Relevant bibliographies by topics / Turning vanes

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Turning vanes'

Author: Grafiati
Published: 4 June 2021
Last updated: 21 June 2025

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Journal articles on the topic "Turning vanes"

1

Langwane, Kahuma, and N. Subaschandar. "Numerical Prediction and Reduction of Pressure Loss of Air Flow Inside a Sharp 90˚ Elbow Using Turning Vanes." WSEAS TRANSACTIONS ON FLUID MECHANICS 16 (July 27, 2021): 127–40. http://dx.doi.org/10.37394/232013.2021.16.13.

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The aim of this study is to calculate the pressure loss and the effect of turning vanes on the pressure loss incurred by the flow in a duct with a 90˚ sharp elbow using numerical fluid mechanics. The main focus this study was to calculate the effects of the number of turning vanes and the length of the turning vanes on the pressure loss. Computational Fluid Dynamics calculations have been carried out using ANSYS Workbench software. Two turbulence models have been used in these calculations. They are the standard k- and the k- turbulence models. The number and length of the vanes were changed in the study to calculate their effects on pressure loss. The length of the vanes was varied from 0mm to 400mm in steps of 100mm on both sides of the bend and the number of vanes was changed from 0 to 3. It was found that a single curved turning vane can reduce the pressure loss significantly. The pressure loss does not reduce further when the length of the vanes was extended. As the number of turning vanes increased beyond one, the predicted pressure loss starts increasing. The turning vanes in duct systems can be used in industries and factories to reduce the pressure loss.
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Johl, G., M. Passmore, and P. Render. "Design and performance of thin, circular arc, wind-tunnel turning vanes." Aeronautical Journal 111, no. 1116 (2007): 115–18. http://dx.doi.org/10.1017/s0001924000001810.

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Although test rig data exists for ¼ circle turning vanes, the actual performance of these vanes once installed in a wind tunnel, and the extent to which test rig results are replicated, is rarely known. This paper compares pressure loss coefficient and velocity profile data from a vane test module with measurements taken in the low speed wind tunnel described in Ref. 1.
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Williams, Hollis. "Comparison of forces for the Crookes and Hettner radiometers." Physics Education 57, no. 2 (2022): 025022. http://dx.doi.org/10.1088/1361-6552/ac420b.

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Abstract The Crookes radiometer (also known as a light mill) is a fascinating sunlight-powered device, in which a set of vanes is placed inside a glass bulb within which a partial vacuum has been pulled. The vanes then rotate when sunlight shines on the bulb. The reason for the turning of the vanes was subject to intense debate and many students still have an incorrect understanding of the device. We analyse the forces involved in a much less well-known radiometer (called the Hettner radiometer) and show that this can help us to understand the forces involved in the Crookes radiometer in a more unified way.
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Xu, Tao, Dongbo Shi, Di Zhang, and Yonghui Xie. "Flow and Heat Transfer Characteristics of the Turbine Blade Variable Cross-Section Internal Cooling Channel with Turning Vane." Applied Sciences 13, no. 3 (2023): 1446. http://dx.doi.org/10.3390/app13031446.

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The gas turbine blades are scoured by high temperature gas sustainedly and long-term in harsh environment. It is of great significance to explore effective cooling methods to lower the turbine blade temperature so as to ensure safe and stable operation of the gas turbine. However, there are few studies on the cooling channel considering the turning vane, variable cross-section characteristics, and rotation effect. In this paper, five kinds of serpentine cooling channel models with variable cross-section properties and different thickness guide vanes are constructed. The effects of different thickness guide vanes on the overall performance of the channel under stationary and rotating conditions are discussed and compared by numerical method. The result shows that when stationary (Re = 10,000-50,000), the turning vane with suitable thickness can increase the Nu/Nu0 by 56.5%. The f/f0 is decreased by 14.2%, and the comprehensive thermal performance is increased by 4.5%. When rotating (Re = 10,000, Ro = 0-0.5), the turning vane with suitable thickness can increase the Nuup/Nu0 and Nuall/Nu0 by 33.0% and 4.0%, respectively. The comprehensive performance of the variable cross-section serpentine channel can be greatly improved by arranging the turning vane structure with appropriate thickness.
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Eynon, P. A., and A. Whitfield. "The effect of low-solidity vaned diffusers on the performance of a turbocharger compressor." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 211, no. 5 (1997): 325–39. http://dx.doi.org/10.1243/0954406971522088.

