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Journal articles on the topic 'Rotor-blade system'

Author: Grafiati

Published: 13 April 2024

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1

Ngui, Wai Keng, M. Salman Leong, L. M. Hee, and Ahmed M. Abdelrhman. "Detection of Twisted Blade in Multi Stage Rotor System." Applied Mechanics and Materials 773-774 (July 2015): 144–48. http://dx.doi.org/10.4028/www.scientific.net/amm.773-774.144.

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This paper studies the detection of twisted blade in a multi stages rotor system. Experimental study was undertaken to simulate twisted blade conditions in a three stages rotor system. The feasibility of vibration analysis as the technique to detect twisted blade based on the rotor operating frequency and its blade passing frequency was investigated in this study. Experimental results show that twisted blade can be easily detected by looking into the pattern of the vibration spectrum and its individual peaks.

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2

Dalli, Uğbreve;ur, and Şcedilefaatdin Yüksel. "Identification of Flap Motion Parameters for Vibration Reduction in Helicopter Rotors with Multiple Active Trailing Edge Flaps." Shock and Vibration 18, no. 5 (2011): 727–45. http://dx.doi.org/10.1155/2011/675791.

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An active control method utilizing the multiple trailing edge flap configuration for rotorcraft vibration suppression and blade loads control is presented. A comprehensive model for rotor blade with active trailing edge flaps is used to calculate the vibration characteristics, natural frequencies and mode shapes of any complex composite helicopter rotor blade. A computer program is developed to calculate the system response, rotor blade root forces and moments under aerodynamic forcing conditions. Rotor blade system response is calculated using the proposed solution method and the developed pr

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3

Lee, Yu-Tai, and JinZhang Feng. "Potential and Viscous Interactions for a Multi-Blade-Row Compressor." Journal of Turbomachinery 126, no. 4 (2004): 464–72. http://dx.doi.org/10.1115/1.1740778.

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A computationally efficient time-accurate vortex method for unsteady incompressible flows through multiple blade row systems is presented. The method represents the boundary surfaces using vortex systems. A local coordinate system is assigned to each independently moving blade row. Blade shed vorticity is determined from two generating mechanisms and convected using the Euler equation. The first mechanism of vorticity generation is a potential mechanism from a nonlinear unsteady pressure-type Kutta condition applied at the blade trailing edges. The second mechanism is a viscous mechanism from

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4

Lu, Zhenyong, Shun Zhong, Huizheng Chen, Yushu Chen, Jiajie Han, and Chao Wang. "Modeling and Dynamic Characteristics Analysis of Blade-Disk Dual-Rotor System." Complexity 2020 (January 25, 2020): 1–13. http://dx.doi.org/10.1155/2020/2493169.

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In this paper, a simplified dynamic model of a dual-rotor system coupled with blade disk is built, and the effects of blade parameters of an aircraft engine on the dynamic characteristics of a dual-rotor system are studied. In the methodology, the blade is simplified as a cantilever structure, and the dynamical equations are obtained by the means of a finite element method. The amplitude-frequency response curves and orbits of shaft centre-vibration shape diagram are used to analyze the effects of blade parameters on dynamic characteristics of a dual-rotor system. The results indicate that the

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5

Wang, Nanfei, Chao Liu, and Dongxiang Jiang. "Prediction of transient vibration response of dual-rotor-blade-casing system with blade off." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (2019): 5164–76. http://dx.doi.org/10.1177/0954410019839884.

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Fan blade off occurring in a running rotor of the turbofan engine dual-rotor system will cause a sudden unbalance and inertia asymmetry, which results in large impact load and consequently induces the rubbing between blade and casing. In order to reveal the transient dynamic response characteristics of actual aero-engine when fan blade off event occurs, the dynamic model of dual-rotor-blade-casing system is developed, in which the distribution characteristics of the stiffness and mass, the load transfer, and the coupling effects of dual-rotor and casing are included. Considering several excita

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6

Lu, Xin, Jie Tang, and Liwen Wang. "Simulation and Experimental Study on Rotor System Dynamic Analysis with the Blade-Coating Rubbing Faults." Shock and Vibration 2021 (September 10, 2021): 1–15. http://dx.doi.org/10.1155/2021/2442760.

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In the modern turbo-machinery, reducing the clearance between the blade tip and casing inner face is an effective method to improve the power performance, but the clearance reduction leads to increased risk of blade-casing rubbing. In this paper, a blade-coating rubbing force model which considered the abradable coating scraping is developed to simulate the rotor system dynamic characteristics at blade-casing rubbing faults with abradable coating. An experimental tester is established to simulate the rotor system blade-casing rubbing faults; the AlSi-ployphenyl ester abradable coating is prepa

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7

Zalkind, Daniel S., Gavin K. Ananda, Mayank Chetan, et al. "System-level design studies for large rotors." Wind Energy Science 4, no. 4 (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-lo

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8

Christensen, René H., and Ilmar F. Santos. "Active Rotor-Blade Vibration Control Using Shaft-Based Electromagnetic Actuation." Journal of Engineering for Gas Turbines and Power 128, no. 3 (2004): 644–52. http://dx.doi.org/10.1115/1.2056533.

