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Relevant bibliographies by topics / Tip Vortexes

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Academic literature on the topic 'Tip Vortexes'

Author: Grafiati

Published: 3 June 2025

Last updated: 31 July 2025

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Journal articles on the topic "Tip Vortexes"

1

Li, Pan, Lihua Cao, Heyong Si, and Wenlong Wang. "Investigation on the unsteady pressure fluctuation characteristic in the blade tip seal of steam turbine based on spectrum." Thermal Science 24, no. 6 Part A (2020): 3823–34. http://dx.doi.org/10.2298/tsci190308053l.

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The paper presents the unsteady numerical simulation results of tip leakage flow in high pressure steam turbines, and also presents the influence analysis of leakage vortexes on pressure fluctuation characteristics of rotor cascade under different blade tip seal clearances. The numerical method for calculating is based on the large eddy simulation turbulence model and the pressure fluctuation of rotor cascade which induced by the unstable leakage vortexes is obtained by frequency spectrum analysis. The results show that the vortex frequencies in tip seal cavity contain both the wheel rotating

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2

Cui, Hongjiang, Shenghui Wu, and Ying Guan. "Analysis of Trailing Vortex Structure and Turbulent Features of High-Speed Train in Vacuum Pipeline." International Journal of Heat and Technology 39, no. 5 (2021): 1601–8. http://dx.doi.org/10.18280/ijht.390523.

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Through the improved delay-detached eddy simulation (IDDES), this paper establishes a 1:1 model for a high-speed train, and simulates the transient state of the train running 600km/h in a vacuum pipeline with the pressure of 1,000Pa. The results show that, following the Ω criteria, a pair of counterrotating vortexes can be captured, which alternatively shed near the tip of the last carriage, and propagate over a long distance along the flow direction. The motion and expansion of the vortexes are clearly three-dimensional (3D). Judging by the physical meaning of vortexes, the high vorticity vor

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3

Jiang, Bin, Xiangtong Shi, Qun Zheng, Qingfang Zhu, Zhongliang Chen, and Zhitao Tian. "The Relationship of Spike Stall and Hub Corner Separation in Axial Compressor." International Journal of Turbo & Jet-Engines 37, no. 1 (2020): 1–16. http://dx.doi.org/10.1515/tjj-2016-0046.

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AbstractThe onset of spike stall induced by the interaction of hub corner separation flow with the tip leakage flow is investigated in detail by numerical method in this paper. The time resolved results indicate that the remarkable radial secondary flow from hub to tip near the trailing edge is formed when the compressor approaching rotating stall. The radial secondary flow is unstable and cross-passages propagates, which flows in and away out of the tip region periodically. The disturbance caused by radial secondary flow will influence the tip leakage flow directly by reforming the vortexes i

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4

Yi, Mei, and Qu Jianjun. "Numerical Study of Flow Field and Aerodynamic Performance of Straight Bladed VAWT at Variable Tip Speed Ratios." Open Mechanical Engineering Journal 9, no. 1 (2015): 1017–24. http://dx.doi.org/10.2174/1874155x01509011017.

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This paper studies the relationship between unsteady flow features and instantaneous torque and power performance of straight bladed vertical axis wind turbine at variable tip speed ratios. The rotor unsteady flow field simulation was carried out by using computational fluid dynamics method. The flow physics and the principle of changing flow field acting on torque performance and power performance have been analyzed where the rotating rotor was the major concern. The results show that the flow feature alters from periodical blade dynamic stall vortexes generation, development and shedding at

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5

Zhong, Fangpan, and Chao Zhou. "Tip gap size effects on thermal performance of cavity-winglet tips in transonic turbine cascade with endwall motion." Journal of the Global Power and Propulsion Society 1 (June 27, 2017): CR5JBC. http://dx.doi.org/10.22261/cr5jbc.

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AbstractThe thermal performance of two cavity-winglet tips with endwall motion is investigated in a transonic high pressure turbine cascade, which operates at an engine representative exit Mach number of 1.2 and an exit Reynolds number of 1.7 × 106. The numerical method is first validated with experimental data and then used to investigate blade heat transfer at three different tip clearances of 1.1, 2.1 and 3.1% chord. The effects of relative endwall motion are considered. The present results show that as the size of the tip gap increases, the heat transfer coefficient and heat load on the ti

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6

Zhang, Mingming, and Anping Hou. "Investigation on the Flow Field Entropy Structure of Non-Synchronous Blade Vibration in an Axial Turbocompressor." Entropy 22, no. 12 (2020): 1372. http://dx.doi.org/10.3390/e22121372.

