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Journal articles on the topic 'Tip-loss'

Author: Grafiati

Published: 4 June 2021

Last updated: 8 February 2022

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1

Mehta, Atul C., Joseph A. Golish, and Douglas R. Livingston. "Loss of Fiberoptic Laser Tip." Chest 88, no. 5 (1985): 798. http://dx.doi.org/10.1378/chest.88.5.798a.

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2

Hansen, Martin O. L., and Jeppe Johansen. "Tip studies using CFD and comparison with tip loss models." Wind Energy 7, no. 4 (2004): 343–56. http://dx.doi.org/10.1002/we.126.

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3

Yoo, Myung Chul, Jin Hwan Ahn, Duke Whan Chung, Byung Ho Kim, and Dong Chul Oh. "Neurovascular Island Graft for Finger Tip Loss." Journal of the Korean Orthopaedic Association 21, no. 1 (1986): 95. http://dx.doi.org/10.4055/jkoa.1986.21.1.95.

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4

Wood, D. H., V. L. Okulov, and D. Bhattacharjee. "Direct calculation of wind turbine tip loss." Renewable Energy 95 (September 2016): 269–76. http://dx.doi.org/10.1016/j.renene.2016.04.017.

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5

Shen, Wen Zhong, Robert Mikkelsen, Jens Nørkær Sørensen, and Christian Bak. "Tip loss corrections for wind turbine computations." Wind Energy 8, no. 4 (2005): 457–75. http://dx.doi.org/10.1002/we.153.

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6

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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7

Ishida, M., H. Ueki, and Y. Senoo. "Effect of Blade Tip Configuration on Tip Clearance Loss of a Centrifugal Impeller." Journal of Turbomachinery 112, no. 1 (1990): 14–18. http://dx.doi.org/10.1115/1.2927412.

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According to the theory presented by the authors, the tip clearance loss of an un-shrouded centrifugal impeller mainly consists of two kinds of loss; one is the drag due to the leakage flow through the blade tip clearance and the other is the pressure loss to support the fluid in the thin annular clearance space between the shroud and the blade tip against the pressure gradient in the meridional plane without blades. The former is proportional to the leakage flow or the contraction coefficient of leakage flow. The authors have conducted performance tests using an impeller with 16 backward-lean

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8

ISHIDA, Masahiro, Hironobu UEKI, and Yasutoshi SENOO. "Effect of blade tip configuration on tip clearance loss of a centrifugal impeller." Transactions of the Japan Society of Mechanical Engineers Series B 53, no. 491 (1987): 2099–103. http://dx.doi.org/10.1299/kikaib.53.2099.

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9

Shen, Wen Zhong, Jens Nørkær Sørensen, and Robert Mikkelsen. "Tip Loss Correction for Actuator/Navier–Stokes Computations." Journal of Solar Energy Engineering 127, no. 2 (2005): 209–13. http://dx.doi.org/10.1115/1.1850488.

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A new tip loss correction, initially developed for 1D Blade Element/Momentum (BEM) computations (submitted to Wind Energy), is now extended to 2D Actuator Disc/Navier–Stokes (AD/NS) computations and 3D Actuator Line/Navier–Stokes (AL/NS) computations. In the paper, it is shown that the tip loss correction is an important and necessary step for actuator/Navier–Stokes models. Computed results are compared to experimental data and to results from BEM computations using the new tip correction as well as the original one of Glauert (Aerodynamic Theory, Dover, New York, Chap. VII, Div. L, pp. 251–26

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10

Storer, J. A., and N. A. Cumpsty. "An Approximate Analysis and Prediction Method for Tip Clearance Loss in Axial Compressors." Journal of Turbomachinery 116, no. 4 (1994): 648–56. http://dx.doi.org/10.1115/1.2929457.

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A simple model for loss created by the tip clearance flow in axial compressors is presented, based on an experimental program performed in conjunction with the Dawes three-dimensional Navier–Stokes calculation method. The principal mechanism of loss (entropy creation) caused by tip leakage flow has been established to be the mixing of flows of similar speeds but different direction. Calculations show that relative motion of the endwall relative to the tip has a small effect on clearance flow. The simple model correctly predicts the magnitude of tip clearance loss and the trend with changes of

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11

Li, Hui, Xinrong Su, and Xin Yuan. "Entropy Analysis of the Flat Tip Leakage Flow with Delayed Detached Eddy Simulation." Entropy 21, no. 1 (2018): 21. http://dx.doi.org/10.3390/e21010021.

