2015.
Cataloged from PDF version of thesis.
Includes bibliographical references (pages 117-119).
Changes in loss generation associated with altering the rotor tip loading of an embedded compressor stage is assessed. Steady and unsteady three-dimensional computations, complemented by control volume analyses, for varying rotor tip loading distributions provided results for determining if aft-loading rotor tip would yield a stage performance benefit in terms of a reduction in loss generation. Aft-loading rotor blade tip yields a relatively less-mixed-out tip leakage flow at the rotor exit and a reduction in overall tip leakage mass flow hence a lower loss generation; however, the attendant changes in tip flow angle distribution are such that there is an overall increase in the flow angle mismatch between tip flow and main flow leading to higher loss generation. The latter outweighs the former so that rotor passage loss from aft-loading rotor tip is marginally higher unless a constraint is imposed on tip flow angle distribution so that associated induced loss is negligible; a potential strategy for achieving this is proposed. In the course of assessing the benefit from unsteady tip leakage flow recovery in the downstream stator, it was determined that tip clearance flow is inherently unsteady with a time-scale distinctly different from the blade passing time. The disparity between the two timescales: (i) defines the periodicity of the unsteady rotor-stator flow, which is an integral multiple of blade passing time; and (ii) causes tip leakage vortex to enter the downstream stator at specific pitchwise locations for different blade passing cycles, which is a tip leakage flow phasing effect. Because of an inadequate grid resolution defining the unsteady interaction of tip flow with downstream stator, the benefit from unsteady tip flow recovery is the lower bound of its actual benefit. A revised design hypothesis is thus as follows: "rotor should be tip-aft-loaded and hub-fore-loaded while stator should be hub-aft-loaded and tip-fore-loaded with tip/hub leakage flow angle distribution such that it results in no additional loss". For the compressor stage being assessed here, an estimated 0.15% enhancement in stage efficiency is possible from aft-loading rotor tip only.
by Aniwat Tiralap.
S.M.
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Walker, John Scott. "Dynamic loading and stall of clean and fouled tidal turbine blade sections." Thesis, University of Glasgow, 2018. http://theses.gla.ac.uk/8715/.

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The current drive to generate energy from sustainable renewable resources has led to an increased interest in generating power through exploiting the kinetic energy in faster flowing tidal streams. Much of the knowledge gained from the development of wind turbines has been applied to the tidal stream turbine. However, the hostile marine environment introduces new technological challenges. The tidal turbine operates under highly unsteady, turbulent flow conditions and the occurrence of marine biofouling adds further complication to the issue. The main objective of the present work is to advance the understanding of the effect marine fouling has on the unsteady hydrodynamic loading and performance of tidal turbine blade sections. To investigate this challenging fluid phenomenon, a series of two-dimensional static and unsteady experiments were designed and conducted in the dynamic stall test rig at the University of Glasgow's Handley Page wind tunnel facility. The test matrix was constructed to cover the full operating envelope of a blade from MW-scale turbines, and included three thicker, cambered blade sections from two radial positions on the blade - a NACA 63-619 and two proprietary AHH designs. Chordwise integrated force and pitching moment coefficients were obtained from surface pressure measurements for three representative blade fouling configurations: an aerodynamically clean baseline; a light level of widely distributed microfouling roughness; and the addition of macrofouling with a single instrumented barnacle protuberance. This work has generated what is believed to be a unique database of unsteady tidal turbine blade section performance and, more importantly, the negative impact marine biofouling is likely to have on these investigated parameters. The approach followed through the work has been to assess the impact of marine biofouling on the individual blade sections and then assess the consequences of marine biofouling on the turbine by combining the blade section findings in a BEMT numerical performance model.
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Mish, Patrick F. "Mean Loading and Turbulence Scale Effects on the Surface Pressure Fluctuations Occurring on a NACA 0015 Airfoil Immersed in Grid Generated Turbulence." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/33751.