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The design of low-solidity diffuser vanes and the effect on the performance of a turbo-charger compressor is discussed. The effect of vane number and turning angle was investigated while maintaining a basic design with a solidity of 0.69 and a leading edge angle of 75°. This large leading edge angle was specifically chosen so that the vane would be aligned with the low flowrates close to surge. Tests were initially conducted with six, eight and ten vanes and a turning angle of 10°. Based on these results the ten-vane design was selected for further investigation with 15 and 20° of vane turning; this led to vane exit angles of 60 and 55° respectively. All results are compared with those obtained with the standard vaneless diffuser configuration and it was shown that all designs increased and shifted the peak pressure ratio to reduced flowrates. The peak efficiency was reduced relative to that obtained with the vaneless diffuser. Despite the low-solidity configuration none of the vane designs provided a broad operating range without the use of a variable geometry configuration. This was attributed to the selection of a large leading edge vane angle.
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Waddington, D. C., and D. J. Oldham. "Noise Generation in Ventilation Systems by the Interaction of Airflow with Duct Discontinuities: Part 1 Bends." Building Acoustics 14, no. 3 (2007): 179–202. http://dx.doi.org/10.1260/135101007781998956.

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Discontinuities in air duct systems give rise to turbulence and some of this turbulence results in airflow generated noise. One potential source of flow generated noise in ducts is the presence of a bend. Various strategies are employed to reduce turbulence by smoothing the flow around a bend, such as the use of turning vanes, large radius of curvature and the associated use of splitters, and these will also affect the noise generated. Recent work on the prediction of airflow generated noise in ducts based upon pressure loss characteristics is applied to a range of bends including mitred bends, with and without turning vanes, and radiussed bends, with and without splitters. The effect of bends with different aspect ratios is also examined. An excellent collapse of measured data onto a single characteristic curve is reported for each configuration based upon standard values of pressure loss coefficients. It is suggested that these characteristic curves might form the basis for a practical prediction method.
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Bohacek, Jan, Miroslav Raudensky, and Petr Kotrbacek. "Remote Cooling of Rolls in Hot Rolling; Applicability to Other Processes." Metals 11, no. 7 (2021): 1061. http://dx.doi.org/10.3390/met11071061.

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A novel method of cooling rolls in hot rolling is proposed. This method uses a combination of solid jet nozzles and specially shaped deflecting vanes. The vanes transform the incoming cylindrical water jet into a flat fan. Thereby, the coolant can be directed into hardly accessible locations whilst maintaining the optimal angle of impingement. The vanes allow for effectively cooling the roll surface near the rolling gap, which is otherwise not possible with classical flat fan nozzles. The jet impact is tangential due to the limited room for nozzle mounts or a coolant supply. The developed method was laboratory tested. A similar cooling efficiency was found between the vane and the flat fan nozzle. The latter was however mounted in a position impossible in the plant. The potential of the proposed cooling is, therefore, eminent. Apart from hot rolling, it could be exploited in other technological processes such as high pressure die casting, machining, turning, hot stamping, etc.
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Bhasker, C. "Flow simulation in Electro-Static-Precipitator (ESP) ducts with turning vanes." Advances in Engineering Software 42, no. 7 (2011): 501–12. http://dx.doi.org/10.1016/j.advengsoft.2011.04.002.

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Williamson, R. G., S. H. Moustapha, and J. P. Huot. "The Effect of a Downstream Rotor on the Measured Performance of a Transonic Turbine Nozzle." Journal of Turbomachinery 108, no. 2 (1986): 269–74. http://dx.doi.org/10.1115/1.3262047.

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Two nozzle designs, involving the same low aspect ratio, high turning angle vanes, and differing in outer wall contour, were tested over a range of exit Mach numbers up to supersonic values. The experiments were conducted on a large-scale, full annular configuration with and without a representative rotor downstream. Nozzle performance was found to be significantly affected by rotor operation, the influence depending on the detailed characteristics of the nozzle flow field, as well as on the design and operation of the rotor itself. It is suggested that performance evaluation of low aspect ratio nozzles of high turning angle may require appropriate testing with a rotor.
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Ross, Richard. "Electro-impulse deicing of the NASA Lewis Altitude Wind Tunnel turning vanes." Journal of Aircraft 25, no. 6 (1988): 499–502. http://dx.doi.org/10.2514/3.45612.

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Dissertations / Theses on the topic "Turning vanes"

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Beale, Mark A. "Turning vanes in exhaust duct flow: study for energy efficiency, optimization and pressure drop mitigation." Thesis, Monterey, California: Naval Postgraduate School, 2014. http://hdl.handle.net/10945/43875.

