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Journal articles on the topic '"turbine blade tip rub"'

Author: Grafiati

Published: 4 June 2021

Last updated: 10 February 2022

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1

Padova, Corso, Jeffrey Barton, Michael G. Dunn, et al. "Development of an Experimental Capability to Produce Controlled Blade Tip∕Shroud Rubs at Engine Speed." Journal of Turbomachinery 127, no. 4 (2004): 726–35. http://dx.doi.org/10.1115/1.1934429.

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An experimental capability using an in-ground spin-pit facility specifically designed to investigate aeromechanic phenomena for gas turbine engine hardware rotating at engine speed is demonstrated herein to obtain specific information related to prediction and modeling of blade-casing interactions. Experiments are designed to allow insertion of a segment of engine casing into the path of single-bladed or multiple-bladed disks. In the current facility configuration, a 90deg sector of a representative engine casing is forced to rub the tip of a single-bladed compressor disk for a selected number

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2

Satish, TN, A. Vivek, SN Anagha, et al. "Novel resistor-capacitor (RC) network-based capacitance signal conditioning circuit for tip clearance measurement on gas turbine engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 2 (2019): 342–60. http://dx.doi.org/10.1177/0954410019865853.

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Blade tip clearance is a critical engine health parameter measured on gas turbines. Increase in tip clearance results in decreased efficiency, whereas with decrease in clearance due to thermal and centrifugal loads, rotor blades might rub the engine case. Various sensing techniques are being used, among them, capacitance-based systems are widely used by many engine houses. Among the capacitance conditioning circuits, resistor-capacitor series network-based circuits are simple to implement but pose many challenges during practical development. During the current work, the authors have designed

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3

Tong, Fujuan, Wenxuan Gou, Lei Li, Zhufeng Yue, Wenjing Gao, and Honglin Li. "Numerical investigation of high pressure turbine blade tip-shaping effects on the aerothermal and dynamic performance." Multidiscipline Modeling in Materials and Structures 15, no. 6 (2019): 1121–35. http://dx.doi.org/10.1108/mmms-03-2019-0053.

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Purpose In order to improve the engine reliability and efficiency, an effective way is to reform the turbine blade tip conformation. The paper aims to discuss this issue. Design/methodology/approach The present research provides several novel tip-shaping structures, which are considered to control the blade tip loss. Four different tip geometries have been studied: flat tip, squealer tip, flat tip with streamwise ribs and squealer tip with streamwise ribs. The tip heat transfer and leakage flow are both analyzed in detail, for example the tip heat transfer coefficient, tip flow and local press

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4

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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5

Jiang, Shijie, Zhigang Li, Jun Li, and Liming Song. "Effects of the novel rib layouts on the tip leakage flow pattern and heat transfer performance of turbine blade." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 8 (2020): 1446–59. http://dx.doi.org/10.1177/0954410020910883.

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The steady simulation with flow field and heat transfer performance for different rib layouts is investigated. By referring the GE-E3 turbine blade tip (Case 1) profile as a prototype model, four kinds of rib layouts of full rib structure (Case 2), half rib structure connected with suction side (Case 3), half rib structure connected with pressure side (Case 4), and half rib structure in the rear squealer cavity (Case 5) was designed. The availability of k-ω turbulence model was validated through comparison of heat transfer coefficient distribution with the experimental data. The area-averaged

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6

Lee, Byung Ju, Kun Sung Park, Jin Young Jeong, Jae Su kwak, and Jin Taek Chung. "Numerical Investigation on Effects of Rib or Cavity Design of Gas Turbine Blade Tip on the Flow and Heat Transfer Characteristics near Tip Region." KSFM Journal of Fluid Machinery 24, no. 3 (2021): 5–14. http://dx.doi.org/10.5293/kfma.2021.24.3.005.

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7

Sewall, Evan A., and Danesh K. Tafti. "Large Eddy Simulation of Flow and Heat Transfer in the 180‐Deg Bend Region of a Stationary Gas Turbine Blade Ribbed Internal Cooling Duct." Journal of Turbomachinery 128, no. 4 (2005): 763–71. http://dx.doi.org/10.1115/1.2098769.