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In order to explore the inducing factors and mechanism of the non-synchronous vibration, the flow field structure and its formation mechanism in the non-synchronous vibration state of a high speed turbocompressor are discussed in this paper, based on the fluid–structure interaction method. The predicted frequencies fBV (4.4EO), fAR (9.6EO) in the field have a good correspondence with the experimental data, which verify the reliability and accuracy of the numerical method. The results indicate that, under a deviation in the adjustment of inlet guide vane (IGV), the disturbances of pressure in t

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7

Mei, Yi, Jian Jun Qu, and Xiao Ya Liu. "Numerical Study of Vertical Axis Wind Turbine Rotor Configuration." Advanced Materials Research 859 (December 2013): 28–32. http://dx.doi.org/10.4028/www.scientific.net/amr.859.28.

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This paper presents a numerical study of a vertical axis wind rotor configuration. Below constant wind condition 8m/s, rotor power performance was investigated over variable turbine configurations. Illustrated by the simulation, increasing rotor cord to radius ratio or blade numbers will enhance the generation of vortexes and flow separation on blades, leading to the significant degradation of turbine performance. It can be conclude form the numerical analysis, a vertical axis wind turbine with high height to radius ratio applied in urban areas experienced better performance when operating in

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8

Bertetta, Daniele, Stefano Brizzolara, Edward Canepa, Stefano Gaggero, and Michele Viviani. "EFD and CFD Characterization of a CLT Propeller." International Journal of Rotating Machinery 2012 (2012): 1–22. http://dx.doi.org/10.1155/2012/348939.

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In the present paper an experimental and numerical analysis of an unconventional CLT propeller is carried out. Two different numerical approaches, a potential panel method and an RANSE solver, are employed. Cavitation tunnel experiments are carried out in order to measure, as usual, thrust, torque, and cavity extension for different propeller working points. Moreover, LDV measurements are performed to have a deep insight into the complex wake behind the propeller and to analyze the dynamics of generated tip vortexes. The numerical/experimental analysis and comparison of results highlight the p

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9

Wang, Junjie, XinFeng Zhang, and Jiaxin Lu. "Aerodynamic Interaction Characteristics Study of the Ducted Coaxial Propeller for a Novel eVTOL in Hovering." International Journal of Aerospace Engineering 2023 (October 3, 2023): 1–15. http://dx.doi.org/10.1155/2023/8098307.

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The ducted coaxial propeller (DCP) is highly advantageous in the design of eVTOL aircraft due to its safety, compactness, and low noise levels. To study the aerodynamic characteristics of DCP in hovering, a novel eVTOL was used, and a slip grid model was established to solve the three-dimensional unsteady N-S equation. The aerodynamic characteristics of DCP were compared to those of the free coaxial propeller (FCP) and ducted single propeller (DSP) to reveal the interaction mechanism of unsteady flow between the duct and propellers. The results indicate that the duct significantly mitigates th

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10

Zhang, Haoguang, Hao Wang, Qi Li, Fengyu Jing, and Wuli Chu. "Mechanism Underlying the Effect of Self-Circulating Casings with Different Circumferential Coverage Ratios on the Aerodynamic Performance of a Transonic Centrifugal Compressor." Aerospace 10, no. 3 (2023): 312. http://dx.doi.org/10.3390/aerospace10030312.

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The aim of this research was to explore the mechanisms underlying the effect of self-circulating casing treatment with different circumferential coverage ratios on the aerodynamic performance of a transonic centrifugal compressor. A three-dimensional unsteady numerical simulation was carried out on a Krain impeller. The circumferential coverage ratios of the self-circulating casings were set to 36%, 54%, 72% and 90%, respectively. The numerical results showed that the Stall Margin Improvement (SMI) increased with the increase in circumferential coverage ratios. The self-circulating casing with

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Dissertations / Theses on the topic "Tip Vortexes"

1

Affes, Habib. "Tip-vortex/airframe interactions /." The Ohio State University, 1992. http://rave.ohiolink.edu/etdc/view?acc_num=osu1487777170407828.