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In this paper the feasibility of actively suppressing rotor and blade vibration via shaft-based actuation is studied. A mathematical model is derived, taking into account the special dynamical characteristics of coupled rotor-blade systems, such as centrifugal stiffened blades and parametric vibration modes. An investigation of controllability and observability shows that if the blades are properly mistuned, it is possible to suppress shaft as well as blade vibration levels by using only shaft-based actuation and sensing; though, in tuned bladed systems, shaft as well as blade actuation and se

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9

Abdelrhman, Ahmed M., M. Salman Leong, Yasin M. Hamdan, and Kar Hoou Hui. "Time Frequency Analysis for Blade Rub Detection in Multi Stage Rotor System." Applied Mechanics and Materials 773-774 (July 2015): 95–99. http://dx.doi.org/10.4028/www.scientific.net/amm.773-774.95.

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Blade fault is one of the most causes of failure in turbo machinery. This paper discussed the time frequency analysis for blade rubbing detection from casing vibration signal. Feasibility of Short Time Fourier Transform (STFT), Wigner-Ville distribution (WVD) and Choi-Williams distribution (CWD) were examined for blade rub detection in a multi stage blade system through an experimental data. Analysis results of the experimental data showed that these time frequency analysis methods have some inevitable deficiencies in segregating the blade passing frequency (BPF) components of the three rotor

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10

Qian, Xiaoru, Peigang Yan, Xiangfeng Wang, and Wanjin Han. "Numerical Analysis of Conjugated Heat Transfer and Thermal Stress Distributions in a High-Temperature Ni-Based Superalloy Turbine Rotor Blade." Energies 15, no. 14 (2022): 4972. http://dx.doi.org/10.3390/en15144972.

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This paper establishes a multidisciplinary method combining conjugate heat transfer (CHT) and thermal stress for a high-temperature Ni-based superalloy turbine rotor blade with integrated cooling structures. A conjugate calculation is performed to investigate the coolant flow characteristics, heat transfer, and thermal stress of the rotor blade under rotating and stationary conditions to understand the effects of rotation on the multidisciplinary design of the blade. Furthermore, the maximum resolved shear stress among the 30-slip systems and the corresponding dominant slip system are obtained

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11

Wang, Yu, Mao Sun, and Chao Yan. "Numerical simulation of hovering flow field and interference characteristics of rotor system." Journal of Physics: Conference Series 2235, no. 1 (2022): 012002. http://dx.doi.org/10.1088/1742-6596/2235/1/012002.

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Abstract In order to investigate the aerodynamic interference characteristics of tandem rotor, this paper simulates the hovering flow field of single rotor and tandem rotor based on the dynamic structure overset grid method and unsteady Navier-Stokes equations in computational fluid dynamics (CFD). In the study of hover state of single rotor with twist, the trajectory of the blade vortex and the change pattern are briefly analyzed. Subsequently, the flow field disturbance of tandem rotor, the vortex structure, the pull coefficient and the downwash flow are investigated. The results show that t

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12

Villeneuve, Eric, Derek Harvey, David Zimcik, Roger Aubert, and Jean Perron. "Piezoelectric Deicing System for Rotorcraft." Journal of the American Helicopter Society 60, no. 4 (2015): 1–12. http://dx.doi.org/10.4050/jahs.60.042001.

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Deicing using piezoelectric actuators is considered as a potential solution to the development of low-energy ice protection systems for rotorcraft. This type of system activates resonant frequencies of a structure using piezoelectric actuators to generate sufficient stress to break the bond between the ice and the substrate. First, a numerical method was validated to assist the design of such systems. Numerical simulations were performed for the case of a flat plate and validated experimentally. The model was then used to study important design parameters such as actuator positioning and activ

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13

Augustyn, Marcin, and Filip Lisowski. "Experimental and Numerical Studies on a Single Coherent Blade of a Vertical Axis Carousel Wind Rotor." Energies 16, no. 14 (2023): 5532. http://dx.doi.org/10.3390/en16145532.

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This article presents the results of experimental and numerical studies on a single coherent rotor blade. The blade was designed for a vertical-axis wind turbine rotor with a self-adjusting system and planetary blade rotation. The experimental tests of the full-scale blade model were conducted in a wind tunnel. A computational fluid dynamics (CFD) analysis of the blade’s cross section was then carried out, including the boundary conditions corresponding to those adopted in the wind tunnel. The main objective of the study was to determine the aerodynamic forces and aerodynamic moment for the pr

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14

Giljarhus, Knut Erik Teigen, Alessandro Porcarelli, and Jørgen Apeland. "Investigation of Rotor Efficiency with Varying Rotor Pitch Angle for a Coaxial Drone." Drones 6, no. 4 (2022): 91. http://dx.doi.org/10.3390/drones6040091.