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Large eddy simulation of the 180 deg bend in a stationary ribbed duct is presented. The domain studied includes three ribs upstream of the bend region and three ribs downstream of the bend with an outflow extension added to the end, using a total of 8.4 million cells. Two cases are compared to each other: one includes a rib in the bend and the other does not. The friction factor, mean flow, turbulence, and heat transfer are compared in the two cases to help explain the benefits and disadvantages of the wide number of flow effects seen in the bend, including flow separation at the tip of the di

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8

Zhang, Bo-lun, Hui-ren Zhu, Chun-yi Yao, and Cun-liang Liu. "Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade." International Journal of Heat and Mass Transfer 176 (September 2021): 121408. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2021.121408.

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9

Hong, Jie, Tianrang Li, Zhichao Liang, Dayi Zhang, and Yanhong Ma. "Research on Blade-Casing Rub-Impact Mechanism by Experiment and Simulation in Aeroengines." Shock and Vibration 2019 (April 22, 2019): 1–15. http://dx.doi.org/10.1155/2019/3237960.

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Aeroengines pursue high performance, and compressing blade-casing clearance has become one of the main ways to improve turbomachinery efficiency. Rub-impact faults occur frequently with clearance decreasing. A high-speed rotor-support-casing test rig was set up, and the mechanism tests of light and heavy rub-impact were carried out. A finite element model of the test rig was established, and the calculation results were in good agreement with the experimental results under both kinds of rub-impact conditions. Based on the actual blade-casing structure model, the effects of the major physical p

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10

Sheard, A. G. "Blade by Blade Tip Clearance Measurement." International Journal of Rotating Machinery 2011 (2011): 1–13. http://dx.doi.org/10.1155/2011/516128.

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This paper describes a capacitance-based tip clearance measurement system which engineers have used in the most demanding turbine test applications. The capacitance probe has survived extended use in a major European gas turbine manufacturer's high-temperature demonstrator unit, where it functioned reliably at a turbine entry temperature in excess of 1800 degrees Kelvin. This paper explores blade by blade tip clearance measurement techniques and examines probe performance under laboratory conditions in support of high-temperature installations. The paper outlines the blade by blade tip clearan

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11

Zhao, T. Y., H. Q. Yuan, B. B. Li, Z. J. Li, and L. M. Liu. "Analytical Solution for Rotational Rub-Impact Plate Under Thermal Shock." Journal of Mechanics 32, no. 3 (2016): 297–311. http://dx.doi.org/10.1017/jmech.2016.19.

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AbstractThe analysis method is developed to obtain dynamic characteristics of the rotating cantilever plate with thermal shock and tip-rub. Based on the variational principle, equations of motion are derived considering the differences between rubbing forces in the width direction of the plate. The transverse deformation is decomposed into quasi-static deformation of the cantilever plate with thermal shock and dynamic deformation of the rubbing plate under thermal shock. Then deformations are obtained through the calculation of modal characteristics of rotating cantilever plate and temperature

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12

Padovan, J., and F. K. Choy. "Nonlinear Dynamics of Rotor/Blade/Casing Rub Interactions." Journal of Turbomachinery 109, no. 4 (1987): 527–34. http://dx.doi.org/10.1115/1.3262143.

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This paper considers the transient analysis of rub problems in high-speed rotating equipment that involve interactions between the rotor, blades, and casing. Special emphasis is given to ascertaining the participation characteristics of turbine/impeller blades during the overall rub event. To generalize the scope of the work, single and multiple blade rub events are considered including the effect of such system parameters as imbalance magnitude, blade/rotor stiffness, system damping, and rub interface friction characteristics.

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13

Cao, Dengqing, Xiaochun Gong, Dong Wei, Shiming Chu, and Ligang Wang. "Nonlinear Vibration Characteristics of a Flexible Blade with Friction Damping due to Tip-Rub." Shock and Vibration 18, no. 1-2 (2011): 105–14. http://dx.doi.org/10.1155/2011/425039.