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Detailed surface pressure measurements have been made on a NACA 0015 immersed in two grid generated homogenous flows at Re = 1.17 x 10^6 for a = 0°, 4°, 8°, 12°, 16°, and 20°. The goal of this measurement was to reveal and highlight mean loading and turbulence scale effects on surface pressure fluctuations resulting from turbulence/airfoil interaction. Also, measurements are compared with the theory of Amiet (1976a,b). The surface pressure response shows a dependance on angle of attack, the nature of which is related to the relative chord/turbulence scale. The dependance on turbulence scale appears to be non-monotonic at low reduced frequencies, wr = Pi*f*c/U with both an increase and decrease in unsteady pressure magnitude occuring with increasing mean load. A reduced frequency overlap region exists at wr > 10 where the two different scale flows begin to produce similar effects on the surface pressure with increasing angle of attack manifesting as a rise in unsteady surface pressure magnitude. Also, the interaction of the full 3-dimensional wavenumber spectrum affects the distance over which pressure fluctuations correlate and the extent of correlation is affected by angle of attack as demonstrated in the chordwise and spanwise pressure correlation. Amietâ s theory is shown to agree favorably with measurements in the leading edge region although demonstrates insufficiencies in predicting unsteady pressure phasing.
Master of Science
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Wong, Vui-Hong, and n/a. "Finite Element Analysis and Improvement of Impeller Blade Geometry." Griffith University. School of Engineering, 2003. http://www4.gu.edu.au:8080/adt-root/public/adt-QGU20030825.150853.

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Stratification of water in large reservoirs occurs in summer, or at anytime in hot climates where the water surface is exposed long-term to sunlight and the water surface is heated. Natural mixing will not occur due to the cooler and denser water always staying at the lower levels. Therefore, mechanical circulators are designed to prevent water quality problems related to stratification and depletion of dissolved oxygen. Impellers that produce the flow in mechanical circulators are available in different sizes and these impellers are designed to produce different flow rates. Due to hydraulic loadings, impellers have to be strong and durable. Loadings on impellers depend on their geometries and therefore, a durable impeller is a good combination of the use of correct materials and good geometry. Long and slender impellers are prone to failure when subjected to high hydrodynamic loadings. Nowadays, designers have very limited information on predicting the stresses on impellers and the deflection patterns of impellers because there are no design rules in designing these impeller blades and there is no such thing as "best geometry". A good impeller blade design is by guesswork and experience. In order to design the geometry that suits this application, trial-and-error finite element analyses have been conducted in this project to minimize stress levels on the blades. This research involves the use of finite element analysis (FEA) to predict stress and deflection of impeller blades used on large (5m diameter) ducted axial flow impellers as the first step in the design process. Then, based on the results, improvements have been done to the models until the final design was made. As far as the author has been able to determine, this has not been researched before. Finite Element Analysis has been used on wind turbine blades, rudders and hulls of boats but not on axial flow impeller blades of the type used in this project. For the purpose of this project, commercial finite element computer program packages STRAND6 and STRAND7 were used as the main analysis tools. A static line load increasing linearly with radius along the blade has been used to simulate the assumed hydrodynamic loading, and applied to all FEA blade models. The analysis results proved the stresses on blades are largely dependant on the blade geometry. From the analysis results, the author modified the stacking arrangement of the FEA elements in order to minimize both the tensile stresses and the displacements of the blades at the tip. Parametric studies have been done in order to obtain the best FEA impeller blade model.
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Marshall, Matthew L. "Validation of a Modified Version of OVERFLOW 2.2 for Use with Turbomachinery Under Clean and Total Pressure Distorted Conditions and a Study of Blade Loading in Distortion." BYU ScholarsArchive, 2014. https://scholarsarchive.byu.edu/etd/5540.

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Inlet distortion is an important consideration in fan performance. Distortion can be generated through flight conditions and airframe-engine interfaces. The focus of this paper is a series of high-fidelity, time-accurate Computational Fluid Dynamics (CFD) simulations of a multistage fan, investigating distortion transfer, distortion generation, and the underlying flow physics under different operating conditions. The simulations are full annulus and include 3 stages and the inlet guide vane (IGV). The code used to carry out these simulations is a modified version of Overflow2.2 that was developed as part of the Computational Research and Engineering Acquisition Tools and Environment (CREATE) program. The inlet boundary condition is a single revolution (sinusoidal pattern with one period over the circumference ) total pressure distortion. Simulations at choke, design, and near stall are analyzed and compared to experimental data. Distortion transfer and generation is analyzed under these different operating conditions. Analysis includes the phase and amplitude of total temperature and pressure distortion through each stage of the fan, level of distortion transfer and generation in each stage, and blade loading. An understanding of the flow physics associated with distorted flows will help fan designers account for unsteady flow physics at design and off-design operating conditions, in order to build more robust fans offering a greater stability margin.
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Jia, H.-X., G. Xi, L. Müller, R. Mailach, and K. Vogeler. "Effect of clocking on unsteady rotor blade loading in a low-speed axial compressor at design and off-design operating conditions." Sage, 2008. https://publish.fid-move.qucosa.de/id/qucosa%3A38439.

