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Journal articles on the topic 'BLADE ROUGHNESS'

Author: Grafiati

Published: 11 September 2023

Last updated: 31 July 2025

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1

Chen, Yan, Chunxiang Gao, and Wuli Chu. "Effect and Mechanism of Roughness on the Performance of a Five-Stage Axial Flow Compressor." Aerospace 9, no. 8 (2022): 428. http://dx.doi.org/10.3390/aerospace9080428.

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In order to prolong the service life of multistage axial compressors, it is increasingly important to study the influence of blade surface roughness on the compressor performance. In this paper, a five-stage axial compressor of a real aero-engine was selected as the research object, and an equivalent gravel roughness model was used to model the roughness based on measured blade surface roughness data. Furthermore, the impact of blade surface roughness on the performance at design rotational speed was studied by full three-dimensional numerical simulation, and the mechanism of performance varia

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2

Yun, Yong Il, Il Young Park, and Seung Jin Song. "Performance Degradation due to Blade Surface Roughness in a Single-Stage Axial Turbine." Journal of Turbomachinery 127, no. 1 (2005): 137–43. http://dx.doi.org/10.1115/1.1811097.

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Turbine blades experience significant surface degradation with service. Previous studies indicate that an order-of-magnitude or greater increase in roughness height is typical, and these elevated levels of surface roughness significantly influence turbine efficiency and heat transfer. This paper presents measurement and a mean-line analysis of turbine efficiency reduction due to blade surface roughness. Performance tests have been conducted in a low-speed, single-stage, axial flow turbine with roughened blades. Sheets of sandpaper with equivalent sandgrain roughnesses of 106 and 400 μm have be

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3

Liu, Chen, Yipeng Cao, Sihui Ding, Wenping Zhang, Yuhang Cai, and Aqiang Lin. "Effects of blade surface roughness on compressor performance and tonal noise emission in a marine diesel engine turbocharger." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 234, no. 14 (2020): 3476–90. http://dx.doi.org/10.1177/0954407020927637.

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A numerical study was conducted to investigate the effects of blade surface roughness on compressor performance and tonal noise emission. The equivalent sand-grain roughness model was used to account for blade surface roughness, and a hybrid method that combines computational fluid dynamics and boundary element method was used to predict compressor performance and tonal noise. The numerical approach was validated against experimental data for a baseline compressor. Nine different cases with different blade surface roughness were studied in this paper, the global performance was analyzed under

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4

Tangler, J. L. "Influence of Pitch, Twist, and Taper on a Blade’s Performance Loss due to Roughness." Journal of Solar Energy Engineering 119, no. 3 (1997): 248–52. http://dx.doi.org/10.1115/1.2888027.

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The purpose of this study was to determine the influence of blade geometric parameters such as pitch, twist, and taper on a blade’s sensitivity to leading edge roughness. The approach began with an evaluation of available test data of performance degradation due to roughness effects for several rotors. In addition to airfoil geometry, this evaluation suggested that a rotor’s sensitivity to roughness was also influenced by the blade geometric parameters. Parametric studies were conducted using the PROP93 computer code with wind tunnel airfoil characteristics for smooth and rough surface conditi

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5

Özgen, Serkan, Eda Bahar Sarıbel, and Ali Rıza Yaman. "Effect of blade contamination on power production of wind turbines." Journal of Physics: Conference Series 2265, no. 3 (2022): 032012. http://dx.doi.org/10.1088/1742-6596/2265/3/032012.

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Abstract Wind turbines suffer from considerable power losses because of contamination on their blades, that can be due to erosion, wear, smog, insect, sand and dust particle impact. Blade contamination, its effects on the flows over the wind turbine blades and consequent power production losses form the main focus of the present study. These effects are mainly due to increased roughness on the blades leading to earlier laminar-turbulent transition and consequently, thicker boundary-layers on the blades. Early laminar-turbulent transition leads to a larger part of the flow over a blade being tu

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6

Mulleners, K., P. Gilge, and S. Hohenstein. "Impact of Surface Roughness on the Turbulent Wake Flow of a Turbine Blade." Journal of Aerodynamics 2014 (December 30, 2014): 1–9. http://dx.doi.org/10.1155/2014/458757.

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Roughened aeroengine blade surfaces lead to increased friction losses and reduced efficiency of the individual blades. The surface roughness also affects the wake flow of the blade and thus the inflow conditions for the subsequent compressor or turbine stage. To investigate the impact of surface roughness on a turbulent blade wake, we conducted velocity field measurements by means of stereo particle image velocimetry in the wake of a roughened turbine blade in a linear cascade wind tunnel. The turbine blade was roughened at different chordwise locations. The influence of the chordwise location

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7

Gutiérrez, R., E. Llorente, and D. Ragni. "Induced stalled flow due to roughness sensitivity for thick airfoils in modern wind turbines." Journal of Physics: Conference Series 2151, no. 1 (2022): 012001. http://dx.doi.org/10.1088/1742-6596/2151/1/012001.