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An approximate approach is proposed in this paper for analyzing the two-dimensional friction contact problem so as to compute the dynamic response of a structure constrained by friction interfaces due to tip-rub. The dynamical equation of motion for a rotational cantilever blade in a centrifugal force field is established. Flow-induced distributed periodic forces and the internal material damping in the blade are accounted for in the governing equation of motion. The Galerkin method is employed to obtain a three-degree-of-freedom oscillator with friction damping due to tip-rub. The combined mo

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14

Xue, Song, and Wing Ng. "Turbine Blade Tip External Cooling Technologies." Aerospace 5, no. 3 (2018): 90. http://dx.doi.org/10.3390/aerospace5030090.

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This article provides an overview of gas turbine blade tip external cooling technologies. It is not the intention to comprehensively review all the publications from past to present. Instead, selected reports, which represent the most recent progress in tip cooling technology in open publications, are reviewed. The cooling performance on flat tip and squealer tip blades from reports are compared and discussed. As a generation conclusion, tip clearance dimension and coolant flow rate are found as the most important factors that significant influence the blade tip thermal performance was well as

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15

Padova, Corso, Jeffery Barton, Michael G. Dunn, and Steve Manwaring. "Experimental Results From Controlled Blade Tip/Shroud Rubs at Engine Speed." Journal of Turbomachinery 129, no. 4 (2006): 713–23. http://dx.doi.org/10.1115/1.2720869.

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Experimental results obtained for an Inconel® compressor blade rubbing a steel casing at engine speed are described. Load cell, strain gauge, and accelerometer measurements are discussed and then applied to analyze the metal-on-metal interaction resulting from sudden incursions of varying severity, defined by incursion depths ranging from 13μm to 762μm (0.0005in. to 0.030in.). The results presented describe the transient dynamics of rotor and casing vibro-impact response at engine operational speed similar to those experienced in flight. Force components at the blade tip in axial and circumfer

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16

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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17

Jiang, Hai Bo. "Lift Performance of Wind Turbine with Blade Tip Loss." Advanced Materials Research 971-973 (June 2014): 569–72. http://dx.doi.org/10.4028/www.scientific.net/amr.971-973.569.

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Blade tip losses would reduce lift and power of wind turbine. This paper analyzed the mechanism of tip losses, and according to Prandtl and Glauert tip loss correction factor and blade element - momentum theory derived the blade chord formula with tip losses. Further, lift coefficient calculation formula was obtained by integrating along the blade span. The lift coefficient formula considering tip loss expressed the highest value of lift coefficient of any practical wind turbine with tip losses. The research shows, the impacts of tip losses to chord concentrated in the tip area; tip losses wil

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18

Wang, Hao, Bing Ma, and Jiao Jiao Ding. "The Analysis of the Flutter Region of Wind Turbine Blade." Applied Mechanics and Materials 423-426 (September 2013): 1520–23. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.1520.

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As the wind turbine blade is becoming larger and larger, the flutter of the wind turbine blade has been paid great attention by many fields. The flutter region of the wind turbine blade airfoil was focused on. The equation of motion for the flutter of blade airfoil was established, based on the simplified aerodynamic force and torque. The flutter analysis of wind turbine blade was carried out with the four-order Runge-Kutta methods, and so the flutter region of the blade airfoil can be obtained. The results show that, there are two critical tip speed ratios for the given blade airfoil. When th

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19

Christophel, J. R., K. A. Thole, and F. J. Cunha. "Cooling the Tip of a Turbine Blade Using Pressure Side Holes—Part I: Adiabatic Effectiveness Measurements." Journal of Turbomachinery 127, no. 2 (2005): 270–77. http://dx.doi.org/10.1115/1.1812320.

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Durability of turbine blade tips has been and continues to be challenging, particularly since increasing turbine inlet temperatures is the driver for improving turbine engine performance. As a result, cooling methods along the blade tip are crucial. Film-cooling is one typically used cooling method whereby coolant is supplied through holes placed along the pressure side of a blade. The subject of this paper is to evaluate the adiabatic effectiveness levels that occur on the blade tip through blowing coolant from holes placed near the tip of a blade along the pressure side. A range of blowing r

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20

Prasad, Anil, and Joel H. Wagner. "Unsteady Effects in Turbine Tip Clearance Flows." Journal of Turbomachinery 122, no. 4 (2000): 621–27. http://dx.doi.org/10.1115/1.1314608.