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Approved for public release; distribution is unlimited<br>This thesis presents a computational fluid dynamics (CFD) study on the effects of turning vanes and their placement in an exhaust duct with a sharp bend of ninety degrees and the application toward waste heat recovery devices. CFD models were implemented in ANSYS/CFX to handle flow in both laminar and turbulent regimes. Applying the principles from the Reynolds-averaging Navier-Stokes governing equations as well as the k-ε turbulent model, accurate simulations were performed to explore the behavior of exhaust gas flow field, pressure drops and recirculation zone sizes for various flow Reynolds (Re) numbers. The effects of turning vane location, vane setting angle, and number of vanes were evaluated. Flow visualization was used as a means of determining ideal locations for future installation of WHR devices. Results for 5000<Re<2x105 showed significant improvement in pressure drop across the 90-degree duct with a single turning vane, showing ranges of 50–70% reduction in overall pressure drop across the duct. This pressure reduction could yield significant fuel savings compared to an engine or generator without a turning vane. Increasing the number of vanes neither reduced the pressure drop further, nor did it reduce the size of the primary recirculation zone.
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Lin, Yi-Tung, and 林奕同. "Improvement of 45-Degree Duct Elbows using Various Turning Vanes." Thesis, 2016. http://ndltd.ncl.edu.tw/handle/rr436e.

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碩士<br>國立臺灣海洋大學<br>機械與機電工程學系<br>104<br>This study simulated the physical mechanism of a flow field influenced by pipe elbows. Circled and squared pipe elbows with 45° orientations along with various types of turning vanes were used in the experiment. Pressure drops near pipe elbows caused flow separation near the outer walls of entrances and the inner walls of exits. Bubbles recirculated both inside and outside of pipe elbows because the insufficient kinetic energy of the flow field could not overcome the effect of the pressure drop. The flow separation possesses substantial influence on pipe elbows because of the loss of energy. The drop between the internal and external pressures caused secondary separated flow. Therefore, the downstream velocity and pressure decreased uniformly. This study used two types of turning vanes, thin plate and pigeon airfoil, to improve the flow field near the pipe elbows and to minimize the distance required for flow field stabilization. The thin-plate and pigeon-airfoil turning vanes comprised single-, dual-, and triple-blade configurations and were tested against 45° circled and squared pipe elbows without turning vanes. The study results are as follows: (a) the flow visualization experiment indicated that bubbles diminished as the numbers of thin-plate turning vanes increased. (b) The maximum pressure coefficient as measured by a pressure scanning device occurred at the range of x/d = 0.5 and x/d = 1 in the downstream area. Furthermore, the pressure coefficient profile in the downstream (i.e., at x/d = 8) started approaching that in the upstream after exiting the pipe elbows.
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Wang, Syuan-Bo, and 王炫博. "Thin-Curved Plate Turning Vanes on Improvement of 45-Degree Duct Elbow Flow." Thesis, 2015. http://ndltd.ncl.edu.tw/handle/4e7h6j.

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碩士<br>國立臺灣海洋大學<br>機械與機電工程學系<br>103<br>Pressure drops near pipe elbows causes the flow separation around the extrados at the pipe entrance and around intrados at the pipe exit. This phenomenon occurs because the kinetic energy of the flow field is insufficient to overcome the effect of pressure drop generated at the pipe elbow, which commonly manifests as recirculation bubbles at the extrados. In addition, this phenomenon typically leads to energy loss. In this study, an experiment on the flow field influenced by pipe elbows was performed in an open-loop wind tunnel with a 45° orientation in the test section. The pressure drop between the intrados and extrados caused the secondary separation; and therefore, the downstream velocity and pressure lost uniformity as the flow passed the elbow. The thin-curved plates were adopted to improve the flow field near the pipe elbows and to minimize the distance required for stabilizing the flow field. The thin-curved plate comprised single-, dual-, triple-, and 5-blade configurations and were tested against a 45° hollow pipe elbow without thin-plate guide vanes. The experimental results were summarized as: (a) the flow visualization experiment showed that bubbles diminished as the number of blades on the thin plate or wind speeds increased; (b) hot-wire detections revealed that the turbulence intensity increased as the number of blades on the thin plates and or wind speeds increased; and (c) the maximum pressure coefficient and velocity fluctuations occurred at approximately x/d = 0.33 and 0.66 in the downstream area. In a dual-blade thin plate configuration, the pressure coefficient and velocity in the downstream (i.e., at x/d = 1.00) were close to those in the upstream. Keywords: pipe elbow, thin-curved guide vane, secondary separation
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Lei, Jiang 1980. "Heat Transfer in Rectangular Channels (AR=2:1) of the Gas Turbine Blade at High Rotation Numbers." Thesis, 2011. http://hdl.handle.net/1969.1/150950.