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Abstract The mid-span region of wind turbine blades can be thickened to fulfil the structural requirements of the blade. Hence, thick airfoils, that were designed to operate at the root region of the blade, are moved to the mid-span region. This could not imply remarkable variations of the blade performance once its surface is smooth. However, the sensitivity of thick airfoils to roughness could cause significant aerodynamic impacts such as flow separation. This research aims to quantify the impact of the blade thickness, under smooth and rough conditions, in the annual energy production and t

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8

Caccia, Francesco, and Alberto Guardone. "Numerical simulations of ice accretion on wind turbine blades: are performance losses due to ice shape or surface roughness?" Wind Energy Science 8, no. 3 (2023): 341–62. http://dx.doi.org/10.5194/wes-8-341-2023.

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Abstract. Ice accretion on wind turbine blades causes both a change in the shape of its sections and an increase in surface roughness. These lead to degraded aerodynamic performances and lower power output. Here, a high-fidelity multi-step method is presented and applied to simulate a 3 h rime icing event on the National Renewable Energy Laboratory 5 MW wind turbine blade. Five sections belonging to the outer half of the blade were considered. Independent time steps were applied to each blade section to obtain detailed ice shapes. The roughness effect on airfoil performance was included in com

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9

Gilge, Philipp, Andreas Kellersmann, Jens Friedrichs, and Jörg R. Seume. "Surface roughness of real operationally used compressor blade and blisk." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (2019): 5321–30. http://dx.doi.org/10.1177/0954410019843438.

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Deterioration of axial compressors is in general a major concern in aircraft engine maintenance. Among other effects, roughness in high-pressure compressor reduces the pressure rise and thus efficiency, thereby increasing the specific fuel consumption of an engine. Therefore, it is important to improve the understanding of roughness on compressor blading and their impact on compressor performance. To investigate the surface roughness of rotor blades of a compressors, different stages of an axial high-pressure compressor and a first-stage blisk (BLade–Integrated–dISK) of a regional aircraft eng

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10

Hamed, Awatef A., Widen Tabakoff, Richard B. Rivir, Kaushik Das, and Puneet Arora. "Turbine Blade Surface Deterioration by Erosion." Journal of Turbomachinery 127, no. 3 (2004): 445–52. http://dx.doi.org/10.1115/1.1860376.

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This paper presents the results of a combined experimental and computational research program to investigate turbine vane and blade material surface deterioration caused by solid particle impacts. Tests are conducted in the erosion wind tunnel for coated and uncoated blade materials at various impact conditions. Surface roughness measurements obtained prior and subsequent to the erosion tests are used to characterize the change in roughness caused by erosion. Numerical simulations for the three-dimensional flow field and particle trajectories through a low-pressure gas turbine are employed to

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11

Liu, Yue, Zhanqiang Liu, Wentong Cai, Yukui Cai, Bing Wang, and Guoying Li. "Optimisation of Planning Parameters for Machining Blade Electrode Micro-Fillet with Scallop Height Modelling." Micromachines 12, no. 3 (2021): 237. http://dx.doi.org/10.3390/mi12030237.

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Aero-engine blades are manufactured by electroforming process with electrodes. The blade electrode is usually machined with five-axis micromilling to get required profile roughness. Tool path planning parameters, such as cutting step and tool tilt angle, have a significant effect on the profile roughness of the micro-fillet of blade electrode. In this paper, the scallop height model of blade electrode micro-fillet processed by ball-end milling cutter was proposed. Effects of cutting step and tool tilt angle the machined micro-fillet profile roughness were predicted with the proposed scallop he

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12

Cai, Yong Lin, and Di Yao. "Research on Surface Roughness Experiment of Flank Milling for the Ruled Surface Blade." Advanced Materials Research 602-604 (December 2012): 2027–30. http://dx.doi.org/10.4028/www.scientific.net/amr.602-604.2027.

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In this paper, the factors affecting the surface roughness by flank milling are selected, and the blade machining experiments are implemented according to the orthogonal table designed, Then, the blade surface roughness are measured using TR200 instrument, and the surface roughness of the blade results are analyzed using visual analysis method and variance analysis method. Finally, the impact of various factors on the blade roughness is obtained, and the optimal process parameters of flank milling aluminum alloy blade are given.

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13

Nosov, Nicolay V. "Study of surface quality using quasi-optimal correlation algorithms." MATEC Web of Conferences 224 (2018): 01077. http://dx.doi.org/10.1051/matecconf/201822401077.