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In unshrouded turbine rotors, the tip leakage vortices develop and interact with the passage vortices. Such complex leakage flow causes the major loss in the turbine stage. Due to the complex turbulence characteristics of the tip leakage flow, the widely used Reynolds Averaged Navier–Stokes (RANS) approach may fail to accurately predict the multi-scale turbulent flow and the related loss. In order to effectively improve the turbine efficiency, more insights into the loss mechanism are required. In this work, a Delayed Detached Eddy Simulation (DDES) study is conducted to simulate the flow insi

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12

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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13

Peters, David A., and Yih‐Wan Chiu. "Technical Note: Extension of Classical Tip Loss Formulas." Journal of the American Helicopter Society 34, no. 2 (1989): 68–71. http://dx.doi.org/10.4050/jahs.34.68.

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14

Bindon, J. P. "The Measurement and Formation of Tip Clearance Loss." Journal of Turbomachinery 111, no. 3 (1989): 257–63. http://dx.doi.org/10.1115/1.3262264.

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The detailed development of tip clearance loss from the leading to trailing edge of a linear turbine cascade was measured and the contributions made by mixing, internal gap shear flow, and endwall/ secondary flow were identified, separated, and quantified for the first time. Only 13 percent of the overall loss arises from endwall/secondary flow and of the remaining 87 percent, 48 percent is due to mixing and 39 percent is due to internal gap shear. All loss formation appears to be dominated by phenomena connected with the gap separation bubble. Flow established within the bubble by the pressur

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15

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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16

El-Batsh, Hesham M., and Magdy Bassily Hanna. "An Investigation on the Effect of Endwall Movement on the Tip Clearance Loss Using Annular Turbine Cascade." International Journal of Rotating Machinery 2011 (2011): 1–11. http://dx.doi.org/10.1155/2011/489150.

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The aerodynamic losses in gas turbines are mainly caused by profile loss secondary flow, and tip leakage loss. This study focuses on tip leakage flow of high-pressure turbine stages. An annular turbine cascade was constructed with fixed blades on the casing, and the distance between blade tip and the hub was considered as tip clearance gap. The effect of endwall movement on loss mechanism was investigated by using experimental and numerical techniques. The measurements were obtained while the hub was fixed but the numerical calculations were carried out for both stationary and moving cascades.

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17

Ye, Shubo, Qingjun Zhao, Weiwei Cui, Guang Xi, and Jianzhong Xu. "An improved model for tip clearance loss in transonic axial compressors." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 4 (2017): 295–314. http://dx.doi.org/10.1177/0957650917736453.

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An improved compressible model for estimating tip clearance loss in transonic compressors is presented with the emphasis on the effects of blade tip loading distribution and double leakage flow. Tip clearance flow is treated as three parts along the chord and the progressive relations from upstream to downstream part is revealed to be responsible for the formation of tip clearance flow. Control volume method is applied to simplify the mixing process and calculate the mixed-out loss for the three parts, separately. Computational study shows that mass flow of the incoming flow entering the contr

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18

Stawarz, Melissa, Cynthia Jackson, Lian Wang, and Joanne Ransom. "Human Milk Fat Loss Is Strongly Affected by Syringe Position During Tube Feeding in the NICU Population." Current Developments in Nutrition 4, Supplement_2 (2020): 1084. http://dx.doi.org/10.1093/cdn/nzaa054_156.

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Abstract Objectives Human milk is the recommended feeding for preterm infants. It is a dynamic, non-homogenized fluid. The most variable component is the fat content, which rapidly separates out when milk is allowed to sit. Fat from human milk is thought to adhere to the plastic syringe and tubing products used to administer tube feedings. The objective of this study was to identify best practices for tube feeding preterm infants to minimize nutrient loss from human milk during administration in the Neonatal Intensive Care Unit (NICU). Methods A study was conducted to investigate the effect of

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19

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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20

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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21

Xiao, Xinwen, Andrew A. McCarter, and Budugur Lakshminarayana. "Tip Clearance Effects in a Turbine Rotor: Part I—Pressure Field and Loss." Journal of Turbomachinery 123, no. 2 (2000): 296–304. http://dx.doi.org/10.1115/1.1368365.