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Coaxial rotor systems are appealing for multirotor drones, as they increase thrust without increasing the vehicle’s footprint. However, the thrust of a coaxial rotor system is reduced compared to having the rotors in line. It is of interest to increase the efficiency of coaxial systems, both to extend mission time and to enable new mission capabilities. While some parameters of a coaxial system have been explored, such as the rotor-to-rotor distance, the influence of rotor pitch is less understood. This work investigates how adjusting the pitch of the lower rotor relative to that of the upper

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15

Mohammed, Abdulbasit, Hirpa G. Lemu, and Belete Sirahbizu. "Determining Optimum Rotary Blade Design for Wind-Powered Water-Pumping Systems for Local Selected Sites." Strojniški vestnik – Journal of Mechanical Engineering 67, no. 5 (2021): 214–22. http://dx.doi.org/10.5545/sv-jme.2021.7140.

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The design of a windmill rotor is critical for harnessing wind energy. In this work, a study is conducted to optimize the design and performance of a rotor blade that is suitable for low wind conditions. The windmills’ rotor blades are aerodynamically designed based on the SG6043 airfoil and wind speed data at local selected sites. The aerodynamic profile of the rotor blade that can provide a maximum power coefficient, which is the relation between real rotor performance and the available wind energy on a given reference area, was calculated. Different parameters, such as blade shapes, chord d

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16

Mohammed, Abdulbasit, Hirpa G. Lemu, and Belete Sirahbizu. "Determining Optimum Rotary Blade Design for Wind-Powered Water-Pumping Systems for Local Selected Sites." Strojniški vestnik – Journal of Mechanical Engineering 67, no. 5 (2021): 214–22. http://dx.doi.org/10.5545/sv-jme.2021.7104.

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The design of a windmill rotor is critical for harnessing wind energy. In this work, a study is conducted to optimize the design and performance of a rotor blade that is suitable for low wind conditions. The windmills’ rotor blades are aerodynamically designed based on the SG6043 airfoil and wind speed data at local selected sites. The aerodynamic profile of the rotor blade that can provide a maximum power coefficient, which is the relation between real rotor performance and the available wind energy on a given reference area, was calculated. Different parameters, such as blade shapes, chord d

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17

Zuo, Chenglin, Chunhua Wei, Jun Ma, Tingrui Yue, Lei Liu, and Zheyu Shi. "Full-Field Displacement Measurements of Helicopter Rotor Blades Using Stereophotogrammetry." International Journal of Aerospace Engineering 2021 (January 8, 2021): 1–18. http://dx.doi.org/10.1155/2021/8811601.

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This study presents a stereophotogrammetry approach to achieve full-field displacement measurements of helicopter rotor blades. The method is demonstrated in the wind tunnel test of a 2 m diameter rotor, conducted at the 5.5 m × 4 m Aeroacoustic Wind Tunnel of China Aerodynamics Research and Development Center (CARDC). By arranging the retroreflective targets on the special hat installed directly above the rotor hub, the dynamic motion of the rotor shaft was tracked accurately, and a unified coordinate system was established on the rotor. Therefore, three-dimensional coordinates of instantaneo

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18

Zuo, Chenglin, Chunhua Wei, Jun Ma, Tingrui Yue, Lei Liu, and Zheyu Shi. "Full-Field Displacement Measurements of Helicopter Rotor Blades Using Stereophotogrammetry." International Journal of Aerospace Engineering 2021 (January 8, 2021): 1–18. http://dx.doi.org/10.1155/2021/8811601.

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This study presents a stereophotogrammetry approach to achieve full-field displacement measurements of helicopter rotor blades. The method is demonstrated in the wind tunnel test of a 2 m diameter rotor, conducted at the 5.5 m × 4 m Aeroacoustic Wind Tunnel of China Aerodynamics Research and Development Center (CARDC). By arranging the retroreflective targets on the special hat installed directly above the rotor hub, the dynamic motion of the rotor shaft was tracked accurately, and a unified coordinate system was established on the rotor. Therefore, three-dimensional coordinates of instantaneo

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19

Choy, F. K., J. Padovan, and C. Batur. "Rub Interactions of Flexible Casing Rotor Systems." Journal of Engineering for Gas Turbines and Power 111, no. 4 (1989): 652–58. http://dx.doi.org/10.1115/1.3240308.