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The article proposes a new approach for evaluating roughness of the profile surface of gas turbine engine blade airfoils after vibratory polishing. An optical electronic unit was used to study microgeometry of blade suction and pressure sides: video imagery of the surface was processed using computer methods to obtain the average amplitude of the autocorrelation function variable component. The applied optical electronic method of evaluating microgeometry of compressor/turbine blades allows obtaining fields of surface roughness and tension concentration coefficients as well as analyzing the fi

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14

Suder, K. L., R. V. Chima, A. J. Strazisar, and W. B. Roberts. "The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor." Journal of Turbomachinery 117, no. 4 (1995): 491–505. http://dx.doi.org/10.1115/1.2836561.

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The performance deterioration of a high-speed axial compressor rotor due to surface roughness and airfoil thickness variations is reported. A 0.025 mm (0.001 in.) thick rough coating with a surface finish of 2.54–3.18 rms μm (100–125 rms μin.) is applied to the pressure and suction surface of the rotor blades. Coating both surfaces increases the leading edge thickness by 10 percent at the hub and 20 percent at the tip. Application of this coating results in a loss in efficiency of 6 points and a 9 percent reduction in the pressure ratio across the rotor at an operating condition near the desig

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15

Cai, Jin, Hao Wu, and Xihui Shi. "Effect of Ultrasonic Shot Peening on Morphology and Structure of NiCrAlYSi Coatings on Superalloys for Blade Applications." Coatings 14, no. 8 (2024): 949. http://dx.doi.org/10.3390/coatings14080949.

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The study evaluated and compared the surface morphology, roughness, and coating structure of ultrasonic shot peening (USP)-treated samples of the NiCrAlYSi-coated GH4169 alloy used for turbine blades and discussed the influence of blade-surface roughness and coating thickness on aerodynamic performance. The NiCrAlYSi coating was deposited on the surface of the alloy using electron beam-physical vapor deposition (EB-PVD), and the NiCrAlYSi bond coat was subsequently surface treated at Almen intensities of 0.1 A, 0.15 A, and 0.2 A by USP. The results following USP treatment indicated that the bo

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16

Degrazia, Felipe Weidenbach, Bruna Genari, Vilmar Antonio Ferrazzo, Ary dos Santos-Pinto, and Renésio Armindo Grehs. "Enamel Roughness Changes after Removal of Orthodontic Adhesive." Dentistry Journal 6, no. 3 (2018): 39. http://dx.doi.org/10.3390/dj6030039.

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The aim of this study was to evaluate enamel roughness, quality of the enamel surfaces and time duration comparing different orthodontic adhesive removal protocols. Premolars were used to test three adhesive removal methods (n = 20): five-blade carbide bur, 30-blade carbide bur, and ultrasonic diamond bur. Bracket was bonded using TransbondTM XT adhesive. Roughness with different parameters was measured before bracket bonding and after adhesive remnants removal. Micromorphological analysis of enamel surface (n = 5) was performed by SEM images and categorized in enamel damage index—“perfect”; “

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17

Wu, Han, Wangqiao Chen, Peng Zhou, et al. "Assessment and mitigation of the rotor noise for future urban air mobility vehicles." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 4 (2023): 4201–8. http://dx.doi.org/10.3397/in_2023_0595.

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Multi-rotor configurations are often adopted in urban air mobility (UAM) designs. The aerodynamic noise of rotors is a significant source of the UAM vehicles, requiring systematic measurements and mitigation. To this end, a large-scale test rig is designed and built to enable the acoustic measurement of UAM rotor blades. The test rig is placed in an anechoic chamber with the size of 8.1 m (L) × 6 m (W) × 5.1 m (H). The aerodynamic force and noise of a pair of custom-designed blades with a radius of 0.5 m are measured. The rotational speed ranges from 600 to 1800 revolutions per minute. A zig-z

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18

Gao, Hang, Z. Zhao, and Y. W. Sun. "Recent Development of the Aero-Engine Impeller and Blade Surface Polishing Technology." Advanced Materials Research 135 (October 2010): 7–12. http://dx.doi.org/10.4028/www.scientific.net/amr.135.7.

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The air compressing efficiency and heat conductance of aero-engine is markedly influenced by the surface micro-morphology and surface roughness of the impeller and blades, which will further affect the thrust weight ratio of plane. To achieve low flow losses, the roughness values of the impeller and blade surface must be below certain limits. Some polishing techniques as final finishing process of the impeller and blades are reviewed and their recent developments are shown in the paper. Further more a new kind of point-by-point NC polishing principle for aero-engine impeller surface, in which

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19

Mian, H. H., M. S. Siddiqui, L. Yang, T. Kvamsdal, and T. Asim. "Numerical investigation of blade roughness impact on the aerodynamic performance and wake behavior of horizontal axis wind turbine." Journal of Physics: Conference Series 2626, no. 1 (2023): 012073. http://dx.doi.org/10.1088/1742-6596/2626/1/012073.