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Gas turbine blade/vane cooling is obtained by circulating the high pressure air from compressor to the internal cooling passage of the blade/vane. Heat transfer and cooling effect in the rotating blade is highly affected by rotation. The typical rotation number for the aircraft engine is in the range of 0~0.25 and for the land based power generation turbine in the range of 0~05. Currently, the heat transfer data at high rotation numbers are limited. Besides, the investigation of heat transfer phenomena in the turn region, especially near hub portion is rare. This dissertation is to study the heat transfer in rectangular channels with turns in the tip or the hub portion respectively at high rotation numbers close to the engine condition. The dissertation experimentally investigates the heat transfer phenomena in a two-pass rectangular channel (AR=W/H=2:1) with a 180 degree sharp turn in the tip portion. The flow in the first passage is radial outward and after the turn in the second passage, the flow direction is radial inward. The hydraulic diameter (Dh) of the channel is 16.9 mm. Parallel square ribs with an attack angle (alpha) of 45 degrees are used on leading and trailing surfaces to enhance the heat transfer. The rib height-to-hydraulic diameter ratio (e/Dh) is 0.094. For the baseline smooth case and the case with rib pitch-to-height ratio (P/e) 10, channel orientation angles (beta) of 90 degrees and 135 degrees were tried to model the cooling passage in the mid and rear portion of the blade respectively. Two other P/e ratios of 5 and 7.5 were studied at beta=135 degrees to investigate their effect on heat transfer. The data are presented under high rotation numbers and buoyancy parameters by varying the Reynolds number (Re=10,000~40,000) and rotation speed (rpm=0~400). Corresponding rotation number and buoyancy parameter are ranged as 0~0.45 and 0~0.8 respectively. The dissertation also studies the heat transfer in a two-pass channel (AR=2:1) connected by a 180 degree U bend in the hub portion. The flow in the first passage is radial inward and after the U bend, the flow in the second passage is radial outward. The cross-section dimension of this channel is the same as the previous one. To increase heat transfer, staggered square ribs (e/Dh=0.094) are pasted on leading and trailing walls with an attack angle (alpha) of 45 degrees and pitch-to-height ratio (P/e) of 8. A turning vane in the shape of half circle (R=18.5 mm, t=1.6 mm) is used in the turn region to guide the flow for both smooth and ribbed cases. Channel orientation angles (beta) of 90 degrees and 135 degrees were taken for both smooth and ribbed cases. The heat transfer data were taken at high rotation numbers close to previous test section.
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Books on the topic "Turning vanes"

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Gelder, Thomas F. Experimental evaluation of turning vane designs for high-speed and coupled fan-drive corners of 0.1-scale model of NASA Lewis Research Center's proposed Altitude Wind Tunnel. Lewis Research Center, 1987.

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Ross, James C. Prediction of vortex-induced loads on wind tunnel turning vanes. National Aeronautics and Space Administration, Ames Research Center, 1985.

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Center, Ames Research, ed. Prediction of vortex-induced loads on wind tunnel turning vanes. National Aeronautics and Space Administration, Ames Research Center, 1985.

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Ross, James C. Prediction of vortex-induced loads on wind tunnel turning vanes. National Aeronautics and Space Administration, Ames Research Center, 1985.

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Moore, Royce D. Detailed flow surveys of turning vanes designed for a 0.1-scale model of NASA Lewis Research Center's proposed altitude wind tunnel. Lewis Research Center, 1987.

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G, Seasholtz Richard, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Laser anemometer measurements and computations in an annular cascade of high turning core turbine vanes. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Johnson, Steven A. Aircraft ground test and subscale model results of axial thrust loss caused by thrust vectoring using turning vanes. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Laser anemometer measurements and computations for transonic flow conditions in an annular cascade of high turning core turbine vanes. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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D, Moore Royce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Detailed flow surveys of turning vanes designed for a 0.1-scale model of NASA Lewis Researach Center's proposed altitude wind tunnel. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Boldman, Donald R. Experimental evaluation of two turning vane designs for fan drive corner of 0.1-scale model of NASA Lewis Research Center's proposed altitude wind tunnel. Lewis Research Center, 1987.

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Book chapters on the topic "Turning vanes"

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Nguyen, Tien-Dung, Hai-Quang Do, Cong-Hung Hoang, et al. "Effect of Turning Vanes on Heat Exchange Characteristics of Cooling Channel in Turbine Blade." In The AUN/SEED-Net Joint Regional Conference in Transportation, Energy, and Mechanical Manufacturing Engineering. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1968-8_100.

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Gao, Jie, Qun Zheng, Feng Lin, Chen Liang, and Yu Liu. "Variable Vane Turning Design Method for a Variable Geometry Turbine." In Variable Geometry Turbine Technology for Marine Gas Turbines. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-6952-2_4.