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The present study is concerned with the unsteady flow field on the blade outer air seal segments of high-work turbines; these segments are installed between the blade tip and outer casing and are usually subjected to extreme heat loads. Time-resolved measurements of the unsteady pressure on the blade outer air seal are made in a low-speed turbine rig. The present measurements indicate the existence of a separation zone on the blade tip, which causes a vena contracta to form at the entrance of the tip gap. In addition, a careful comparison between the ensemble-averaged pressure measurement and

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21

Dahal, Chiranjivi, Janak Kumar Tharu, and Hari Bahadur Dura. "Thermo-Structural Analysis of High-Pressure Turbine Blade." Journal of the Institute of Engineering 15, no. 3 (2020): 78–82. http://dx.doi.org/10.3126/jie.v15i3.32018.

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Turbine blade tip clearance plays major role in smooth running of axial turbines. The turbine blade clearance contributes 20-40% of total loss in gas turbine. In Rolls Royce MT2 Turbine with 2% tip to span clearance ratio, tip clearance accounts for 40% of total losses. Turbine blade clearance is necessary as the turbine blade operates at very high temperature up to 1700 ºC and very high centrifugal load. Small turbine tip clearance may forbid expansion of turbine blade which will result in turbine tip rubbing with the casing. High pressure turbine blade experiences high thermal and cent

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22

Pan, Yang, Qi Yuan, Gongge Huang, Guangyu Zhu, and Pu Li. "Numerical analysis of the aerodynamic performance and excitation forces in a transonic turbine cascade with flat-tip and squealer-tip blades." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 234, no. 22 (2020): 4377–89. http://dx.doi.org/10.1177/0954406220922275.

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The purpose of this paper is to numerically investigate the effect of blade tip clearance and its structure on the turbine aerodynamic performance and excitation force on blades in a transonic turbine cascade. Hence, circular cascades with flat-tip and squealer-tip blades and eight different tip clearances based on the SNECMA transonic turbine were established and the rotational effect was taking into consideration. The simulations were performed by solving the RANS equations and the SST turbulence model was used. The results show that tip clearance and tip structure have a significant influen

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23

Ferrer, E., and X. Munduate. "Wind turbine blade tip comparison using CFD." Journal of Physics: Conference Series 75 (July 1, 2007): 012005. http://dx.doi.org/10.1088/1742-6596/75/1/012005.

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24

Piechowski, L., R. Rzadkowsk, P. Troka, P. Piechowski, L. Kubitz, and R. Szczepanik. "Tip-Timing Steam Turbine Rotor Blade Simulator." Journal of Vibration Engineering & Technologies 6, no. 4 (2018): 317–23. http://dx.doi.org/10.1007/s42417-018-0041-4.

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25

Azad, Gm S., Je-Chin Han, Shuye Teng, and Robert J. Boyle. "Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip." Journal of Turbomachinery 122, no. 4 (2000): 717–24. http://dx.doi.org/10.1115/1.1308567.

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Heat transfer coefficient and static pressure distributions are experimentally investigated on a gas turbine blade tip in a five-bladed stationary linear cascade. The blade is a two-dimensional model of a first-stage gas turbine rotor blade with a blade tip profile of a GE-E3 aircraft gas turbine engine rotor blade. The flow condition in the test cascade corresponds to an overall pressure ratio of 1.32 and exit Reynolds number based on axial chord of 1.1×106. The middle 3-blade has a variable tip gap clearance. All measurements are made at three different tip gap clearances of about 1, 1.5, an

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26

Ma, Yue, Bing Qian, Zhiguo Feng, et al. "Flow behaviors in a Kaplan turbine runner with different tip clearances." Advances in Mechanical Engineering 13, no. 5 (2021): 168781402110158. http://dx.doi.org/10.1177/16878140211015879.