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Abstract The prolonged operation of wind turbines in harsh offshore environments leads to deterioration and roughness accumulation on the blade surface. This roughness, particularly on the leading edge and other surfaces, can affect the laminar-to-turbulent transition, alter the flow characteristics in the turbine wake and turbulent boundary layer, and become critical for the accurate design and performance analysis of offshore horizontal axis wind turbines (HAWT). This study investigates the effects of blade surface roughness on the aerodynamic performance and wake evolution of the NREL Phase

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20

Taylor, R. P. "Surface Roughness Measurements on Gas Turbine Blades." Journal of Turbomachinery 112, no. 2 (1990): 175–80. http://dx.doi.org/10.1115/1.2927630.

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Results are presented from profilometer measurements of the surface roughness on in-service turbine engine blades from F-100 and TF-39 aeroengines. On each blade, one roughness profile is taken in the region of the leading edge, the midchord and the trailing edge on both the pressure and suction sides for a total of six profiles. Thirty first-stage turbine blades are measured from each engine. Statistical computations are performed on these profiles and the root mean square height, skewness and kurtosis of the roughness height distribution are presented along with the correlation length of the

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21

Gao, Limin, Panpan Tu, Guang Yang, and Song Yang. "Uncertainty Modeling of Fouling Thickness and Morphology on Compressor Blade." Aerospace 12, no. 6 (2025): 547. https://doi.org/10.3390/aerospace12060547.

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To describe the fouling characteristics of compressor blades, fouling is categorized into dense and loose layers to characterize thickness and rough structures. An uncertainty model for dense fouling layer thickness distribution is constructed using the numerical integration and the Karhunen–Loève (KL) expansion method, while the Fouling Longuet-Higgins (FLH) model is proposed to address the uncertainty of loose fouling layer roughness. The FLH model effectively simulates the morphology characteristics of actual blade fouling and elucidates how parameters influence fouling roughness, morpholog

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22

Han, Xu, Xiangyu Liu, Yunyun Yuan, and Zhonghe Han. "Effect of blade surface roughness on condensation process in a stator cascade." International Journal of Numerical Methods for Heat & Fluid Flow 30, no. 8 (2019): 4067–81. http://dx.doi.org/10.1108/hff-10-2019-0736.

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Purpose The flow state of wet steam will affect the thermodynamic and aerodynamic characteristics of steam turbine. The purpose of this study is to effectively control the wetness losses caused by wet steam condensation, and hence a cascade of 600 MW steam turbine was taken as the research object. Design/methodology/approach The influence of blade surface roughness on the condensation characteristics was analyzed, and the dehumidification mechanism and wetness control effect were obtained. Findings With the increase of blade surface roughness, the peak nucleation rate decreases gradually. Acco

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23

Qiu, Lei, Liangtao Qi, Lanlan Liu, Zhu Zhang, and Jianwei Xu. "The blade surface performance and its robotic machining." International Journal of Advanced Robotic Systems 17, no. 2 (2020): 172988142091409. http://dx.doi.org/10.1177/1729881420914090.

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Through numerical calculations, it could be found that when the blade surface quality reaches a certain level, the surface quality of the blade was continuously improved, and the guarantee effect on its performance would be weakened. Under this circumstance, continuing to improve the surface quality of the blade had no positive effect on the performance of the blade. Studies had shown that when the blade surface equivalent grit roughness Ks reaches 4.96 (about R a = 0.8 µm), the blade performance was close to the smooth surface of the blade, and no further processing was required to improve th

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Datsenko, Vadym. "Виявлення впливу шорсткості та радіального зазору на характеристику осьового багатоступеневого компресора". Aerospace Technic and Technology, № 3 (20 червня 2024): 51–58. http://dx.doi.org/10.32620/aktt.2024.3.04.

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The operation of gas turbine engines inevitably increases the blade roughness and tip clearance in multistage axial compressors. The result is an increase in its thermogasodynamic parameters. The reason for the increase in the roughness of the blades and the tip clearance can be various factors: clogging of the flow part of the compressor (adhesion and deposition of dust on the surface of the blades), erosion due to the arrival of hard sand grains in the flow part, etc. The subject of this study is thermogasodynamic processes in the flow part of a multistage axial compressor, based on the pres

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25

Li, Da Qi, Lei Zhang, Wei Dong Ye, and Hai Ying Zu. "Research on Path of Contact Wheel for Ruled Blade Grinding." Applied Mechanics and Materials 536-537 (April 2014): 1343–46. http://dx.doi.org/10.4028/www.scientific.net/amm.536-537.1343.

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Blade is one of the important components in aero-engine, turbine, and wind generators. The quality of the blades has big influence on the performance of the machine. So high profile accuracy and low surface roughness were put forward. Ruled blade is just one of the blades of aero-engine, which has simple profile and little distort. This blade was grinded by two sides together in the paper. Therefore, in this thesis, the main objects are as fallow: firstly, according to the characteristics of the abrasive belt grinding, analysis the selection of grinding distance for the blade. Secondly, establ

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Loboda, A. A., S. A. Mozgov, and B. P. Saushkin. "Electrochemical finishing of airfoil blade wheels." Izvestiya MGTU MAMI 7, no. 2-2 (2013): 251–57. http://dx.doi.org/10.17816/2074-0530-68287.