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Rub interactions between a rotor assembly and its corresponding casing structure has long been one of the major causes for machine failure. Fracture/fatigue failures of turbine impeller blade components may even lead to catastrophic consequences. This paper presents a comprehensive analysis of a complex rotor-bearing-blade-casing system during component rub interactions. The modal method is used in this study. Orthonormal coupled rotor-casing modes are used to obtain accurate relative motion between rotor and casing. External base vibration input and the sudden increase of imbalance are used t

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20

Wen, Chuanmei, Zhimin Zhu, Xuezhong Fu, Tianliang Long, and Bing Li. "Dynamic Analysis of a Bolted Joint Rotor-Bearing System with a Blade–Casing Rubbing Fault." Processes 11, no. 8 (2023): 2379. http://dx.doi.org/10.3390/pr11082379.

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Bolted joints are widely used in aeroengine rotor systems to connect multiple components into an integrated structure and provide sufficient stiffness. The mechanical properties of a bolted joint have a significant effect on rotor dynamics. For modern aeroengine designs, the blade-tip clearance is gradually reduced to improve efficiency, which may lead to rubbing damage and affect safe operation. The mechanical properties of a bolted joint change significantly during the blade–casing rubbing process and influence the dynamic properties of the rotor system. Based on the finite element (FE) mode

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21

Wu, Fei, Jie Wu, Mei Jin, Fang Wang, and Ping Lu. "Influence of Gas-Liquid Distribution Inducer on Mass Transfer Coefficient in Rotating Packed Bed." Advanced Materials Research 908 (March 2014): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amr.908.277.

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Based on acetone-H2O system, the influence of the gas-liquid distribution inducer on the mass transfer coefficient in the rotating packed bed with the stainless steel packing was investigated. Furthermore, the absorption performance was also obtained under the experimental condition of the rotational speed of 630 rpm, the gas flow rate of 2 m3/h and the liquid flow rate of 100 L/h in the rotating packed bed with different types and different installation ways of the distribution inducer. The experimental results showed that the volumetric mass transfer coefficient Kyα per unit contact length o

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22

Lim, Joon W., Chee Tung, and Yung H. Yu. "Prediction of Blade-Vortex Interaction Airloads With Higher-Harmonic Pitch Controls Using the 2GCHAS Comprehensive Code." Journal of Pressure Vessel Technology 123, no. 4 (2001): 469–74. http://dx.doi.org/10.1115/1.1401025.

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Analytically predicted results of blade-vortex interaction (BVI) airloads, using the second- generation comprehensive helicopter analysis system (2GCHAS), are presented with the experimental results obtained from the higher-harmonic-control aeroacoustic rotor test (HART) program using a 40-percent, Mach-scaled model of the hingeless BO-105 main rotor. Correlations include airloads, blade tip deflections, and tip vortex geometry. The effects on blade airload predictions are studied with higher-harmonic pitch controls (HHC). It was concluded that the blade torsional deflection and the wake syste

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23

Srinivasan, A. V., D. G. Cutts, H. T. Shu, D. L. Sharpe, and O. A. Bauchau. "Structural Dynamics of a Helicopter Rotor Blade System." Journal of the American Helicopter Society 35, no. 1 (1990): 75–85. http://dx.doi.org/10.4050/jahs.35.75.

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Abubakar Mas’ud, Abdullahi, Ahmad Jamal, Surajuddeen Adewusi, and Arunachalam Sundaram. "Rotating blade faults classification of a rotor-disk-blade system using artificial neural network." International Journal of Power Electronics and Drive Systems (IJPEDS) 12, no. 3 (2021): 1900. http://dx.doi.org/10.11591/ijpeds.v12.i3.pp1900-1911.

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<span lang="EN-US">In this paper, the artificial neural network (ANN) has been utilized for rotating machinery faults detection and classification. First, experiments were performed to measure the lateral vibration signals of laboratory test rigs for rotor-disk-blade when the blades are defective. A rotor-disk-blade system with 6 regular blades and 5 blades with various defects was constructed. Second, the ANN was applied to classify the different </span><em><span lang="EN-US">x</span></em><span lang="EN-US">- and </span><em><span lang="

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25

Eggers,, A. J., R. Digumarthi, and K. Chaney. "Wind Shear and Turbulence Effects on Rotor Fatigue and Loads Control." Journal of Solar Energy Engineering 125, no. 4 (2003): 402–9. http://dx.doi.org/10.1115/1.1629752.