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2

Margaris, Panagiotis. "Wing tip vortex control by means of tip blowing." Thesis, University of Bath, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.436750.

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3

Dedekarginoglu, Riza Can. "A Parametric Investigation Of Tip Injection For Active Tip Vortex Control." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12612703/index.pdf.

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ABSTRACT A PARAMETRIC INVESTIGATION OF TIP INJECTION FOR ACTIVE TIP VORTEX CONTROL Dedekarginoglu, Riza Can M.Sc., Department of Aerospace Engineering Supervisor :Asst. Prof. Dr. Oguz Uzol December 2010, 79 pages Wing tip vortex is a challenging phenomenon that reduces the lift generation at the tip region of the wing. For aerial vehicles, several methodologies were presented for the sake of controlling vortices and alleviating effects of tip loss. In this study, the effect of wing tip injection on wing tip vortex structure was investigated computationally. A NACA0015 profile rectangular wing

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Pentelow, Steffen L. "Wing-tip Vortex Structure and Wandering." Thèse, Université d'Ottawa / University of Ottawa, 2014. http://hdl.handle.net/10393/31114.

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An isolated wing-tip vortex from a square-tipped NACA 0012 wing at an angle of attack of 5 degrees was studied in a water tunnel at a chord based Reynolds number of approximately 24000. Measurements were taken using stereo particle image velocimetry at three measurement planes downstream of the wing under each of three freestream turbulence conditions. The amplitude of wandering of the vortex axis increased with increasing distance downstream of the wing and with increasing freestream turbulence intensity. The magnitude of the peak azimuthal velocity decreased with increasing distance from

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Ghimire, Hari Charan. "WING-TIP VORTEX EVOLUTION IN TURBULENCE." UKnowledge, 2018. https://uknowledge.uky.edu/me_etds/110.

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Planar and stereo particle image velocimetry measurements were conducted of a wing-tip vortex decaying in free-stream turbulence in order to understand the evolution of a vortex and its decay mechanism. The vortex decayed faster in the presence of turbulence. The decay of the circulation was found to be almost entirely due to a decrease in circulation of the vortex core, caused by the relative decrease in peak tangential velocity without a corresponding increase in core radius. These events were found to be connected with the stripping of core fluid from the vortex core. The increased rate of

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6

Ostovan, Yashar. "Experimental Investigation Of Waveform Tip Injection Onthe Characteristics Of The Tip Vortex." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613780/index.pdf.

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This study investigates the effect of chordwisely modulated tip injection on the flow and turbulence characteristics of the tip vortex through experimental measurements downstream of a rectangular half-wing that has an aspect ratio of three. This injection technique involves spanwise jets at the tip that are issued from a series of holes along the chord line normal to the freestream flow direction. The injection mass flow rate from each hole is individually controlled using computer driven solenoid valves and therefore the flow injection geometrical pattern at the tip can be adjusted to any de

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Pereira, Jennifer Loren. "Experimental investigation of tip vortex control using a half delta shaped tip strake." Thesis, McGill University, 2012. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=107592.

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The effectiveness of using a half delta wing tip strake for static wing tip vortex control and performance enhancement was investigated. The flowfield over the wingtip and in the near-field was studied over a low aspect ratio NACA 0012 wing fitted with a half delta wing with a leading-edge sweep of 64º at a chord Reynolds number of 3 x 10⁵. The incidence of the strake relative to the main wing was movable allowing for strake settings from δ = -10º to +10º. Force balance data supplemented with flowfield measurements were used to investigate the performance improvements with the addition of the

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Duraisamy, Karthikeyan. "Studies in tip vortex formation, evolution and control." College Park, Md. : University of Maryland, 2005. http://hdl.handle.net/1903/2372.

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Thesis (Ph. D.) -- University of Maryland, College Park, 2005.<br>Thesis research directed by: Aerospace Engineering. Title from t.p. of PDF. Includes bibliographical references. Published by UMI Dissertation Services, Ann Arbor, Mich. Also available in paper.

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9

Zsoldos, Jeffrey S. "An experimental investigation of interacting wing-tip vortex pairs." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-11242009-020215/.