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The article describes the change in the basic manufacture technology of the blades closed blade wheels through the use of finishing operations to remove the defective layer and to reduce the surfaces roughness of the blades after electroerosive firmware operation. The efficiency of the new operation instead of the original is based on a manual finishing of blade profile was confirmed by experimental studies. The article describes the experiments on the selection of the optimum parameters of the processing and selection of the optimal electrolyte. It also shows the effect of various parameters

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SMAJIC, Selver, and Juraj JOVANOVIC. "INFLUENCE OF DIFFERENT MACHINING ON THE ROUGHNESS OF OAK WOOD." Series II: Forestry Wood Industry Agricultural Food Engineering 14(63), no. 1 (2021): 101–8. http://dx.doi.org/10.31926/but.fwiafe.2021.14.63.1.9.

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The paper presents research on the differences the in total roughness and the impact of parameters during different kinds of machining processes of oak samples. Oak wood samples were planed referring to a radial surface structure of wood. The planing machine was Weinig Unimat 500 and the planing head had two blades. The planing was conducted at a feed speed of 10, 15, 20, 25, and 30 m·min-1. The cutting depth of the machining grip was 1.00 mm and the rake angle of the tool blade was bio γ = 15°, at 6000°/min. The diameter of the cutting blade was Φ = 125 mm. Sanding was performed on a Viet Ope

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Boyle, R. J. "Prediction of Surface Roughness and Incidence Effects on Turbine Performance." Journal of Turbomachinery 116, no. 4 (1994): 745–51. http://dx.doi.org/10.1115/1.2929468.

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The use of a Navier–Stokes analysis to predict the change in turbine efficiency resulting from changes in blade surface roughness or incidence flow angles is discussed. The results of a midspan Navier–Stokes analysis are combined with those from a quasi-three-dimensional flow analysis code to predict turbine performance. A quasi-three-dimensional flow analysis code was used to determine turbine performance over a range of incidence flow angles. This analysis was done for a number of incidence loss models. The change in loss due to changes in incidence flow computed from the Navier–Stokes analy

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Zhang, Qinyi, Feng Liu, Dong Wu, Shikang Qu, Wei Liu, and Zhangxiao Chen. "A Comprehensive Understanding of Knife Cutting: Effects of Hardness, Blade Angle and the Micro-Geometry of Blade Edge on the Cutting Performance." Materials 16, no. 15 (2023): 5375. http://dx.doi.org/10.3390/ma16155375.

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The cutting performance of steel blades is an eternal, attractive topic in the knife industry. It is a complicated process to cut up materials because it usually involves the contact mechanics of the material been cut, the geometry and roughness of the blade edge and the hardness and wear resistance of the blade steel. Therefore, a comprehensive analysis is required to evaluate the cutting performance of knife blades. In this study, such an analysis was conducted based on a quantitative model to describe the cutting depth of paper cards containing SiO2 particles by steel blades, and major cont

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Ortolani, Andrea, Alessio Castorrini, and M. Sergio Campobasso. "Multi-scale Navier-Stokes analysis of geometrically resolved erosion of wind turbine blade leading edges." Journal of Physics: Conference Series 2265, no. 3 (2022): 032102. http://dx.doi.org/10.1088/1742-6596/2265/3/032102.

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Abstract A multi-scale computational fluid dynamics analysis of wind turbine blade leading edge erosion is presented. The test case is a large set of eroded blade sections. These are obtained by fitting the resolved eroded leading edge geometry of the outboard part of a multi-megawatt offshore wind turbine to the NACA633-618 airfoil. The erosion geometry measured by a blade laser scan is geometrically resolved in the aerodynamic simulations, whereas the aerodynamic effects of unresolved lower-amplitude scales are accounted for by using distributed surface roughness models. The simulations also

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Jafari, Kamyar, Mohammad Hassan Djavareshkian, and Behzad Forouzi Feshalami. "The Effects of Different Roughness Configurations on Aerodynamic Performance of Wind Turbine Airfoil and Blade." International Journal of Renewable Energy Development 6, no. 3 (2017): 273. http://dx.doi.org/10.14710/ijred.6.3.273-281.

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In this research, viscous and turbulent flow is simulated numerically on an E387 airfoil as well as on a turbine blade. The main objective of this paper is to investigate various configurations of roughness to find a solution in order to mitigate roughness destructive impacts. Hence, the sand grain roughness is distributed uniformly along pressure side, suction side and both sides during the manufacturing process. Navier-Stokes equations are discretized by the finite volume method and are solved by SIMPLE algorithm. Results indicated that in contrast with previous studies, the roughness will b

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Nielsen, Mikkel Schou, Ivan Nikolov, Emil Krog Kruse, Jørgen Garnæs, and Claus Brøndgaard Madsen. "High-Resolution Structure-from-Motion for Quantitative Measurement of Leading-Edge Roughness." Energies 13, no. 15 (2020): 3916. http://dx.doi.org/10.3390/en13153916.