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Tip clearance between the runner blade tip and shroud in a Kaplan turbine is inevitable, and the tip leakage flow (TLF) and tip leakage vortex (TLV) induced by the tip clearance have a considerable effect on the flow behaviors. To reveal the effect of the tip clearance on the flow characteristics, based on the Reynolds time-averaged Navier-Stokes (N-S) equation and the shear stress transfer (SST) k-ω turbulence model, the three-dimensional turbulence flow in a Kaplan turbine is simulated using ANSYS CFX. Meanwhile, the flow laws in the tip clearance are emphatically analyzed and summarized. Re

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27

Balda, Miroslav, and Olga Červená. "Residual Fatigue Lives of Steam Turbine Blades." Applied Mechanics and Materials 827 (February 2016): 121–24. http://dx.doi.org/10.4028/www.scientific.net/amm.827.121.

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The paper deals with an assessment of blade tip movements based on precise time measurement known under abbreviation BTT - Blade Tip Timing. In addition to the common way of BTT data processing, a new Residual Fatigue Lives of Blades system (RFLB) proceeds further up to estimation of blade damages by processing output files generated by BTT systems.

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28

Jin, Jiahui, Yanping Song, Jianyang Yu, and Fu Chen. "Effect of arbitrary blade tip design on tip leakage flow." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 1 (2019): 19–30. http://dx.doi.org/10.1177/0957650919848171.

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Tip geometry modification is frequently used to suppress the tip leakage flow in the turbine cascade however a universally beneficial tip geometry modification design has not been fully discovered. In this paper, the two-surface coupling arbitrary blade tip design method in three-dimensional physical space which satisfies the simple trigonometric function law is proposed and the mathematical parametric description is presented. The effects of different arbitrary blade tips on tip leakage flow have been studied numerically in a highly loaded axial turbine cascade. The aerodynamic performance of

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29

Teng, Shuye, Je-Chin Han, and G. M. S. Azad. "Detailed Heat Transfer Coefficient Distributions on a Large-Scale Gas Turbine Blade Tip." Journal of Heat Transfer 123, no. 4 (2000): 803–9. http://dx.doi.org/10.1115/1.1373655.

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Measurements of detailed heat transfer coefficient distributions on a turbine blade tip were performed in a large-scale, low-speed wind tunnel facility. Tests were made on a five-blade linear cascade. The low-speed wind tunnel is designed to accommodate the 107.49 deg turn of the blade cascade. The mainstream Reynolds number based on cascade exit velocity was 5.3×105. Upstream unsteady wakes were simulated using a spoke-wheel type wake generator. The wake Strouhal number was kept at 0 or 0.1. The central blade had a variable tip gap clearance. Measurements were made at three different tip gap

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30

Kim, Y. W., and D. E. Metzger. "Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models." Journal of Turbomachinery 117, no. 1 (1995): 12–21. http://dx.doi.org/10.1115/1.2835630.

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In unshrouded axial turbine stages, a small but generally unavoidable clearance between the blade tips and the stationary outer seal allows a clearance gap leakage flow to be driven across the blade tip by the pressure-to-suction side pressure difference. In modern high-temperature machines, the turbine blade tips are often a region prone to early failure because of the presence of hot gases in the gap and the resultant added convection heating that must be counteracted by active blade cooling. The blade tip region, particularly near the trailing edge, is often very difficult to cool adequatel

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31

Jin, Jiahui, Yanping Song, Jianyang Yu, and Fu Chen. "Modification and optimization strategies for turbine arbitrary blade tips." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 233, no. 6 (2019): 675–88. http://dx.doi.org/10.1177/0957650919826326.

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The influence of different arbitrary blade tip shapes on restraining the tip leakage flow in a highly loaded turbine cascade has been numerically studied. A combined method of establishing and optimizing the arbitrary blade tip shape is proposed by using B-spline surface modeling, Kriging model and genetic optimization algorithm. The results show that the Kriging model established by the B-spline surface modeling method can accurately fit the relationship between the arbitrary blade tip shape and the relevant aerodynamic parameters. The optimal leakage mass flow tip and the optimal total press

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32

Zhou, Zhihua, Shaowen Chen, and Songtao Wang. "Unsteady winglet-cavity tip on leakage flow in a high-pressure turbine stage of low-aspect ratio." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 232, no. 20 (2017): 3708–21. http://dx.doi.org/10.1177/0954406217741517.