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The effects of wind shear and turbulence on rotor fatigue and loads control are explored for a large horizontal axis wind turbine in variable speed operation at wind speeds from 4 to 20 m/s. Two- and three-blade rigid rotors are considered over a range of wind shear exponents up to 1.25 and a range of turbulence intensities up to 17%. RMS blade root flatwise moments are predicted to be very substantially increased at higher wind shear, and resultant fatigue damage is increased by many orders of magnitude. Smaller but similar trends occur with increasing turbulence levels. In-plane fatigue dama

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26

Rahmanto, Bayu, Ferry Setiawan, and Edi Sofyan. "Perancangan Aktivitas Pemeliharaan dengan Metode Reliability pada Sistem Main Rotor Blade Helikopter BELL 412EP Studi Kasus Penerbad Semarang." Journal of Applied Mechanical Engineering and Renewable Energy 2, no. 1 (2022): 9–15. http://dx.doi.org/10.52158/jamere.v2i1.243.

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BENGPUSPENERBAD is a central workshop specifically owned by the Indonesian Army in Semarang, where aircraft and helicopters are subject to preventive and corrective maintenance. During the period 2018-2020 the BELL 412 EP helicopters often experienced unscheduled maintenance which resulted in losses resulting in flight failure, this was due to a malfunction in the Main Rotor Blade system. The malfunction of the Main Rotor Blade system is dominated by the hub component, namely on the shaft associated with Crack, Noise and Burn damage, and blade components, namely Corrosions, Nicks, Scratches, D

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27

Awal, Ziad Bin Abdul, and Mohd Shariff bin Ammoo. "A Case Study on the Air Flow Characteristics of the Hirobo-FALCON 505 Controllable Helicopter's Main Rotor Blade." Applied Mechanics and Materials 527 (February 2014): 39–42. http://dx.doi.org/10.4028/www.scientific.net/amm.527.39.

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The aerodynamics of the helicopter rotor is one of the most elating and exigent tribulations faced by the aerodynamicists today. Study through flow visualization process plays a key role in understanding the airflow distinctiveness and vortex interaction of the helicopter main rotor blade. Inspecting and scrutinizing the effects of wake vortices during operation is a great challenge and imperative in designing effective rotor system. This study aimed to visualize the main rotor airflow pattern of the Hirobo-FALCON 505 controllable subscale helicopter and seek for the vortex flow at the blade t

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28

Sekula, Martin K., and Matthew L. Wilbur. "Analysis of a Multiflap Control System for a Swashplateless Rotor." Journal of the American Helicopter Society 57, no. 3 (2012): 1–12. http://dx.doi.org/10.4050/jahs.57.032006.

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An analytical study was conducted examining the feasibility of a swashplateless rotor controlled through two trailing-edge flaps (TEFs), where the cyclic and collective controls were provided by separate TEFs. This analysis included a parametric study examining the impact of various design parameters on TEF deflections. Blade pitch bearing stiffness; blade pitch index; and flap chord, span, location, and control function of the inboard and outboard flaps were systematically varied on a utility-class rotorcraft trimmed in steady level flight. Gradient-based optimizations minimizing flap deflect

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29

Krott, Matthew J., Edward C. Smith, and Christopher D. Rahn. "Modeling and Testing of Fluidic Flexible Matrix Composite Lead–Lag Dampers." Journal of the American Helicopter Society 65, no. 1 (2020): 1–10. http://dx.doi.org/10.4050/jahs.65.012012.

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A new lead–lag damper concept using a fluidic flexible matrix composite (F2MC) tube is presented in this paper. A model is developed for an articulated rotor blade integrated with an F2MC damper consisting of an F2MC tube, an inertia track, an orifice, and a hydraulic accumulator. Benchtop tests using a 4.5-ft rotor blade demonstrate the performance of a smallscale F2MC damper. The blade–damper system model predictions are verified by comparing experimentally measured and model-predicted frequency response data. In benchtop tests, the model predicts blade damping ratios of up to 0.34 with the

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Weiss, Felix, and Christoph Kessler. "Load prediction of hingeless helicopter rotors including drivetrain dynamics." CEAS Aeronautical Journal 12, no. 2 (2021): 215–31. http://dx.doi.org/10.1007/s13272-020-00483-6.

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AbstractIn contrast to analyses with constrained hub speed, the present study includes the dynamic response of coupled rotor-drivetrain modes in the aeromechanic simulation of rotor blade loads. The structural model of the flexible Bo105 rotor-drivetrain system is coupled to aerodynamics modeled by an analytical formulation of unsteady blade element loads combined with a generalized dynamic wake or a free wake, respectively. For two flight states, i. e. cruise flight and large blade loading, a time-marching autopilot trim of the rotor-drivetrain system in wind tunnel configuration is performed

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Alam, M., and H. D. Nelson. "A Blade Loss Response Spectrum for Flexible Rotor Systems." Journal of Engineering for Gas Turbines and Power 107, no. 1 (1985): 197–204. http://dx.doi.org/10.1115/1.3239683.