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Over time, erosion of the leading edge of wind turbine blades increases the leading-edge roughness (LER). This may reduce the aerodynamic performance of the blade and hence the annual energy production of the wind turbine. As early detection is key for cost-effective maintenance, inspection methods are needed to quantify the LER of the blade. The aim of this proof-of-principle study is to determine whether high-resolution Structure-from-Motion (SfM) has the sufficient resolution and accuracy for quantitative inspection of LER. SfM provides 3D reconstruction of an object geometry using overlapp

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Hamed, A., W. Tabakoff, and D. Singh. "Modeling of Compressor Performance Deterioration Due to Erosion." International Journal of Rotating Machinery 4, no. 4 (1998): 243–48. http://dx.doi.org/10.1155/s1023621x98000207.

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This paper presents the results of a simulation of compressor performance deterioration due to blade erosion. The simulation at both design and off-design conditions is based on a mean line row by row model, which incorporates the effects of blade roughness and tip clearance. The results indicate a pronounced effect of blade erosion on the compressor adiabatic efficiency and a lesser effect on the pressure ratio. The loss in performance is mainly caused by the increased blade surface roughness and was highest at 100% speed.

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Huang, Yun, Ming Wei, GuiJian Xiao, and Shuai Liu. "Belt grinding method considering outer profile and inner wall thickness." Journal of Physics: Conference Series 2252, no. 1 (2022): 012024. http://dx.doi.org/10.1088/1742-6596/2252/1/012024.

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Abstract Increasing thrust-to-weight ratio is the goal pursued by aero-engines. Aero-engine blades are the core components of aero-engines. In order to reduce the weight and improve the thrust-to-weight ratio, the cavity structure is gradually applied to aero-engine blades. The constraints of the outer contour and the inner wall thickness of the cavity structure blade make its trajectory planning difficult, which seriously affects its surface roughness and profile accuracy. In this study, proposes a titanium alloy blade surface machining method based on belt grinding, which is constrained by t

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Huang, Yun, Ming Wei, GuiJian Xiao, and Shuai Liu. "Belt grinding method considering outer profile and inner wall thickness." Journal of Physics: Conference Series 2252, no. 1 (2022): 012024. http://dx.doi.org/10.1088/1742-6596/2252/1/012024.

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Abstract Increasing thrust-to-weight ratio is the goal pursued by aero-engines. Aero-engine blades are the core components of aero-engines. In order to reduce the weight and improve the thrust-to-weight ratio, the cavity structure is gradually applied to aero-engine blades. The constraints of the outer contour and the inner wall thickness of the cavity structure blade make its trajectory planning difficult, which seriously affects its surface roughness and profile accuracy. In this study, proposes a titanium alloy blade surface machining method based on belt grinding, which is constrained by t

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Egorov, Sergey, Alexey Kapitanov, Dmitriy Loktev, Sergey Fedorov, and Tatiana Egorova. "The Problems of Measuring Profile and Roughness of Turbine Blades." Applied Mechanics and Materials 876 (February 2018): 110–16. http://dx.doi.org/10.4028/www.scientific.net/amm.876.110.

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The article presents a study of a turbine blade profile and roughness measurement processes - the task facing any manufacturer of this part. The blade is one of the most complex regarding parts manufacture because of its complex profile. This profile should be measured in several sections on the feather on all profile elements - the suction side, pressure surface, leading and trailing edge of a blade. If the blade has a shroud platform, its profile should be also measured (and possibly the gland packing profile). It is also necessary to measure the feather end and base of blade profile. Finall

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Bishtawi, Basel Al, Gianfranco Scribano, and Manh-Vu Tran. "Numerical Study of Blade Roughness Effect on Cavitation in Centrifugal Pumps." Journal of Physics: Conference Series 2051, no. 1 (2021): 012047. http://dx.doi.org/10.1088/1742-6596/2051/1/012047.

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Abstract Cavitation is classified as an undesirable complex multiphase phenomenon due to its negative effects on the structural and flow behaviours of hydraulic machineries, specifically centrifugal pumps. Typically, the pump’s cavitation performance tends to vary due to a multitude of factors, one of which is the impeller blade roughness. In this study, a numerical analysis is conducted, using ANSYS Fluent 20.1, to evaluate the relationship between the impeller blade roughness and the cavitation performance of an ISO 80-50-250 centrifugal pump operating at different pressures and flow rates.

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Hasan, Muhammad Hasibul, and Shugata Ahmed. "Wear Resistance Performance of Conventional and Non-Conventional Wind Turbine Blades with TiN Nano-Coating." International Journal of Engineering Materials and Manufacture 2, no. 3 (2017): 37–48. http://dx.doi.org/10.26776/ijemm.02.03.2017.01.