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"Silencer with Rectangular Turning-Vane Splitters silencer with rectangular turning-vane splitters." In Formulas of Acoustics. Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-76833-3_223.

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d’Agostino, Bruno, Maria Grazia Palmieri, and A. C. Cassio. "Potters, Hippeis and Gods at Penteskouphia (Corinth), Seventh to Sixth Centuries BC." In The Archaeology of Greece and Rome, translated by Federico Poole. Edinburgh University Press, 2016. http://dx.doi.org/10.3366/edinburgh/9781474417099.003.0007.

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The archaeological context of the fictile tablets found at the archaeological site of Penteskouphia, along the Phliasian road at the rear of Acrocorinth, still resists attempts at interpretation. The special interest of this context lies in the fact that it provides lavish evidence for the work of potters. All stages of the work cycle are documented: the extraction of clay from the quarry, the shaping of the vase on the turning wheel, the work at the kiln, from fuelling to watching over the vases in the crucial stages of firing, the finishing and decoration of the vases in the workshop, the loading of the vases onto ships and their transportation by sea.1
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"Zero-Order and First-Order Transmission Loss of Turning-Vane Splitter Silencers transmission loss turning-vane splitter silencer transmission loss." In Formulas of Acoustics. Springer Berlin Heidelberg, 2008. http://dx.doi.org/10.1007/978-3-540-76833-3_221.

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Cottom, Daniel. "On the Dignity of Tables." In Abyss of Reason. Oxford University PressNew York, NY, 1991. http://dx.doi.org/10.1093/oso/9780195068573.003.0002.

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Abstract Soon after modern spiritualism announced itself with the “Rochester knockings” of 1848, tables took on a new and controversial life. No longer were they content to live out their days impassively upholding dishes and glasses and silverware, vases, papers and novels, bibelots, elbows, or weary heads. They were changed: they began to move. Tables all over the United States and then in England, France, and other countries commenced rapping, knocking, tilting, turning, tipping, dancing, levitating, and even “thrilling” - though this last was uncommon.
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Meyer, Caspar. "Why Drawing Still Matters." In Drawing the Greek Vase. Oxford University PressOxford, 2023. http://dx.doi.org/10.1093/oso/9780192856128.003.0002.

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Abstract This chapter explores drawings of Greek vases from three turning points in the history of ceramic studies and in archaeological thinking more broadly: they reveal how these objects were made sense of through the emergent taxonomies of early modern antiquarianism, how Neoclassical critics reinterpreted the materiality of the painted decoration as form and reconceptualized the act of drawing itself, and finally how drawing allowed painted pottery to be accommodated in the all-embracing classifications of scientific archaeology that crystalized in the twentieth century. The final section considers how drawing aided the formation of processes of knowing, inviting the consideration of touch, embodied viewing, and craft in general into object-based research. Throughout, the aim is to shift the conversation from evaluating drawings of vases as more or less accurate visual records to the transformations which the practice of visualization itself accomplishes—how it shapes the viewer’s perceptions and has given rise to new frameworks of interpretation.
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Slaney, Helen. "Eighteenth-Century Antiquity: Extended, Embodied, Enacted." In Distributed Cognition in Enlightenment and Romantic Culture. Edinburgh University Press, 2019. http://dx.doi.org/10.3366/edinburgh/9781474442282.003.0013.

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Sir William Hamilton’s Greek vase collection, assembled at Naples between the 1760s and 1790s, became a turning point in the reception of ancient material culture and hence in perceptions of classical antiquity. This chapter compares three angles of approach to the collection, each corresponding to a strand of distributed cognition. Extended cognition is represented by the catalogue which made the collection available to the reading public; embodied cognition is represented by the dance performances of Emma Hamilton, Sir William’s wife, who based her tableaux vivants of ancient life around the images represented on the vases; and enactive cognition by the aesthetic theory of the ‘feeling imagination’ developed by philosopher Johann Gottfried Herder, who visited the Hamiltons at Naples and commented unfavourably on Emma’s performances. I argue that Herder’s rejection of Emma’s kinetic reception of ancient artwork was predicated in part on his reluctance to place physical limitations on simulated movement.
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Woolrych, Austin. "The First Phase of Cromwellian Rule." In Britain in Revolution 1625–1660. Oxford University PressOxford, 2002. http://dx.doi.org/10.1093/oso/9780198200819.003.0020.