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This paper presents the results of stator clocking investigations at a design point and an operating point near the stability limit in a low-speed research compressor (LSRC). The unsteady flow field of the LSRC at several clocking configurations was investigated using a three-dimensional unsteady, viscous solver. The unsteady pressure on the rotor blades at midspan (MS) was measured using time-resolving piezoresistive miniature pressure transducers. The effect of clocking on the unsteady pressure fluctuation at MS on the rotor blades is discussed for different operating points. Based on the unsteady profile pressures, the blade pressure forces were calculated. The peak-to-peak amplitudes of the unsteady blade pressure forces are presented and analysed for different clocking positions at both the design point and the operating point near the stability limit of the compressor.
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Huh, Kevin S. (Kevin Sangmin). "Helicopter rotor blade loading calculations using an axisymmetric vortex sheet and the free wake method." Thesis, Massachusetts Institute of Technology, 1988. http://hdl.handle.net/1721.1/34028.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1988.
Title as it appeared in M.I.T. Graduate List, Sept. 1987: Calculations of helicopter blade loading using an axisymmetric vortex sheet and free wake method.
Bibliography: leaves 75-77.
by Kevin Huh.
M.S.
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Reynolds, Scott B. "Particle Image Velocimetry Analysis on the Effects of Stator Loading on Transonic Blade-Row Interactions." Diss., CLICK HERE for online access, 2010. http://contentdm.lib.byu.edu/ETD/image/etd3423.pdf.

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Books on the topic "Blade Loading"

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Hanson, Donald B. Unified aeroacoustics analysis for high speed turboprop aerodynamics and noise. Volume 1 - Development of theory for blade loading, wakes and noise. Cleveland, Ohio: Lewis Research Center, 1991.

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Watson, Warren T. Measurement of dynamic blade loadings for marine propellers. [Downsview, Ont.]: Dept. of Aerospace Science and Engineering, University of Toronto, 1991.

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Watson, Warren T. Measurement of dynamic blade loadings for marine propellers. Ottawa: National Library of Canada = Bibliothèque nationale du Canada, 1991.

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Sadowski, Tomasz, and Przemysław Golewski. Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8.

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United States. National Transportation Safety Board. Aircraft accident report: In-flight loss of propeller blade and uncontrolled collision with terrain, Mitsubishi MU-2B-60, N86SD, Zwingle, Iowa, April 19, 1993. Washington, D.C: National Transportation Safety Board, 1993.

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Have, A. A. ten. WISPER and WISPERX: Final definition of two standardised fatigue loading sequences for wind turbine blades. Amsterdam: National Aerospace Laboratory, 1992.

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Have, A. A. ten. WISPER and WISPERX: Final definition of two standardised fatigue loading sequences for wind turbine blades. Amsterdam: National Aerospace Laboratory, 1992.

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United States. National Transportation Safety Board. Aircraft accident report: In-flight loss of propeller blade, forced landing and collision with terrain, Atlantic Southeast Airlines, Inc. Flight 529, Embraer EMB-120RT, N256AS, Carrollton, Georgia, August 21, 1995. Washington, D.C: National Transportation Safety Board, 1996.

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J, Clark Bruce, Groeneweg John F, and United States. National Aeronautics and Space Administration., eds. High-speed propeller noise predictions: Effects of boundary conditions used in blade loading calculations. [Washington, DC]: National Aeronautics and Space Administration, 1987.

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J, Clark Bruce, Groeneweg John F, and United States. National Aeronautics and Space Administration., eds. High-speed propeller noise predictions: Effects of boundary conditions used in blade loading calculations. [Washington, DC]: National Aeronautics and Space Administration, 1987.