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A shock spectrum procedure is developed to estimate the peak displacement response of linear flexible rotor-bearing systems subjected to a step change in unbalance (i.e., a blade loss). A progressive and a retrograde response spectrum are established. These blade loss response spectra are expressed in a unique non-dimensional form and are functions of the modal damping ratio and the ratio of rotor spin speed to modal damped whirl speed. Modal decomposition using complex modes is utilized to make use of the unique feature of the spectra for the calculation of the peak blade loss displacement re

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Ignatkin, Yurii M., Pavel V. Makeev, and Alexander I. Shomov. "CALCULATED RESEARCH OF INFLUENCE OF HELICOPTER MAIN ROTORS GEOMETRY ON THE EFFICIENCY IN HOVER MODE BASED ON THE NONLINEAR VORTEX MODEL." Civil Aviation High TECHNOLOGIES 21, no. 6 (2018): 43–53. http://dx.doi.org/10.26467/2079-0619-2018-21-6-43-53.

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The efficiency of the helicopter main rotor in the hover mode is very important, because this mode essentially determines the performance characteristics of the helicopter. A feature of the helicopter rotor aerodynamics is a significant inductive blade influence that highly defines its aerodynamic characteristics. The problem of the influence of the blade twist and spatial geometric layout of the main rotor on its aerodynamic characteristics in the hover mode for a fixed value of the rotor solidity has been considered in this article. As a criterion of efficiency of the rotor in the hover mode

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Гребеников, А. Г., Ю. В. Дьяченко, В. В. Коллеров та ін. "АНАЛІЗ КОНСТРУКТИВНО-ТЕХНОЛОГІЧНИХ ОСОБЛИВОСТЕЙ ЛОПАТЕЙ НЕСУЧИХ ГВИНТІВ ВАЖКИХ ТРАНСПОРТНИХ ВЕРТОЛЬОТІВ". Open Information and Computer Integrated Technologies, № 93 (19 листопада 2021): 59–103. http://dx.doi.org/10.32620/oikit.2021.93.04.

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The analysis of the design and technological features of the rotor blades of heavy transport helicopters is carried out. The main performance characteristics of heavy helicopters are presented. General requirements to helicopter main rotor blades design and specifications for their production are formulated. The design and force diagram of heavy helicopter main rotor blades is considered. The features of structural materials for the main rotor blades of heavy transport helicopters are marked. The main rotor blades differ in their design due to different approaches to materials, manufacturing a

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Coton, F. N., R. A. McD Galbraith, T. Wang, and S. J. Newman. "A wind-tunnel based study of helicopter tail rotor blade vortex interaction." Aeronautical Journal 108, no. 1083 (2004): 237–44. http://dx.doi.org/10.1017/s0001924000005091.

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AbstractThe interaction of a helicopter tail rotor blade with the tip vortex system from the main rotor is a significant source of noise and, in some flight states, can produce marked reductions in control effectiveness. This paper describes a series of wind-tunnel tests to simulate tail rotor blade vortex interaction with a view to providing data for the development and validation of numerical simulations of the phenomenon. In the experiments, which were carried out in the Argyll wind-tunnel of Glasgow University, a single-bladed rotor located in the tunnel’s contraction was used to generate

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35

Mwanyika, Hegespo H., Yusufu AC Jande, and Thomas Kivevele. "Design and Performance Analysis of Composite Airfoil Wind Turbine Blade." Tanzania Journal of Science 47, no. 5 (2021): 1701–15. http://dx.doi.org/10.4314/tjs.v47i5.18.

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Abstract Small horizontal axis wind turbine rotors with composite airfoil rotor blades were designed and investigated in the present study in order to improve its performance in low wind speed and low Reynolds number (Re) conditions for standalone system. The geometrical and aerodynamic nature of a single airfoil small horizontal axis wind turbine blade curtails efficient energy harnessing of the rotor blade. The use of composite airfoil rotor blade improves energy production but imposes uncertainty in determining an optimal design angle of attack and the off design aerodynamic behaviour

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Chiu, Yi-Jui, and Shyh-Chin Huang. "The Influence of a Mistuned Blade’s Staggle Angle on the Vibration and Stability of a Shaft-Disk-Blade Assembly." Shock and Vibration 15, no. 1 (2008): 3–17. http://dx.doi.org/10.1155/2008/714346.

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The influence on coupling vibrations and stability among shaft-torsion, disk-transverse and blade-bending of a rotor system with a mistuned blade's staggle angle was investigated analytically. A shaft-disk-blade system has been found existing two types of coupling vibrations, disk-blade (DB), and blade-blade (BB) modes when the shaft was assumed rigid. If the shaft's torsional flexibility was taken into account, an additional type of coupling modes, shaft-disk-blade (SDB), appeared. When an angle-mistuned blade existed, the blades periodicity was destroyed and it was found to change not only t

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37

Prasad, Damarla Kiran, Kavuluri Venkata Ramana, and Nalluri Mohan Rao. "Weight Function Approach for Semi Elliptical Crack at Blade Mounting Locations in Steam Turbine Rotor System." Periodica Polytechnica Mechanical Engineering 62, no. 3 (2018): 203–8. http://dx.doi.org/10.3311/ppme.11604.