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In an unshrouded high-pressure turbine, the upstream vane wake, vane–blade interaction and blade tip leakage flow indicate complex and unsteady flow characteristics. Considering a high-pressure turbine stage of low-aspect ratio, the effects of the flat tip, cavity tip and winglet-cavity tip on the unsteady flow characteristics are investigated by numerical simulation. The exit Mach number and Reynolds number based on the chord of vane are 0.9 and 5.5×105, respectively. The pressure ratio of stage is 2.4. The time-resolved results indicate that the winglet-cavity tip scheme has smaller time var

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33

Yu, Hyeon Tak, Byung Hyun Ahn, Jong Myeong Lee, Jeong Min Ha, and Byeong Keun Choi. "Study on Rub Vibration of Rotary Machine for Turbine Blade Diagnosis." Transactions of the Korean Society for Noise and Vibration Engineering 26, no. 6_spc (2016): 714–20. http://dx.doi.org/10.5050/ksnve.2016.26.6.714.

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34

Langston, Lee S. "Blade Tips - Clearance and Its Control." Mechanical Engineering 135, no. 08 (2013): 66–71. http://dx.doi.org/10.1115/1.2013-aug-4.

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This article focuses on studying blade tip clearance phenomena. It is important to realize that to be freely turning, a blade (or a cantilevered stator) must have a clearance gap between its tip and the engine casing (or hub). Such clearances introduce aerodynamic losses, decreasing gas turbine efficiency. Tip leakage losses in compressors can be significant and have been reviewed by the experts. During transient operations, gas turbine blade tip clearances will change based on blade/disk centrifugal loads and the different response times of engine parts to thermally induced expansions and con

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35

Zhou, Jun Wei, and Da Zheng Wang. "Parametric Study of Crowned Blade in Horizontal Axial Turbine." Advanced Materials Research 732-733 (August 2013): 443–50. http://dx.doi.org/10.4028/www.scientific.net/amr.732-733.443.

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The horizontal axial turbine could extract kinetic energy from both wind and tidal stream. In this paper, a type of horizontal axial turbine was designed with a crown stalled on the blade tip and the turbine was analyzed in a tidal stream. Several turbines with different geometries of the crowns were compared, whose power coefficients were numerically simulated by the CFD method. Effects of the crown design parameters, such as crown setting directions and different widths on turbine efficiency were discussed. Furthermore, when the turbine worked at different tip speed ratio, the results were d

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36

Gao, Xiang, Jun Hu, and Zhi Qiang Wang. "PIV Experiment on Near Wake Flow of Horizontal Axis Wind Turbine." Advanced Materials Research 718-720 (July 2013): 1811–15. http://dx.doi.org/10.4028/www.scientific.net/amr.718-720.1811.

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A three-dimensional horizontal axis wind turbine model was experimentally studied. The experiment was carried out in a laboratory wind tunnel. With PIV measurement, details about flow fields in the near wakeof the turbine blade were obtained. The result shows vortices generateon the tailing edge of the blade, and propagatedownstream then dissipate into small vortices. Vortices also generate at the tip of the blade, propagate downstream and along the radial direction then dissipate. The dissipation of the tip vortex is slower than the former. We also find that the wake of turbine blade rotates

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37

Yu, Kua Hai, Liu Xian Hu, Xi Yang, and Zhu Feng Yue. "Influence of Tip Injection and Film Cooling for Blade Tip Flow and Heat Transfer." Applied Mechanics and Materials 117-119 (October 2011): 643–46. http://dx.doi.org/10.4028/www.scientific.net/amm.117-119.643.

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A numerical based study was conducted to further understanding of turbine tip leakage and flow mechanisms for squealer tip blade. Three blade geometry models with different tips are established. They are squealer tip blade, squealer tip with injection holes blade, squealer tip with injection and film cooling holes blade, separately. Coupled aerodynamic and heat transfer numerical simulation method is used to study blade tip flow and heat transfer based the whole blade computational model. The results show that tip coolant injection will perform a positive effect for the resisting tip leakage,

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38

Metzger, D. E., M. G. Dunn, and C. Hah. "Turbine Tip and Shroud Heat Transfer." Journal of Turbomachinery 113, no. 3 (1991): 502–7. http://dx.doi.org/10.1115/1.2927902.