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Abstract In England, during the dozen years prior to the Protectorate, each major political turning-point had alienated a significant section of the Long Parliament’s original adherents, and so had narrowed the basis of support for the government of the day. When Civil War loomed, the constitutional royalists who had helped to pass the reforms of 1641 broke with Pym and his party and rallied to the king. In the crisis of 1648–9, most of the political presbyterians were driven into the wilderness by Pride’s Purge and the regicide, and some of them became royalists. In 1653, Cromwell’s expulsion of the Rump made enemies for life of such parliamentary republicans as Haselrig, Vane, Bradshaw, and Marten, while the Fifth Monarchists among others were never to forgive his elevation to the Protectorship at the end of the year.
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"Chapter Two. Turning Into A Satyr: Small Vases From The First Half Of The 6th Century BCE." In Dionysos in Archaic Greece. BRILL, 2006. http://dx.doi.org/10.1163/ej.9789004144453.i-363.13.

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Conference papers on the topic "Turning vanes"

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Hayden, Andrew P., John Gillespie, Cole Hefner, Todd Lowe, and Alexandrina Untaroiu. "Wake Dynamics of Complex Turning Vanes Using Time-Resolved Particle Image Velocimetry Measurements." In ASME 2023 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/imece2023-113379.

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Abstract The use of turning vanes spans multiple engineering disciplines such as aerospace, ocean, and biomedical to effectively turn an otherwise uniform flowfield and achieve desired downstream flow angles. The presented work investigates the wake dynamics generated by sets of complex turning vanes which contained nonaxisymmetric geometries, spanwise variations in turning angle, and multiple vane junctions. Time-resolved particle image velocimetry (TR-PIV) measurements were performed to collect three-component velocity data downstream of the vane pack geometries. As the vanes contained blunt trailing edges, large-scale periodic structures (von Kármán vortices) dominated the unsteady wakes. Two post-processing methods, Proper Orthogonal Decomposition (POD) and Dynamic Mode Decomposition (DMD), were employed to extract the wake energy or enstrophy content, corresponding spatial modes, and associated frequencies. This was completed for various parameters such as Reynolds number, vane turning angle, and vane trailing edge thickness. Spatial POD analyses showed that zero-turning vanes contained similar dynamics to that of a circular cylinder, and the total wake energy distributions were affected by freestream velocity. A spectral POD analysis in the wake of vane junctions found that the junction flow contained significant coherent content, and gave some insight into the mean flow. Lastly, vane parameters such as turning angle and TE thickness were found to play a large role in modifying the enstrophy content of the large-scale shedding modes.
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GELDER, T., R. MOORE, J. SANZ, and E. MCFARLAND. "Wind tunnel turning vanes of modern design." In 24th Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-44.

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Balligand, Hélène, Xiubao Huang, and Joost J. Brasz. "The Effect of Impeller Inlet Annular Turning Vanes on Multistage Centrifugal Compressor Performance." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-257.

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The flow path of multistage centrifugal compressors is characterized by two 180-degree turns per stage: the inlet turning bend connecting the radial inflow return channel with the radial outflow impeller and the cross-over bend connecting the radial outflow diffuser with the return channel. Due to higher flow velocity and larger width to turning radius ratio, the turning losses are substantially higher in the inlet bend than in the return channel bend. Performance measurements were taken using different annular through-flow turning vane arrangements designed to reduce the inlet turning losses and increase the overall efficiency of the multistage centrifugal compressor. The experiments have shown consistent efficiency gains with corresponding capacity increases by adding multiple annular turning vanes in the inlet bend. The performance improvement potential of the vanes depends strongly on the positioning of these vanes in the flow passage. Based on these results, an empirical turning loss model was developed with the capability to predict the performance improvement achievable with correctly positioned single or multiple turning vanes in the impeller inlet bend area.
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4

Lee, Dong Myeong, Jun Su Park, Dong Hyun Lee, Beom Soo Kim, and Hyung Hee Cho. "Heat Transfer Characteristics of a Non-Rotating Two-Pass Rectangular Duct With Various Guide Vanes in the Tip Turn Region." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-45962.

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The present study investigated convective heat transfer inside a two-pass rectangular duct with guide vanes in the turning region. The objective was to determine the effect of the guide vanes on blade tip cooling. The duct had a hydraulic diameter (Dh) of 26.67 mm and an aspect ratio (AR) of 5. The duct inlet width was 80 mm, and the distance between the tip of the divider and the tip wall of the duct was also 80 mm. Various guide vane configurations were used in the turning region. The Reynolds number (Re), based on the hydraulic diameter, was held constant at 10,000. The naphthalene sublimation technique was used to determine the detailed local heat transfer coefficients, using the heat and mass transfer analogy. The results indicated that guide vanes in the turning region enhanced heat transfer in the blade tip region. The guide vane on the second-pass side of the turning region had higher heat transfer than the guide vane on the first-pass side. Strong secondary flow enhanced heat transfer in the blade tip region. Dean vortices induced by the guide vanes pushed the high-momentum core flow towards the tip wall, and heat transfer was increased in the turning region, but decreased in the second passage. Consequently, a guide vane on the second-pass side of the turning region generates high heat transfer rates on the tip surface, and can also increase the thermal performance factor in a two-pass duct.
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Huang, Szu-Chi, Kai-Chieh Chia, Je-Wei Yeh, and Yao-Hsien Liu. "Effect of Turning Vane on Tip Wall Heat Transfer in a Rotating Two-Pass Rectangular Channel." In ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/gt2024-126984.