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This paper presents an experimental investigation of the effects of the tip clearance flow in an axial turbine rotor. The effects investigated include the distribution and the development of the pressure, the loss, the velocity, and the turbulence fields. These flow fields were measured using the techniques of static pressure taps, rapid response pressure probes, rotating five-hole probes, and Laser Doppler Velocimeter. Part I of this paper covers the loss development through the passage, and the pressure distribution within the passage, on the blade surfaces, on the blade tip, and on the casi

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22

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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23

Zhong, Wei, Tong Guang Wang, Wei Jun Zhu, and Wen Zhong Shen. "Evaluation of Tip Loss Corrections to AD/NS Simulations of Wind Turbine Aerodynamic Performance." Applied Sciences 9, no. 22 (2019): 4919. http://dx.doi.org/10.3390/app9224919.

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The Actuator Disc/Navier-Stokes (AD/NS) method has played a significant role in wind farm simulations. It is based on the assumption that the flow is azimuthally uniform in the rotor plane, and thus, requires a tip loss correction to take into account the effect of a finite number of blades. All existing tip loss corrections were originally proposed for the Blade-Element Momentum Theory (BEMT), and their implementations have to be changed when transplanted into the AD/NS method. The special focus of the present study is to investigate the performance of tip loss corrections combined in the AD/

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24

Chen, Shaowen, Zhihua Zhou, Qinghe Meng, Songtao Wang, and Xun Zhou. "Experiment study of the winglet-cavity tip on the aerodynamic performance in a turbine cascade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 231, no. 7 (2017): 676–85. http://dx.doi.org/10.1177/0957650917720560.

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The effects of a novel winglet-cavity tip on the flow field and aerodynamic performance of a turbine blade with tip clearance have been investigated in a low-speed wind tunnel. A calibrated five-hole probe is used for the measurement of three-dimensional flows downstream of the cascade. The method of oil-flow visualization is used to show the endwall flow field structure. The distribution of endwall static pressure is measured particularly by using the special moveable endwall. The downstream results show that, compared with the flat tip and cavity tip, the winglet-cavity tip reduces aerodynam

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25

Zhou, Zhihua, Shaowen Chen, and Songtao Wang. "Aerodynamic optimisation of a winglet-cavity tip in a high-pressure axial turbine cascade." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 4 (2016): 649–63. http://dx.doi.org/10.1177/0954410016683735.

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Tip clearance flow between rotating blades and the stationary casing in high-pressure turbines is very complex and is one of the most important factors influencing turbine performance. The rotor with a winglet-cavity tip is often used as an effective method to improve the loss resulting from the tip clearance flow. In this study, an aerodynamic geometric optimisation of a winglet-cavity tip was carried out in a linear unshrouded high-pressure axial turbine cascade. For the purpose of shaping the efficient winglet geometry of the rotor tip, a novel parameterisation method has been introduced in

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26

Cheon, Joo Hong, and Sang Woo Lee. "Winglet geometry effects on tip leakage loss over the plane tip in a turbine cascade." Journal of Mechanical Science and Technology 32, no. 4 (2018): 1633–42. http://dx.doi.org/10.1007/s12206-018-0318-2.

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27

Zeng, Fei, Weihao Zhang, Yufan Wang, Xia Cao, and Zhengping Zou. "Effects of Squealer Geometry of Turbine Blade Tip on the Tip-Leakage Flow and Loss." Journal of Thermal Science 30, no. 4 (2021): 1376–87. http://dx.doi.org/10.1007/s11630-021-1488-2.

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28

Shen, W. Z., W. J. Zhu, and J. N. Sørensen. "Study of tip loss corrections using CFD rotor computations." Journal of Physics: Conference Series 555 (December 16, 2014): 012094. http://dx.doi.org/10.1088/1742-6596/555/1/012094.

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29

Kim, Byung Nam, and Myung Kyoon Chung. "Improvement of Tip Leakage Loss Model for Axial Turbines." Journal of Turbomachinery 119, no. 2 (1997): 399–401. http://dx.doi.org/10.1115/1.2841126.

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30

Senoo, Y. "Mechanics on the Tip Clearance Loss of Impeller Blades." Journal of Turbomachinery 113, no. 4 (1991): 680–85. http://dx.doi.org/10.1115/1.2929134.