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Unshrouded blades of axial turbine stages move in close proximity to the stationary outer seal, or shroud, of the turbine housing. The pressure difference between the concave and convex sides of the blade drives a leakage flow through the gap between the moving blade tip and adjacent wall. This clearance leakage flow and accompanying heat transfer are of interest because of long obvious effects on aerodynamic performance and structural durability, but understanding of its nature and influences has been elusive. Previous studies indicate that the leakage through the gap is mainly a pressure-dri

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39

Jin, P., and R. J. Goldstein. "Local Mass and Heat Transfer on a Turbine Blade Tip." International Journal of Rotating Machinery 9, no. 2 (2003): 81–95. http://dx.doi.org/10.1155/s1023621x03000083.

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Local mass and heat transfer measurements on a simulated high-pressure turbine blade-tip surface are conducted in a linear cascade with a nonmoving tip endwall, using a naphthalene sublimation technique. The effects of tip clearance (0.86–6.90% of chord) are investigated at various exit Reynolds numbers (4–7 ×105) and turbulence intensities (0.2 and 12.0%).The mass transfer on the tip surface is significant along its pressure edge at the smallest tip clearance. At the two largest tip clearances, the separation bubble on the tip surface can cover the whole width of the tip on the second half of

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Dishart, P. T., and J. Moore. "Tip Leakage Losses in a Linear Turbine Cascade." Journal of Turbomachinery 112, no. 4 (1990): 599–608. http://dx.doi.org/10.1115/1.2927700.

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An investigation of tip leakage flow and its effects on loss production was performed on a large-scale linear turbine cascade having a tip gap measuring 2.1 percent of the blade height. The flow exiting the tip gap was measured to determine the losses incurred within the tip gap and the secondary kinetic energy due to tip leakage. Additional measurements, 40 percent of an axial chord downstream of the blade trailing edges, showed the development of the leakage flow and the overall cascade losses. At the downstream location, the additional loss due to tip leakage was found to be the sum of the

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Azad, Gm S., Je-Chin Han, and Robert J. Boyle. "Heat Transfer and Flow on the Squealer Tip of a Gas Turbine Blade." Journal of Turbomachinery 122, no. 4 (2000): 725–32. http://dx.doi.org/10.1115/1.1311284.

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Experimental investigations are performed to measure the detailed heat transfer coefficient and static pressure distributions on the squealer tip of a gas turbine blade in a five-bladed stationary linear cascade. The blade is a two-dimensional model of a modern first-stage gas turbine rotor blade with a blade tip profile of a GE-E3 aircraft gas turbine engine rotor blade. A squealer (recessed) tip with a 3.77 percent recess is considered here. The data on the squealer tip are also compared with a flat tip case. All measurements are made at three different tip gap clearances of about 1, 1.5, an

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Thorpe, S. J., S. Yoshino, G. A. Thomas, R. W. Ainsworth, and N. W. Harvey. "Blade-tip heat transfer in a transonic turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 219, no. 6 (2005): 421–30. http://dx.doi.org/10.1243/095765005x31171.

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Clifton-Smith, M. J. "Wind Turbine Blade Optimisation with Tip Loss Corrections." Wind Engineering 33, no. 5 (2009): 477–96. http://dx.doi.org/10.1260/030952409790291226.

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Martinez-Sanchez, M., B. Jaroux, S. J. Song, and S. Yoo. "Measurement of Turbine Blade-Tip Rotordynamic Excitation Forces." Journal of Turbomachinery 117, no. 3 (1995): 384–92. http://dx.doi.org/10.1115/1.2835673.

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This paper presents results of a program to investigate the magnitude, origin, and parametric variations of destabilizing forces that arise in high power turbines due to blade-tip leakage effects. Five different unshrouded turbine configurations and one configuration shrouded with a labyrinth seal were tested with static offsets of the turbine shaft. The forces along and perpendicular to the offset were measured directly with a dynamometer, and were also inferred from velocity triangles and pressure distributions obtained from detailed flow surveys. These two routes yielded values in fair agre

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BUNKER, RONALD S. "A Review of Turbine Blade Tip Heat Transfer." Annals of the New York Academy of Sciences 934, no. 1 (2006): 64–79. http://dx.doi.org/10.1111/j.1749-6632.2001.tb05843.x.