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Abstract During gas turbine operation, the blade tip region experiences high thermal load. Adequate cooling near the tip is necessary to reduce thermal stresses and extend blade lifespan. This study examined heat transfer distribution on the tip wall of internal cooling channels through experimental measurement and numerical simulation. A two-pass rectangular channel with an aspect ratio (AR) of 1:4 and a hydraulic diameter of 25.6 mm was used. In the 180° turn region, both full turning vanes and slotted turning vanes were installed to minimize pressure loss while maintaining favorable heat transfer distribution. Thermochromic liquid crystals thermography and stroboscopic photography were employed in the experiment to obtain heat transfer distribution on the tip wall. The Reynolds number ranged from 10,000 to 30,000, while the rotation number ranged from 0 to 0.53. To increase rotation number, internal channel pressure was increased while keeping Reynolds number constant in order to decrease flow velocity. In the numerical study, ANSYS-Fluent R19.2 software was used for predicting flow field using a transition SST turbulence model with air as working fluid. The slotted turning vanes allowed flow impingement on the tip wall resulting in a higher heat transfer rate compared to cases with full turning vanes (10% higher). Both cases with turning vanes showed lower pressure drop and reduced heat transfer magnitude compared to smooth cases without turning vanes. Generally, rotation had less effect on tip wall heat transfer for cases with turning vanes due to reduction of rotation-induced secondary flow by these vane structures. The effect of channel orientation was less significant for cases with turning vanes compared to those without them.
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6

Im, Kangsoo, and Jongsik Jeong. "Performance Characteristics of a Centrifugal Compressor With Capacity Control by Variable Diffuser Vanes." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-16255.

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Abstract A study of a variable diffuser vane capacity control method was done for the delivery of air into degasser of a SRU (Sulfur Recovery Unit) in a refinery process which requires a wide operating range and high head rise. Rig tests were made with diffuser vanes with various diffuser turning angles to evaluate performance of the compressor with variable diffuser vane. The compressor running on the test rig consisted of inlet bell mouth venturi, unshrouded impeller and vaned diffuser with tip clearance and scroll. To evaluate performance of the impeller and diffuser, static pressure was measured on the shroud side through 30 pressure tabs. The performance characteristics of the compressor stage, such as head coefficient, work coefficient, impeller exit flow condition and diffuser pressure recovery, are evaluated for 3 diffuser vanes and speeds. All performance characteristics are expressed as dimensionless form for each diffuser turning angle and speed. For the stage performance, compressor capacity is reduced as diffuser turning angle increase. For the impeller and diffuser performance, impeller exit flow coefficient is used for impeller exit flow condition and its performance. Based on the rig test, 6 customized single stage compressors with the variable diffuser vane capacity control system for the degasser of SRU were made and shop test were performed on each compressor. It was found that surge of the compressors can be controlled by variable diffuser vane and largely depends on the diffuser geometry.
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7

Micklow, Gerald J., and Michael Benjamin. "Three Dimensional Analysis of Advanced Swirl Vane/Nozzle Assemblies." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-226.