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For predicting the tip clearance loss of turbomachines, different equations are published in the literature based on different principles. In 1986 the present author postulated a new theory where the pressure loss consisted of two parts: the pressure loss induced by the drag force of the leaked flow, and the pressure loss to support the axial pressure difference without blades in the tip clearance zone. It has been suggested that the two losses were the same loss looked from two different viewpoints, or at least apart of the former was included in the latter or vice versa. In this paper the pr

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31

Bindon, J. P., and G. Morphis. "The Development of Axial Turbine Leakage Loss for Two Profiled Tip Geometries Using Linear Cascade Data." Journal of Turbomachinery 114, no. 1 (1992): 198–203. http://dx.doi.org/10.1115/1.2927985.

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To assess the possibility of tip clearance loss reduction and to explore the nature and origin of tip clearance loss, blade tip geometries that reduce the roughly 40 percent of total loss occurring within the gap were studied. The shapes investigated aimed at reducing or avoiding the gap separation bubble thought to contribute significantly to both internal gap loss and to the endwall mixing loss. It was found that radiusing and contouring the blade at gap inlet eliminated the separation bubble and reduced the internal gap loss but created a higher mixing loss to give almost unchanged overall

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32

Morphis, G., and J. P. Bindon. "The Flow in a Second-Stage Nozzle of a Low-Speed Axial Turbine and Its Effect on Tip Clearance Loss Development." Journal of Turbomachinery 117, no. 4 (1995): 571–77. http://dx.doi.org/10.1115/1.2836569.

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The flow field in a one-and-a-half-stage low-speed axial turbine with varying levels of rotor tip clearance was measured in order to compare the behavior of the second nozzle with the first and to identify the manner in which the second nozzle responds to the complex tip clearance dependent flow presented to it and completes the formation of tip clearance loss. The tangentially averaged flow relative to the rotor blade in the tip clearance region was found to differ radically from that found in cascade and is not underturned with a high axial velocity. There is evidence rather of overturning c

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33

Senoo, Y., and M. Ishida. "Deterioration of Compressor Performance Due to Tip Clearance of Centrifugal Impellers." Journal of Turbomachinery 109, no. 1 (1987): 55–61. http://dx.doi.org/10.1115/1.3262070.

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The authors’ theory on the tip-clearance loss of centrifugal impellers is modified to include the variation of slip coefficient of the impeller due to the tip clearance, by deriving a rational relationship between two empirical parameters in the theory. In order to compare experimental data in the literature with prediction, examination was made regarding accuracy of available data and the way to select corresponding flow rates of a compressor with different values of tip clearance. Good agreement between data and prediction was observed. These examples demonstrate the following tendency regar

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34

Xu, Zhi Hui, He Bin Lv, and Ru Bin Zhao. "Numerical Investigation of Tip Clearance Flow in an Axial Compressor Cascade." Applied Mechanics and Materials 599-601 (August 2014): 368–71. http://dx.doi.org/10.4028/www.scientific.net/amm.599-601.368.

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Using blade tip winglet to control the tip leakage flow has been concerned in the field of turbomachinery. Computational simulation was conducted to investigate the phenomenological features of tip clearance flow. The simulation results show that suction-side winglet can reduce leakage flow intensity. The tip winglet can also decrease tip leakage mass flow and weaken tip leakage flow mixing with the mainstream and therefore reduce the total pressure loss at the blade tip.

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35

Chen, Shaowen, Qinghe Meng, Weihang Li, Zhihua Zhou, and Songtao Wang. "Experimental study on axially non-uniform clearances in a linear turbine cascade with a cavity squealer tip." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 5 (2018): 1645–55. http://dx.doi.org/10.1177/0954410018759837.

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The effects of axially non-uniform clearances on the tip leakage flow and aerodynamic performance in a linear turbine cascade with a cavity squealer tip were investigated in this study with the objective of improving the flow loss and tip flow field structure. A calibrated five-hole probe was used for the measurement of three-dimensional flows downstream of the cascade. The method of oil-flow visualization was used to show the endwall flow field structure. The distribution of endwall static pressure was measured particularly by using the special moveable endwall. The axially non-uniform cleara

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36

Kaneko, Masanao. "Influences of groove-type casing treatment on the tip leakage flow behaviour in linear compressor cascades at different tip clearances: influence of single groove at mid-chord." ACTA IMEKO 10, no. 1 (2021): 277. http://dx.doi.org/10.21014/acta_imeko.v10i1.874.