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Rhee, Dong-Ho, and Hyung Hee Cho. "Local Heat/Mass Transfer Characteristics on a Rotating Blade With Flat Tip in Low-Speed Annular Cascade—Part I: Near-Tip Surface." Journal of Turbomachinery 128, no. 1 (2005): 96–109. http://dx.doi.org/10.1115/1.2098756.

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The present study focuses on local heat/mass transfer characteristics on the near-tip region of a rotating blade. To investigate the local heat/mass transfer on the near-tip surface of the rotating turbine blade, detailed measurements of time-averaged mass transfer coefficients on the blade surfaces were conducted using a naphthalene sublimation technique. A low speed wind tunnel with a single stage annular turbine cascade was used. The turbine stage is composed of sixteen guide plates and blades with spacing of 34 mm, and the chord length of the blade is 150 mm. The mean tip clearance is abou

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Kwak, Jae Su, and Je-Chin Han. "Heat Transfer Coefficients on the Squealer Tip and Near Squealer Tip Regions of a Gas Turbine Blade." Journal of Heat Transfer 125, no. 4 (2003): 669–77. http://dx.doi.org/10.1115/1.1571849.

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Detailed heat transfer coefficient distributions on a squealer tip of a gas turbine blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Tests were performed on a five-bladed linear cascade with a blow-down facility. The blade was a two-dimensional model of a first stage gas turbine rotor blade with a profile of a GE-E3 aircraft gas turbine engine rotor blade. The Reynolds number based on the cascade exit velocity and axial chord len

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Jin, P., and R. J. Goldstein. "Local Mass/Heat Transfer on Turbine Blade Near-Tip Surfaces." Journal of Turbomachinery 125, no. 3 (2003): 521–28. http://dx.doi.org/10.1115/1.1554410.

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Local mass transfer measurements on a simulated high-pressure turbine blade are conducted in a linear cascade with tip clearance, using a naphthalene sublimation technique. The effects of tip clearance (0.86–6.90% of chord) are investigated at an exit Reynolds number of 5.8×105 and a low turbulence intensity of 0.2%. The effects of the exit Reynolds number 4−7×105 and the turbulence intensity (0.2 and 12.0%) are also measured for the smallest tip clearance. The effect of tip clearance on the mass transfer on the pressure surface is limited to 10% of the blade height from the tip at smaller tip

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Kwak, Jae Su, and Je-Chin Han. "Heat Transfer Coefficients and Film Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade." Journal of Turbomachinery 125, no. 4 (2003): 648–57. http://dx.doi.org/10.1115/1.1622712.

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Experimental investigations were performed to measure the detailed heat transfer coefficients and film cooling effectiveness on the squealer tip of a gas turbine blade in a five-bladed linear cascade. The blade was a two-dimensional model of a first stage gas turbine rotor blade with a profile of the GE-E3 aircraft gas turbine engine rotor blade. The test blade had a squealer (recessed) tip with a 4.22% recess. The blade model was equipped with a single row of film cooling holes on the pressure side near the tip region and the tip surface along the camber line. Hue detection based transient li

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Winarto, Eko Wismo, Sugiyanto Sugiyanto, Soeadgihardo Siswantoro, and Isworo Djati. "Turbin Hibrid Bi-Directional Sebagai Pemanen Energi pada Thermoacoustic Engine." Jurnal Rekayasa Mesin 12, no. 1 (2021): 19. http://dx.doi.org/10.21776/ub.jrm.2021.012.01.3.

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Bi-directional turbines that are commonly applied to convert wave energy into motion energy are the types of Impulse turbines and Wells turbines. Both types of turbines each have advantages and disadvantages. In this research, hybrid turbine type is designed and made to bridge the weaknesses in impulse turbine and turbine wells. Hybrid turbines are made by placing impulse turbines on the outside while turbine wells placed on the inside. In this research, the variation of hybrid bi-directional turbine design aims to find out the most optimal design of this turbine type. Six variations were carr

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