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The performance of high shear axial inflow/radial outflow airblast fuel injectors for advanced gas turbine combustors is highly dependent on the design of the swirl vanes. Curved vanes usually exhibit lower losses but straight vanes are also used due to lower cost and ease of manufacture. These type of vanes often operate under highly stalled conditions with high total pressure loss and a highly non-uniform exit velocity profile. This may produce poor fuel atomization with a non-uniform combustor fuel distribution resulting in lowered combustor efficiency and increased pollutant emissions. Properly designed vanes result in a greatly reduced total pressure loss. The exit velocity distribution is more uniform and higher in magnitude which can result in improved fuel atomization and distribution in the combustor. The present study investigates two curved swirler/nozzle shroud configurations operating at 1 and 10 atmospheres pressure for the same inlet temperature of 293°K. The first configuration was a twisted curved vane with thickness where the turning angle varied non-linearly from hub to tip with a maximum turning at the tip of 70 degrees. The second configuration was a curved vane with a linear variation of turning with 70 degrees turning at the tip. The results from a three dimensional viscous numerical flow simulation of these configurations shows similar performance for all cases investigated. The non-linear twisted vane however, had an approximately 3% higher mass flow rate than the vane with the linear variation in turning for the same exit static pressure at the hub. One problem which existed for all the conditions analyzed was a high loss region near the vane tip. This was due to the interaction with the shroud. As the flow exits the vane row and progresses along the nozzle outer lip, the flow area increases. This condition along with the streamline curvature effect of the outer nozzle lip causes an adverse pressure gradient to be formed in this region. This adverse pressure gradient causes the flow to separate from the vane suction surface. The problem initiated in the region of 70% span and increased in magnitude to the vane tip.
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Diwakar, Philip, Ajay Prakash, and Cyrus Thomas. "Flow Induced Vibration of Equipment Internals in a Two-Phase Gas/Liquid Flow." In ASME 2017 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/pvp2017-65812.

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The paper describes the use of Fluid-Structure-Interaction (FSI) to evaluate turning vane blades in an inlet distributor with two-phase gas/liquid flow. A fatigue failure mechanism attributed to flow induced vibration (FIV) resulting from vortex shedding and un-steadiness in the flow field is evaluated. This failure mechanism can be missed in a complex flow field that is assumed to be steady. Natural frequency of the turning vanes was found to be well within the flow induced forcing frequency range, which led to structural failure of the vanes.
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9

Alsaleem, Sulaiman M., Lesley M. Wright, and Je-Chin Han. "Heat Transfer and Pressure Loss in a Two-Pass, Rectangular Channel Featuring a Reduced Cross-Sectional Area After the 180-Degree Tip Turn With Different Turning Vane Configurations." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14510.

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Abstract Serpentine, varying aspect ratio cooling passages, are typically used in cooling advanced gas turbine blades. These passages are usually connected by sharp, 180-deg bends. In the open literature, most of the internal cooling studies use a fixed cross-sectional area for multi-pass channels. Studies that use varying aspect ratio channels, along with a guide (turn) vane to direct the flow with turning, are scarce. In general, studies show that the incorporation of turning vanes in the bend region of a multi-pass channel keeps the heat transfer rate high while reducing pressure loss. Therefore, the current study investigates the effect of using different guide (turn) vane designs on both the detailed heat transfer distribution and pressure loss in a multi-pass channel with an aspect ratio of (4:1) in the entry passage and (2:1) in the second passage downstream of the vane (s). The first vane configuration is one solid-vane with a semi-circular cross-section connecting the two flow passages. The second configuration has three broken-vanes with a quarter-circular cross-section; two broken vanes are located downstream in the first passage (entering the turn), and one broken vane is upstream in the second passage (exiting the turn). For a Reynolds number range 15,000 to 45,000, detailed heat transfer distributions were obtained on all surfaces within the flow passages by using a transient liquid crystal method. The results show that the turning vane configurations have large effects on the heat transfer, in the turning bend and second passage, and the overall pressure drop. Results show that including the semi-circular vane in the turning region of a multi-pass channel enhanced the overall heat transfer by around 29% with a reduction in pressure loss by around 20%. Moreover, results show that the quarter-circular vane design provides higher overall averaged heat transfer enhancement than the semi-circular vane design by around 9% with penalty of higher pressure drop by 6%, which yields higher thermal performance by 7%, over the Reynolds number range.
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Luo, Jiang, and Eli H. Razinsky. "Analysis of Turbulent Flow in 180° Turning Ducts With and Without Guide Vanes." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-28173.

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This paper presents a numerical study of the turbulent flows through a number of 2-D and 3-D 180° U-ducts, with and without guide vanes, using the Reynolds-averaged Navier-Stokes method. Computations have been first carried out for a 2-D U-duct flow (W/H = 1.0) with four turbulence models (V2F, k-ε, SST and Reynolds stress). The models’ capability for streamline curvature effects on turbulence and separation has been assessed, using flow and turbulence data. The effects of adding a guide vane inside the bend have been analyzed, to reduce/avoid flow separation. Three vanes with different radial locations have been studied, and the mechanism for pressure loss reduction has been examined. Analyses have been performed for turbulent flows in 3-D U-ducts with square cross-section and sharp 180° turning (W/D = 0.2), similar to the U-bends in typical turbine blade cooling passages. The predictions are compared with the data of outer wall pressure. The effects of the guide vane and outer-wall shape on the flow separation, secondary-flow vortices and pressure loss have been evaluated. The combined vane and uniform cross-section area provide a large benefit for the flow distribution and pressure loss reduction.
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