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Heckel, Scott P. "Reynolds stress measurements in a turbine tip leakage vortex." Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-10102009-020346/.

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Books on the topic "Tip Vortexes"

1

Sponagle, Neil Charles. Noise from tip vortex and bubble cavitation. Defence Research Establishment Atlantic, 1990.

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2

-J, Lin S., and Langley Research Center, eds. User's guide, tip vortex computer code, SRATIP. National Aeronautics and Space Administration, Langley Research Center, 1985.

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3

K, Uenishi, Gliebe P. R, and United States. National Aeronautics and Space Administration., eds. An investigation of counterrotating tip vortex interaction. National Aeronautics and Space Administration, 1989.

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4

1936-, Tung C., Heineck James T, and Ames Research Center, eds. Devices that alter the tip vortex of a rotor. National Aeronautics and Space Administration, Ames Research Center, 2001.

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5

W, McAlister Kenneth, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Preliminary study of a wing-tip vortex using laser velocimetry. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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6

United States. National Aeronautics and Space Administration., ed. Computation of the tip vortex flowfield for advanced aircraft propellers. National Aeronautics and Space Administration, 1990.

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7

Center, Ames Research, ed. Numerical study of the trailing vortex of a wing with wing-tip blowing. National Aeronautics and Space Administration, Ames Research Center, 1994.

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8

J, McCroskey W., Ames Research Center, and United States. Army Aviation Systems Command., eds. Tip vortices of wings in subsonic and transonic flow: A numerical simulation. National Aeronautics and Space Administration, Ames Research Center, 1987.

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9

Yamamoto, Atsumasa. Interaction mechanisms between tip leakage flow and the passage vortex in a linear turbine rotor cascade. National Aerospace Laboratory, 1988.

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10

S, Wittmer Kenneth, Wenger Christian W, and United States. National Aeronautics and Space Administration., eds. The spectral and statistical properties of turbulence generated by a vortex/blade-tip interaction: Final technical report ... Dept. of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, 1997.

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Book chapters on the topic "Tip Vortexes"

1

Tsujimoto, Yoshinobu. "Tip Leakage and Backflow Vortex Cavitation." In Fluid Dynamics of Cavitation and Cavitating Turbopumps. Springer Vienna, 2007. http://dx.doi.org/10.1007/978-3-211-76669-9_6.

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2

Decaix, Jean, Guillaume Balarac, and Cécile Münch. "Rans Computations of a Cavitating Tip Vortex." In Advances in Hydroinformatics. Springer Singapore, 2015. http://dx.doi.org/10.1007/978-981-287-615-7_35.

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3

Fruman, D. H., D. Bismuth, and S. Aflalo. "Effect of Polymer Solutions on Tip Vortex Cavitation." In The Influence of Polymer Additives on Velocity and Temperature Fields. Springer Berlin Heidelberg, 1985. http://dx.doi.org/10.1007/978-3-642-82632-0_31.

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4

Yang, Li. "Study Tip Leakage Vortex of CPU Fan with Skewed Rotors." In Lecture Notes in Electrical Engineering. Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-4981-2_86.

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5

Wang, Yufan, and Weihao Zhang. "Analysis of Vortex Evolution in Turbine Rotor Tip Region Based on Liutex Method." In Liutex and Third Generation of Vortex Definition and Identification. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-70217-5_26.

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6

Debernardis, Nicola, Clemens Schwarz, and Johannes N. Braukmann. "BOS-Based Three-Dimensional Reconstruction of Rotor Blade Tip Vortex Positions." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79561-0_30.

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Stepanov, Robert, and Alexander Kusyumov. "Experimental Study of Wing-Tip Vortex Core Circulation in Near-Field." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9632-9_21.

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8

Sanpei, Akio, Kiyokazu Ito, Yukihiro Soga, Jun Aoki, and Yasuhito Kiwamoto. "Formation of a symmetric vortex configuration in a pure electron plasma trapped with a penning trap." In TCP 2006. Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-73466-6_53.

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9

Russell, Justin W., Lakshmi N. Sankar, and Chee Tung. "Modifications of the Tip Vortex Structure from a Hovering Rotor Using Spoilers." In IUTAM Symposium on Dynamics of Slender Vortices. Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5042-2_37.