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Book chapters on the topic "Blade Loading"

1

Edwards, J. P., D. R. Glynn, and D. G. Tatchell. "Flow and Blade Loading in Centrifugal Impellers." In Lecture Notes in Engineering, 302–17. Berlin, Heidelberg: Springer Berlin Heidelberg, 1986. http://dx.doi.org/10.1007/978-3-642-82781-5_23.

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Chen, Shih H. "Turbomachinery Blade Loading Prediction Using the Panel Method." In Boundary Element Methods in Engineering, 29–35. Berlin, Heidelberg: Springer Berlin Heidelberg, 1990. http://dx.doi.org/10.1007/978-3-642-84238-2_5.

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Backaert, Stéphane, Philippe Chatelain, Grégoire Winckelmans, and Ivan De Visscher. "Vortex Particle-Mesh Simulations of Atmospheric Turbulence Effects on Wind Turbine Blade Loading and Wake Dynamics." In Research Topics in Wind Energy, 135–40. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54696-9_20.

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Lautridou, J. C., J. Y. Guedou, and J. Delautre. "Comparison of Single Crystal Superalloys for Turbine Blades Through TMF Tests." In Fatigue under Thermal and Mechanical Loading: Mechanisms, Mechanics and Modelling, 141–49. Dordrecht: Springer Netherlands, 1996. http://dx.doi.org/10.1007/978-94-015-8636-8_15.

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Sadowski, Tomasz, and Przemysław Golewski. "Introduction." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 1–3. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_1.

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Sadowski, Tomasz, and Przemysław Golewski. "Protective Thermal Barrier Coatings." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 5–11. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_2.

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Sadowski, Tomasz, and Przemysław Golewski. "Thermal Loads." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 13–24. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_3.

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Sadowski, Tomasz, and Przemysław Golewski. "Mechanical Loads." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 25–35. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_4.

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Sadowski, Tomasz, and Przemysław Golewski. "Environmental Loads." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 37–44. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_5.

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Sadowski, Tomasz, and Przemysław Golewski. "State of Arts in Experimental Testing of TBCs Systems—Literature Analysis." In Loadings in Thermal Barrier Coatings of Jet Engine Turbine Blades, 45–65. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-0919-8_6.

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Conference papers on the topic "Blade Loading"

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Nathan, K. Rajaguru, and S. Thanigaiarasu. "Effect of different endplates on blade aerodynamic performance and blade loading of VAWT with symmetric airfoil blades." In 2017 International Conference on Green Energy and Applications (ICGEA). IEEE, 2017. http://dx.doi.org/10.1109/icgea.2017.7924645.

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MANWARING, STEVEN, and SANFORD FLEETER. "Periodic rotor blade aerodynamics including loading effects." In 1st National Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3639.

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DASH, R. "High speed rotor noise due to blade loading." In 10th Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1902.

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Mahmoud, Abdelgadir M., and Mohd S. Leong. "The Effect of Non-Uniform Aerodynamic Loading on the Blade Responses." In ASME 2007 Power Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/power2007-22048.

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Turbine blades are always subjected to severe aerodynamic loading. The aerodynamic loading is uniform and Of harmonic nature. The harmonic nature depends on the rotor speed and number of nozzles (vanes counts). This harmonic loading is the main sources responsible for blade excitation. In some circumstances, the aerodynamic loading is not uniform and varies circumferentially. This paper discussed the effect of the non-uniform aerodynamic loading on the blade vibrational responses. The work involved the experimental study of forced response amplitude of model blades due to inlet flow distortion in the presence of airflow. This controlled inlet flow distortion therefore represents a nearly realistic environment involving rotating blades in the presence of airflow. A test rig was fabricated consisting of a rotating bladed disk assembly, an inlet flow section (where flow could be controlled or distorted in an incremental manner), flow conditioning module and an aerodynamic flow generator (air suction module with an intake fan) for investigations under laboratory conditions. Tests were undertaken for a combination of different air-flow velocities and blade rotational speeds. The experimental results showed that when the blades were subjected to unsteady aerodynamic loading, the responses of the blades increased and new frequencies were excited. The magnitude of the responses and the responses that corresponding to these new excited frequencies increased with the increase in the airflow velocity. Moreover, as the flow velocity increased the number of the newly excited frequency increased.
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Pampreen, Ronald C. "Cascade Blade Loading Analysis With Application to Turbomachinery Design." In ASME 2007 International Mechanical Engineering Congress and Exposition. ASMEDC, 2007. http://dx.doi.org/10.1115/imece2007-41398.