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In this study, the influences of the single groove installed at the mid-chord – which is known to have a large expansion effect on the stable operating flow range of low-speed axial compressors – on the flow behaviour and the loss generation in a linear compressor cascade were investigated numerically at different tip clearances. Reynolds-averaged Navier–Stokes simulations of the incompressible flow in the test cascade were performed, with the computed results clarifying the following remarkable phenomena, which are common to both small and large tip-clearance cases. The single groove locally

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37

Cao, Lihua, Heyong Si, Jiaxin Wang, and Pan Li. "Effects of leakage vortex on aerodynamic performance and loss mechanism of steam turbine." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 233, no. 7 (2019): 866–76. http://dx.doi.org/10.1177/0957650919831916.

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To avoid friction, a clearance between the rotor blade tip and the cylinder is needed in a steam turbine. As a result, the leakage flow is formed under the pressure difference which mixes with the main flow and causes the mixing loss. So, a numerical calculation was conducted based on a high-pressure 1.5-stage steam turbine with the tip labyrinth seal. The leakage vortex system and the mixing progress at different tip clearances were analyzed. The related leakage losses were calculated. The results show that the leakage flow will lead to the steam deflecting at the rotor exit and cause inciden

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38

Qin, Denghui, Guang Pan, Qiaogao Huang, Zhengdong Zhang, and Jiujiu Ke. "Numerical Investigation of Different Tip Clearances Effect on the Hydrodynamic Performance of Pumpjet Propulsor." International Journal of Computational Methods 15, no. 05 (2018): 1850037. http://dx.doi.org/10.1142/s0219876218500378.

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Previous studies show that the tip clearance loss limits the improvement of turbomachinery performance, and it is roughly in close relation with the gap size. In this study, a pumpjet propulsor (PJP) with different sizes of tip clearances ([Formula: see text], 0.5, 1, 2, 3[Formula: see text]mm) has been presented to investigate the influence of tip clearances on PJP. This analysis is based on computational fluid dynamic (CFD) method, and the SST k-[Formula: see text] turbulence model is applied. Calculations are carried out with a worldwide employed ducted propeller (the Ka4-70 propeller in 19

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39

Kavurmacioglu, Levent, Hidir Maral, Cem Berk Senel, and Cengiz Camci. "Performance of Partial and Cavity Type Squealer Tip of a HP Turbine Blade in a Linear Cascade." International Journal of Aerospace Engineering 2018 (May 2, 2018): 1–11. http://dx.doi.org/10.1155/2018/3262164.

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Three-dimensional highly complex flow structure in tip gap between blade tip and casing leads to inefficient turbine performance due to aerothermal loss. Interaction between leakage vortex and secondary flow structures is the substantial source of that loss. Different types of squealer tip geometries were tried in the past, in order to improve turbine efficiency. The current research deals with comparison of partial and cavity type squealer tip concepts for higher aerothermal performance. Effects of squealer tip have been examined comprehensively for an unshrouded HP turbine blade tip geometry

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40

Farokhi, Saeed. "Analysis of rotor tip clearance loss in axial-flow turbines." Journal of Propulsion and Power 4, no. 5 (1988): 452–57. http://dx.doi.org/10.2514/3.23087.

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41

Zarzour, J. F., D. W. Yuan, and M. J. Kleinosky. "Loss of crack-tip constraints for shallow cracks in bending." Journal of Materials Engineering and Performance 2, no. 6 (1993): 867–72. http://dx.doi.org/10.1007/bf02645687.

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42

Li, Hui, Xinrong Su, and Xin Yuan. "Analysis of the relationship between turbulence characteristics and loss mechanism in the tip leakage flow of turbine blade." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1302–14. http://dx.doi.org/10.1177/09576509211032077.

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The tip leakage flow passed over the tip clearance makes the flow very complicated near the tip gap, and the interaction of the tip leakage vortex and endwall vortex enhances the instability of the flow. Accurately capturing detailed flow structures and investigating the relationship between the flow structures and loss are beneficial for understanding the flow physics and providing guidance on reducing the loss. Due to the conventional Reynolds Averaged Navier-Stokes (RANS) methods is limited to predict the complex turbulence structures of the tip clearance flow, high fidelity simulation appr

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43

Zhang, Botao, Bo Liu, Hejian Wang, and Xiaochen Mao. "Effect of endwall suction on aerodynamic performance of compressor cascade with tip clearance at a large incidence angle." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1332–43. http://dx.doi.org/10.1177/0957650920983957.