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Xue, Xianbo, Zejun Hua, Haijun Liu, et al. "Optimization of Structural Parameters of Vortex Type Coiled Tubing Drag Reduction Tool Based on Coanda Effect." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-97-7887-4_58.

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Abstract The vortex drag reduction tool based on wall attachment effect has a simple structure and high reliability, but lacks systematic research on tool structural parameters. In the application of coiled tubing drilling, there are problems such as poor parameter matching and weak power output. Therefore, based on the theory of wall attached jet, this article establishes a numerical model of vortex drag reduction tools, and investigates the effects of wedge distance, sidewall angle, wedge angle, and flow channel width on the oscillation performance of the tools. The research results indicate

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Conference papers on the topic "Tip Vortexes"

1

Wolf, C., Johannes Braukmann, Wolfgang Stauber, Till Schwermer, and Markus Raffel. "The Tip Vortex-System of a Four-Bladed Rotor in Dynamic Stall Conditions." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0074-2018-12691.

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The tip vortex-system downstream of a four-bladed instrumented rotor was investigated experimentally through the application of stereoscopic particle image velocimetry (PIV). A dynamic stall test case was facilitated by a high cyclic pitch setting of the swashplate, with additional attached-flow and constant-pitch test cases for comparison reasons. The phase-locked PIV system and a rotation of the swashplate assembly allowed for an acquisition of the tip vortex system over the entire dynamic stall cycle and vortex ages up to at least 235°. The vortex structure and its relation to the blade she

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2

Bhagwat, Mahendra, Manikandan Ramasamy, and Francis Caradonna. "Fundamental Characterization of Spanwise Loading and Trailed Wake Vortices." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10105.

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Rotorcraft flowfields are dominated by the vortices trailing from the blade tips. The formation, evolution and subsequent interaction of these vortices with the following blade(s) is a key to rotor airloads and performance. A fixed-wing wind tunnel test was designed to simulate the aerodynamic environment of a rotor blade tip in hover, using an upstream wing to generate an interacting vortex. Detailed surface pressure and flow field measurements were performed to better understand the relationship between the tip vortex characteristics, such the circulation distribution inside the vortex core,

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A., Abhishek, and Rahul R. "Investigation of Tip-Vortex Modifications on Rotor Loads and Performance." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10158.

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This paper studies the influence of tip vortex modification on the airloads and performance of the helicopter for high speed steady level flight and unsteady maneuver using a lifting-line based comprehensive analysis. The tip vortex modification is modeled inside the free wake model of the comprehensive analysis in three different ways: (1) the location of tip vortex release point is altered, keeping the strength constant, (2) strength of the tip vortex is diminished by certain factor while keeping the release location constant, and (3) both the release location and strength of the vortex are

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4

Mei, Lei, and Junwei Zhou. "Effects of Blade Tip Foil Thickening on Tip Vortexes in Ducted Propeller." In 3rd International Conference on Material, Mechanical and Manufacturing Engineering (IC3ME 2015). Atlantis Press, 2015. http://dx.doi.org/10.2991/ic3me-15.2015.323.

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Hernandez-Rivera, Ricardo, Abel Hernandez-Guerrero, Cuauhtemoc Rubio-Arana, and Raul Lesso-Arroyo. "Numerical Study in Wing Tip Vortex for a Modified Commercial Boeing Aircraft." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68149.

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Recent studies have shown that the use of winglets in aircrafts wing tips have been able to reduce fuel consumption by reducing the lift-induced drag caused by wing tip vortex. This paper presents a 3-D numerical study to analyze the drag and lift forces, and the behavior of the vortexes generated in the wing tips from a modified commercial Boeing aircraft 767-300/ER. This type of aircraft does not contain winglets to control the wing tip vortex, therefore, the aerodynamic effects were analyzed adding two models of winglets to the wing tip. The first one is the vortex diffuser winglet and the

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Bang, Minho, Seok Min Choi, Ho-Seong Sohn, Jun Su Park, and Hyung Hee Cho. "Effects of Unsteady Wakes on Heat Transfer of Blade Tip and Shroud." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64216.