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This paper presents analysis of stress intensity factors at blade mounting locations of steam turbine rotor system. General expressions for the stresses induced in a rotating disc are derived and these equations are applied to steam turbine rotor disc. It is observed that the radial stress increases instantly at blade mounting location which indicates the probability of crack initiation and growth. A semi elliptical crack is considered at that location and weight function approach is used to determine the stress intensity factors. The results are validated with the influence coefficient approa

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38

Bauknecht, Andŕe, Xing Wang, Jan-Arun Faust, and Inderjit Chopra. "Wind Tunnel Test of a Rotorcraft with Lift Compounding." Journal of the American Helicopter Society 66, no. 1 (2021): 1–16. http://dx.doi.org/10.4050/jahs.66.012002.

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Rotorcraft flight speed is limited by compressibility effects on the advancing blade side and decreasing lift potential on the retreating blade side. It may thus be beneficial to employ a hingeless rotor to generate additional lift with the advancing blade and compensate the resulting rolling moment with a fixed wing on the retreating blade side. This concept is a form of "lift compounding" that appears to show enormous potential. The present paper presents results of a wind tunnel test with a slowed, hingeless rotor and single fixed wing on the retreating blade side. Based on rotor test stand

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Roy, Arunabha M. "Finite Element Framework for Efficient Design of Three Dimensional Multicomponent Composite Helicopter Rotor Blade System." Eng 2, no. 1 (2021): 69–79. http://dx.doi.org/10.3390/eng2010006.

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In the present study, a three-dimensional finite element framework has been developed to model a full-scale multilaminate composite helicopter rotor blade. Tip deformation and stress behavior have been analyzed for external aerodynamic loading conditions and compared with the Abaqus FEA model. Furthermore, different parametric studies of geometric design parameters of composite laminates are studied in order to minimize tip deformation and maximize the overall efficiency of the helicopter blade. It is found that these parameters significantly influence the tip deformation characteristic and ca

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Wang, Xing, Wen Li, Xuehui Zhang, Yangli Zhu, Wei Qin, and Haisheng Chen. "Flow characteristic of a multistage radial turbine for supercritical compressed air energy storage system." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 6 (2017): 622–40. http://dx.doi.org/10.1177/0957650917743366.

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Compressed air in supercritical compressed air energy storage system expand from supercritical to atmospheric conditions at lower inlet temperature (<500 K) to generate MW scale power. Therefore, a new multistage radial turbine is adopted and the flow characteristic is investigated by numerical simulation. Effects of ideal gas model and tip clearance on the performance and flow field of the multistage turbine are revealed. Results show that ideal gas model can reveal flow pattern under supercritical condition correctly while leading to obvious deviation of isentropic enthalpy drop, entropy,

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41

Cameron, Christopher, Jayant Sirohi, Joseph Schmaus, and Inderjit Chopra. "Performance and Loads of a Reduced-Scale Coaxial Counterrotating Rotor." Journal of the American Helicopter Society 64, no. 4 (2019): 1–15. http://dx.doi.org/10.4050/jahs.64.042003.

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The results of hover and wind tunnel tests of a reduced-scale, closely spaced, rigid, coaxial counterrotating rotor system are presented, along with results from a comprehensive analysis. The system features two-bladed upper and lower rotors, 2.03 m in diameter, with uniform section, untwisted rotor blades. Measurements include upper and lower rotor steady and vibratory hub loads, as well as control angles and control loads. Blade tip clearance was measured using an optical sensor. The rotor system was tested in hover and at advance ratios between 0.21 and 0.53, at collective pitches ranging f

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42

Chen, T. Y., C. W. Hung, and Y. T. Liao. "Experimental Study on Aerodynamics of Micro-Wind Turbines with Large-Tip non-Twisted Blades." Journal of Mechanics 29, no. 3 (2013): N15—N20. http://dx.doi.org/10.1017/jmech.2013.35.

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AbstractThis research experimentally investigates the rotor aerodynamics of horizontal-axis, micro-wind turbines. Specifically, the aerodynamic characteristics of large-tip, non-twisted blades are studied. The study is conducted in a wind tunnel system to obtain the relations between the power coefficient (CP) and tip speed ratio (TSR), the torque coefficient (CT) and TSR. Effects of rotor position inside a flanged diffuser, rotor solidity and blade number on rotor performance are investigated. The blade cross-section is NACA4415 airfoil. The pitch angle of the blades is fixed at 30°, and the

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El-Oun, Z. B., and J. M. Owen. "Preswirl Blade-Cooling Effectiveness in an Adiabatic Rotor–Stator System." Journal of Turbomachinery 111, no. 4 (1989): 522–29. http://dx.doi.org/10.1115/1.3262303.