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The efficient performance of a compressor or pump over a desired stall-free operating range is related to the fluid mechanic loading on the rotating and stationary blades. This loading is a function of the suction and pressure surface velocities and is commonly referred to as aerodynamic (compressors) or hydraulic (pumps) loading. Overall values of maximum limits have been established in design practice as a result of development work. However, the distribution of loading has not been well established. One source of guidance is the database provided by cascade data. Velocity distributions are available, and from this data, blade loading coefficients can be calculated with the intent of applying the results to blade design. In this paper, the blade loading equation is derived to illustrate the principal factors that influence blade loading. These factors include blade number, blade wrap angle, blade length, and the magnitude of the average velocity between blades as determined by flow path contours and blade thickness. The equation gives the designer the ability to make design adjustments to achieve proper loading distribution within recommended values of maximum loading. The review of the cascade data provides the designer with a reference for allowable design distribution and maximum loading limits.
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Sjolander, Steen A., and Kim K. Amrud. "Effects of Tip Clearance on Blade Loading in a Planar Cascade of Turbine Blades." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-245.

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The paper examines in detail the structure of the tip leakage flow and its effect on the blade loading in a large-scale planar cascade of turbine blades. The tip clearance was varied from 0.0 to 2.86% of the blade chord. One of the blades is instrumented with 14 rows of 73 static taps which allowed a very detailed picture of the loading near the tip to be obtained. In addition to the measurements, extensive flow visualization was conducted using both smoke and surface oil flow. A new feature found in the present experiment was the formation of multiple, discrete tip-leakage vortices as the clearance was increased. Their presence is clearly evident from the surface oil flow and they account for the multiple suction peaks found in the blade pressure distributions. Integration of the pressure distributions showed that for larger values of the clearance the blade loading increases as the tip is approached and only begins to decline very near the tip. The increase was found to occur primarily in the axial component of the force.
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Johnston, David, and Sanford Fleeter. "Turbine blade unsteady loading change due to stator indexing." In 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-3597.

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Rabe, D., A. Bolcs, and P. Russler. "Influence of inlet distortion on transonic compressor blade loading." In 31st Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-2461.

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Liu, Baojie, Du Fu, and Xianjun Yu. "Maximum Loading Capacity of Tandem Blades in Axial Compressors." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76770.

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Tandem blades are widely reported to be superior to a single-blade configuration under the aerodynamic circumstance with a large flow turning in a stator or a high work input in a rotor. Aiming at the design of a highly loaded rear stage of a high pressure compressor with the advanced concept, the maximum loading capacity of a tandem-blade configuration, which is rarely described in open literature, is fundamentally necessary to be explicit in order to determine a stable operation range. A diffuser analogy is carefully carried out between the tandem-blade geometry and the diffuser passage using a reliable and robust numerical method. The analysis approach to effectively predicting the maximum static pressure rise is verified by the limited results of computational fluid dynamics (CFD) and experiments. In addition, the maximum loading capacity of the tandem-blade configuration is compared with that of the single-blade configuration to define a more favorable design range of meanline parameters. The results indicate that the tandem blade outperforms the conventional blade in a specific design space and the approach can be a potential design tool to guide the selection of one-dimensional parameters of tandem blades in a highly loaded axial compressor.
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Boyd, Douglas, and Sanford Fleeter. "Rotor Blade Unsteady Aerodynamics at High Loading Including Dynamic Stall." In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3637.

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Reports on the topic "Blade Loading"

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Kelley, N. D. Inflow characteristics associated with high-blade-loading events in a wind farm. Office of Scientific and Technical Information (OSTI), July 1993. http://dx.doi.org/10.2172/10172220.

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White, D. New Method for Dual-Axis Fatigue Testing of Large Wind Turbine Blades Using Resonance Excitation and Spectral Loading. Office of Scientific and Technical Information (OSTI), April 2004. http://dx.doi.org/10.2172/15007390.

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