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Efficiency and durability are critical issues that affect widely-adopted aerofoil-power generator as a sustainable source of electrical power. Even though high wind power density can be achieved; installing wind turbines in desert condition has difficulties including thermal variation, high turbulence and sand storms. Sand blasting on turbine blade surface at high velocities causes erosion resulting turbine efficiency drop. Damage-induced erosion phenomena and aeroelastic performance of the blades needed to be investigated. Suitable coating may prevent erosion to a great extent. A numerical in

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Nosov, N. V., N. P. Kostin, and R. V. Ladyagin. "Estimation of texture parameters for the precision surfaces using the quasioptimal correlation algorithms." Vektor nauki Tol'yattinskogo gosudarstvennogo universiteta, no. 1 (2021): 24–31. http://dx.doi.org/10.18323/2073-5073-2021-1-24-31.

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The authors considered a new method of texture analysis of machined precision surfaces based on using computer optics and the autocorrelation method of processing the images of micro-relief textures under the study. This method is based on a probabilistic comparative evaluation of the unknown texture of the micro-relief under the investigation with the available textures of reference micro-patterns, in which microrelief parameters are determined. The paper proposes an approach to identify the profile surface roughness of a gas turbine engine (GTE) blade after vibro-contact polishing according

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Livya, E., R. Abishaveni, M. D. Ashika Deepthi, P. Ranjitha, and S. Nadaraja Pillai. "Analyzing the aerodynamic characteristics of eroded wind turbine blades." IOP Conference Series: Earth and Environmental Science 1161, no. 1 (2023): 012015. http://dx.doi.org/10.1088/1755-1315/1161/1/012015.

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Abstract The study investigates the influence of erosion over the leading edge of S809 series airfoil and its impact on the aerodynamic performance of wind turbine blades. The research work determines how erosion affects the performance of wind turbine blades at an angle of attack varying from 0° to 45° for the fixed Reynolds number of 2.1 x 105. To analyse the flow characteristics, the average pressure acting around the surface of the airfoil is scanned with the aid of 20 pressure taps. The time series pressure of 10,000 samples at each point has been collected. The roughness is introduced at

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Vimalakanthan, Kisorthman, Harald van der Mijle Meijer, Iana Bakhmet, and Gerard Schepers. "Computational fluid dynamics (CFD) modeling of actual eroded wind turbine blades." Wind Energy Science 8, no. 1 (2023): 41–69. http://dx.doi.org/10.5194/wes-8-41-2023.

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Abstract. Leading edge erosion (LEE) is one of the most critical degradation mechanisms that occur with wind turbine blades (WTBs), generally starting from the tip section of the blade. A detailed understanding of the LEE process and the impact on aerodynamic performance due to the damaged leading edge (LE) is required to select the most appropriate leading edge protection (LEP) system and optimize blade maintenance. Providing accurate modeling tools is therefore essential. This paper presents a two-part study investigating computational fluid dynamics (CFD) modeling approaches for different o

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Vdovin, R. A. "Investigation of Uniformity of Allowance along Airfoil of GTE Turbine Blade." MATEC Web of Conferences 329 (2020): 03054. http://dx.doi.org/10.1051/matecconf/202032903054.

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This paper shows the results of a study of the uniformity of the allowance along the airfoil in the turbine blades workpieces. It is found that in the existing industry, there is a defect associated with a lack of allowance along the airfoil (from the blade back and pressure side) for the polishing operation in order to give the required cleanliness and roughness of the surface layer. By measuring the wall thickness of the blade airfoils, it is concluded that by mechanically modifying the technological bases on the blade, it is possible to select the optimal position of the workpiece in the te

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Kind, R. J., P. J. Serjak, and M. W. P. Abbott. "Measurements and Prediction of the Effects of Surface Roughness on Profile Losses and Deviation in a Turbine Cascade." Journal of Turbomachinery 120, no. 1 (1998): 20–27. http://dx.doi.org/10.1115/1.2841383.

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Measurements of pressure distributions, profile losses, and flow deviation were carried out on a planar turbine cascade in incompressible flow to assess the effects of partial roughness coverage of the blade surfaces. Spanwise-oriented bands of roughness were placed at various locations on the suction and pressure surfaces of the blades. Roughness height, spacing between roughness elements, and band width were varied. A computational method based on the inviscid/viscous interaction approach was also developed; its predictions were in good agreement with the experimental results. This indicates

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Moshizi, S. A., M. H. Nakhaei, M. J. Kermani, and A. Madadi. "Development of a Numerical Based Correlation for Performance Losses due to Surface Roughness in Axial Turbines." Journal of Mechanics 30, no. 6 (2014): 631–42. http://dx.doi.org/10.1017/jmech.2014.10.