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Blade-cooling air for a high-pressure turbine is often supplied from preswirl nozzles attached to a stationary casing. By swirling the cooling air in the direction of rotation of the turbine disk, the temperature of the air relative to the blades can be reduced. The question addressed in this paper is: Knowing the temperatures of the preswirl and disk-cooling flows, what is the temperature of the blade-cooling air? A simple theoretical model, based on the Reynolds analogy applied to an adiabatic rotor–stator system, is used to calculate the preswirl effectiveness (that is, the reduction in the

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Ng, W. F., and A. H. Epstein. "Unsteady Losses in Transonic Compressors." Journal of Engineering for Gas Turbines and Power 107, no. 2 (1985): 345–53. http://dx.doi.org/10.1115/1.3239727.

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A newly developed probe has been used to measure the time-resolved total temperature and pressure in a transonic compressor. The investigation revealed the presence of large fluctuations in the blade-to-blade core flow occurring at a frequency of three to four times blade passing. These variations are not steady in the rotor relative frame and are thought to be caused by unsteadiness in the rotor shock system, driven perhaps by a shed vortex in the blade wake. The loss associated with this unsteadiness is calculated and the implications for stage performance are discussed.

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Abdelrhman, Ahmed M., M. Salman Leong, Lim Meng Hee, and Wai Keng Ngui. "Application of Wavelet Analysis in Blade Faults Diagnosis for Multi-Stages Rotor System." Applied Mechanics and Materials 393 (September 2013): 959–64. http://dx.doi.org/10.4028/www.scientific.net/amm.393.959.

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Blade fault is one of the most common faults in turbomachinery. In this article, a rotor system which consists of multiple stages of blades was developed. A variety of blade fault conditions were investigated and its vibration responses were measured. The feasibility of wavelet analysis for multi-stages blade fault diagnosis was tested using simulated signals as well as experimental data. The use of wavelet analysis as the tool to detect multi stages blade faults was studied. Some probable solutions to improve multi stages blade fault diagnosis by wavelet analysis were also suggested.

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Ma, Hui, Fanli Yin, Zhiyuan Wu, Xingyu Tai, and Bangchun Wen. "Nonlinear vibration response analysis of a rotor-blade system with blade-tip rubbing." Nonlinear Dynamics 84, no. 3 (2015): 1225–58. http://dx.doi.org/10.1007/s11071-015-2564-5.

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Lee, Hwanhee, Ji-Seok Song, Seog-Ju Cha, and Sungsoo Na. "Dynamic response of coupled shaft torsion and blade bending in rotor blade system." Journal of Mechanical Science and Technology 27, no. 9 (2013): 2585–97. http://dx.doi.org/10.1007/s12206-013-0702-x.

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48

Mingfu, Liao, Song Mingbo, and Wang Siji. "Active Elastic Support/Dry Friction Damper with Piezoelectric Ceramic Actuator." Shock and Vibration 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/712426.

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The basic operation principle of elastic support/dry friction damper in rotor system was introduced and the unbalance response of the rotor with elastic support/dry friction damper was analyzed theoretically. Based on the previous structure using an electromagnet as actuator, an active elastic support/dry friction damper using piezoelectric ceramic actuator was designed and its effectiveness of reducing rotor vibration when rotor traverses its critical speed and blade-out event happened was experimentally verified. The experimental results show that the active elastic support/dry friction damp

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Kingan, Michael J., Riul Jung, and Ryan S. McKay. "Contra-rotating rotor noise reduction methods." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 6 (2023): 2218–24. http://dx.doi.org/10.3397/in_2023_0327.

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This paper describes an experimental and numerical investigation into the tones produced by a contra-rotating rotor system for use on small unmanned aerial vehicles. The effect of changing the blade shape and the diameter of the lower rotor is investigated and it is shown that different blade geometries can be used to significantly reduce tone noise levels. The numerical simulations are validated against the experimental measurements.

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Kumar, K. Ramesh, and M. Selvaraj. "Review on Energy Enhancement Techniques of Wind Turbine System." Advances in Science and Technology 106 (May 2021): 121–30. http://dx.doi.org/10.4028/www.scientific.net/ast.106.121.

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Wind energy is the quickest growing sustainable energy resource in present energy crisis scenario. It has been considered as one of the most viable sources of environmental friendly energy. Starting investment cost of the wind turbine plant is exorbitant. Moreover, production cost of the wind turbine blade is about 20% of the wind turbine plant cost. It is fundamental to decrease the life-cycle cost of wind turbine plant by efficient utilization available wind speed. Optimized diffuser (Convergent divergent type and Convergent type) has been developed with highest possible pressure difference

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