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In order to deeply analyze the application prospect of the boundary layer suction technique on the compressor, the flow control effect of endwall suction scheme on the tip leakage flow of a compressor cascade at a large incidence angle with complex internal flow structure and different loss proportion from the case at design incidence angle, was studied numerically, as well as on the overall aerodynamic performance. The results show that the suction scheme directly affects the structure of the tip leakage flow and makes the onset position of the tip leakage vortex move backward, which weakens

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44

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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Harvey, Neil W., and Ken Ramsden. "A Computational Study of a Novel Turbine Rotor Partial Shroud." Journal of Turbomachinery 123, no. 3 (2000): 534–43. http://dx.doi.org/10.1115/1.1370166.

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The over tip leakage (OTL) flow that exists between the stationary casing and the rotor tip of a shroudless HP turbine remains a major source of loss of performance for modern aero gas turbines. To date the principal approaches to reducing OTL loss have been to minimize the clearance gap and/or apply a rotating shroud to the rotor. Tip clearance control systems continue to improve, but a practical limit on tip gap remains. A rotating shroud is highly effective but increases the rotor weight, forcing it to run more slowly and thus increasing other aerodynamic losses. Additional means of reducin

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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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Matsunuma, Takayuki. "Effects of Reynolds Number and Freestream Turbulence on Turbine Tip Clearance Flow." Journal of Turbomachinery 128, no. 1 (2005): 166–77. http://dx.doi.org/10.1115/1.2103091.

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Tip clearance losses represent a major efficiency penalty of turbine blades. This paper describes the effect of tip clearance on the aerodynamic characteristics of an unshrouded axial-flow turbine cascade under very low Reynolds number conditions. The Reynolds number based on the true chord length and exit velocity of the turbine cascade was varied from 4.4×104 to 26.6×104 by changing the velocity of fluid flow. The freestream turbulence intensity was varied between 0.5% and 4.1% by modifying turbulence generation sheet settings. Three-dimensional flow fields at the exit of the turbine cascade

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Wu, Wanyang, and Jingjun Zhong. "Experimental investigation of the influence on compressor cascade characteristics at high subsonic speed with pressure surface tip winglets." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 235, no. 6 (2021): 1257–71. http://dx.doi.org/10.1177/0957650921990198.

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To investigate the influence of tip winglets on the tip leakage flow in a compressor cascade with different incidences, the experimental measurement combined with numerical simulation are used to study the conventional cascade and cascades with three different pressure surface tip winglets at five incidences of −6°, −3°, 0°, +3° and +6°. The results indicate that three different tip winglets at five incidences all restrain the occurrence of leakage flow, delay the mixing of leakage flow and the mainstream, change the formation path of leakage vortex and weaken its intensity, reduce the flow lo

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Lu, Hanan, Qiushi Li, Tianyu Pan, and Ramesh Agarwal. "Analysis and application of shroud wall optimization to an axial compressor with upstream boundary layer to improve aerodynamic performance." International Journal of Numerical Methods for Heat & Fluid Flow 29, no. 11 (2019): 4237–61. http://dx.doi.org/10.1108/hff-01-2019-0071.

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PurposeFor an axial-flow compressor rotor, the upstream inflow conditions will vary as the aircraft faces harsh flight conditions (such as taking off, landing or maneuvering) or the whole compressor operates at off-design conditions. With the increase of upstream boundary layer thickness, the rotor blade tip will be loaded and the increased blade load will deteriorate the shock/boundary layer interaction and tip leakage flows, resulting in high aerodynamic losses in the tip region. The purpose of this paper is to achieve a better flow control for tip secondary flows and provide a probable desi

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Younoussi, Somaya, and Abdeslem Ettaouil. "Design and optimization of a small horizontal axis wind turbine using BEM theory and tip loss corrections." E3S Web of Conferences 294 (2021): 01003. http://dx.doi.org/10.1051/e3sconf/202129401003.

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In this paper, an optimization approach of a small horizontal axis wind turbine based on BEM theory including De Vries and Shen et al. tip loss corrections is proposed. The optimal blade geometry was obtained by maximizing the power coefficient along the blade using the optimal angle of attack and the optimal tip speed ratio. The Newton’s iterative method applied to axial induction factor was used to solve the problem. This study was conducted for a NACA4418 small wind turbine, at low wind velocity. Among the two used tip loss corrections, the De Vries correction was found to be the most suita

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