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An experimental study has been conducted to investigate the heat-transfer characteristics of blade tips and shrouds with and without unsteady wakes. Depending on the presence of unsteady wakes, the local heat/mass-transfer coefficients of the tip and shroud were measured using the naphthalene sublimation method. Wakes from unsteady blades were modeled as wakes generated from moving cylindrical rod bundles. Test conditions were set to the Reynolds number of 100,000, based on an inlet velocity of 11.4 m/s and the axial chord length. The Strouhal number was varied from 0 to 0.22. For St = 0, high

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Zhang, Xinze, Zhenliang Liu, Zeyuan Yang, Yadong Wu, and Hua Ouyang. "Investigation on rotating instability in an axial compressor with different inlet reynolds numbers." In GPPS Chania24. GPPS, 2024. http://dx.doi.org/10.33737/gpps24-tc-042.

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In the near-stall condition, the axial flow compressor experiences an unstable flow phenomenon known as rotating instability (RI), which typically manifests as a broad bulge in the near-wall pressure spectrum, occurring at frequencies lower than blade passing frequency (BPF). It is considered the primary source of other instabilities such as non-synchronous vibration (NSV) and tip clearance noise (TCN), attracting considerable attention from researchers in recent years. This paper conducts a numerical simulation and experimental verification of a high-speed axial compressor to examine flow phe

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8

Liu, Yinhong, Ce Yang, Mingxu Qi, Hanzhi Zhang, and Ben Zhao. "Shock, Leakage Flow and Wake Interactions in a Radial Turbine With Variable Guide Vanes." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-25888.

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The clearances of the nozzle and volute have significant influences on the unsteady flow, blade load distribution and thermodynamic performance of downstream radial turbine. The unsteady flow and blade loads are intensified due to the interactions among shock, leakage flow and nozzle wake. Few studies have been conducted to date to investigate these effects in detail. This work focuses on the tip leakage flow effects on the nozzle wake and shock. Furthermore, the blade loads of the downstream rotor are considered by evaluating the effects of shock, leakage flow and nozzle wake, and the fluctua

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9

Wang, Xiangyu, Kun Xiao, and Zhenping Feng. "Study on Cooling Characteristics of an Internal Cooling Structure With a Sloping Sheet for Gas Turbine Blade." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76625.

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This study presents a cooling structure with a sloping sheet to improve the internal cooling of gas turbine blades, inspired by the concept of aircraft wing tip vortex. In this paper, the numerical simulation for the sloping sheet cooling structure has been carried out, which takes into account the heat conduction of the metallic material and the heat transfer of the external high temperature flow field. The results indicate that the structure utilizes the pressure difference between two sides of the sloping sheet to produce a strong vortex pair. The vortexes are led to the inner wall surface

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10

Jin, Yejia, Hongwei Ma, and Xinghang Yu. "Unsteady Analysis of Inlet Hot Streaks Clocking Effects in a 1-1/2 Turbine Stage." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14488.

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Abstract Migration of inlet hot streaks and the clocking effects are investigated by three-dimensional unsteady numerical simulations in a 1-1/2 turbine stage. Two hot streak circumferential positions with respect to first-stage stator, passage centered and vane centered, are simulated. Results indicate that hot streaks tend to accumulate on rotor blade pressure side and move towards shroud, causing hot spots on these parts. Separation of hot and cold fluid is observed in rotor, thus influence of hot streaks spreads to second-stage stator. Hot streaks are broken into fragments by rotor blade w

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Reports on the topic "Tip Vortexes"

1

Zsoldos, J. S., and W. J. Devenport. An Experimental Investigation of Interacting Wing-Tip Vortex Pairs. Defense Technical Information Center, 1992. http://dx.doi.org/10.21236/ada258471.

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2

Shen, Young T., and Murray Strasberg. The Effect of Scale on Propeller Tip-Vortex Cavitation Noise. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada420392.

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3

Telste, John G., Roderick M. Coleman, and Joseph J. Gorski. DTNS3D Computer Code Simulation of Tip-Vortex Formation: RANS Code Validation. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada343797.

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4

Zheng, Youxin, and B. R. Ramaprian. An Experimental Study of Wing Tip Vortex in the Near Wake of a Rectangular Wing. Defense Technical Information Center, 1993. http://dx.doi.org/10.21236/ada275389.

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