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AbstractIn the present work, a recently developed in-house 2D CFD code is used to study the effect of gas turbine stator blade roughness on various performance parameters of a two-dimensional blade cascade. The 2D CFD model is based on a high resolution flux difference splitting scheme of Roe (1981). The Reynolds Averaged Navier-Stokes (RANS) equations are closed using the zero-equation turbulence model of Baldwin-Lomax (1978) and two-equation Shear Stress Transport (SST) turbulence model. For the smooth blade, results are compared with experimental data to validate the model. Finally, a corre

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Jarolmasjed, Seyedamin, Behnam Davoodi, and Babak Pourebrahim Alamdari. "Influence of milling toolpaths in machining of the turbine blade." Aircraft Engineering and Aerospace Technology 91, no. 10 (2019): 1327–39. http://dx.doi.org/10.1108/aeat-12-2018-0316.

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Purpose The purpose of this paper is to machine the pressure surface of the turbine blade made of A286 iron-based superalloy by using four directions of raster strategy, including horizontal upward, horizontal downward, vertical upward and vertical downward, to achieve appropriate surface roughness and to investigate the tool wear in each strategy. Design/methodology/approach In this study, all cutting tests were performed by DAHLIH-MCV 1020 BA vertical 3-axis machining center with ball nose end mill. After milling by each strategy, according to the surface slope, the surface was divided into

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Shi, Yameng, Baoqin Wen, Liqiao Li, et al. "Analysis of Wear Characteristics of Blade Materials and Glycyrrhiza uralensis." Transactions of the ASABE 64, no. 4 (2021): 1259–68. http://dx.doi.org/10.13031/trans.14442.

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HighlightsThe thermal reaction between Glycyrrhiza uralensis and metal was analyzed via thermogravimetry.The wear characteristics of three common blade metals were studied under laboratory conditions.The wear mechanisms on the blades by different parts of Glycyrrhiza uralensis were analyzed.Thermal oxidation and element transfer occurred during the wear of Glycyrrhiza uralensis and metals.Abstract. To investigate the wear of metal blades when kneading and crushing total mixed ration (TMR) forage grass, the chemical composition of licorice (Glycyrrhiza uralensis) was determined using hydrochlor

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Hummel, Frank, Michael Lötzerich, Pasquale Cardamone, and Leonhard Fottner. "Surface Roughness Effects on Turbine Blade Aerodynamics." Journal of Turbomachinery 127, no. 3 (2005): 453. http://dx.doi.org/10.1115/1.1860377.

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Sazonov, M. B., and L. V. Solovatskaya. "Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades." VESTNIK of Samara University. Aerospace and Mechanical Engineering 18, no. 1 (2019): 109–17. http://dx.doi.org/10.18287/2541-7533-2019-18-1-109-117.

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Different types of final strengthening treatment of gas turbine engine (GTD) compressor blades are considered. The influence of each type of treatment on the formation of roughness of the surface with favorable microrelief, as well as on the level and depth of distribution of residual compressive stresses in the compressor blade airfoil is analyzed. The causes of blade fatigue failure are described and methods of controlling this kind of failure are presented. The results of testing special specimens made of VT9 titanic alloy are presented to establish the influence of final strengthening trea

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Tanürün, Himmet Erdi, Ahmet Giray Akın, Adem Acır, and İzzet Şahin. "Experimental and Numerical Investigation of Roughness Structure in Wind Turbine Airfoil at Low Reynolds Number." International Journal of Thermodynamics 27, no. 3 (2024): 26–36. http://dx.doi.org/10.5541/ijot.1455513.

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This paper experimentally and numerically investigates the effects of suction side surface roughness on the aerodynamic performances of the NACA 0015 turbine blade profile. Three different NACA 0015 turbine blade configurations, which are smooth (K0), single roughness (K1), and double roughness (K2), are considered. The experimental studies were conducted using the HM-170 GUNT open wind tunnel model. The aerodynamic characteristics of these three blade configurations are evaluated in terms of their lift coefficient (CL), drag coefficient (CD), and aerodynamic efficiency (CL/CD). The maximum CL

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Khuengpukheiw, Ronnarit, Charnnarong Saikaew, and Anurat Wisitsoraat. "Wear resistance of HVOF sprayed NiSiCrFeB, WC-Co/NiSiCrFeB, WC-Co, and WC-Cr3C2-Ni rice harvesting blades." Materials Testing 63, no. 1 (2021): 62–72. http://dx.doi.org/10.1515/mt-2020-0009.

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Abstract In this work, NiSiCrFeB, WC-Co/NiSiCrFeB, WC-Co, and WC-Cr3C2-Ni coatings were sprayed on rice harvesting blade surfaces using a high velocity oxygen fuel (HVOF) process. Each of the rice harvesting blades was sprayed with one of four coating materials using different spraying durations. The effects of coating materials and spraying durations on the average values of coated blade volume loss, hardness and surface roughness (Ra) were studied through real rice-harvesting field tests. Analysis of variance (ANOVA) and a multiple comparison approach with Tukey’s test were used in order to

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