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Journal articles on the topic 'Wakes (Aerodynamics) Turbulence. Turbomachines'

Author: Grafiati

Published: 4 June 2021

Last updated: 6 February 2022

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1

Abhari, R. S., and M. Giles. "A Navier–Stokes Analysis of Airfoils in Oscillating Transonic Cascades for the Prediction of Aerodynamic Damping." Journal of Turbomachinery 119, no. 1 (1997): 77–84. http://dx.doi.org/10.1115/1.2841013.

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An unsteady, compressible, two-dimensional, thin shear layer Navier–Stokes solver is modified to predict the motion-dependent unsteady flow around oscillating airfoils in a cascade. A quasi-three-dimensional formulations is used to account for the stream-wise variation of streamtube height. The code uses Ni’s Lax–Wendroff algorithm in the outer region, an implicit ADI method in the inner region, conservative coupling at the interface, and the Baldwin–Lomax turbulence model. The computational mesh consists of an O-grid around each blade plus an unstructured outer grid of quadrilateral or triang

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2

Gundy-Burlet, K. L., M. M. Rai, R. C. Stauter, and R. P. Dring. "Temporally and Spatially Resolved Flow in a Two-Stage Axial Compressor: Part 2—Computational Assessment." Journal of Turbomachinery 113, no. 2 (1991): 227–32. http://dx.doi.org/10.1115/1.2929090.

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Fluid dynamics of turbomachines are complicated because of aerodynamic interactions between rotors and stators. It is necessary to understand the aerodynamics associated with these interactions in order to design turbomachines that are both light and compact as well as reliable and efficient. The current study uses an unsteady, thin-layer Navier–Stokes zonal approach to investigate the unsteady aerodynamics of a multistage compressor. Relative motion between rotors and stators is made possible by the use of systems of patched and overlaid grids. Results have been computed for a 2 1/2-stage com

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3

Zhang, Di, Ma Jiao-Bin, and Qi Jing. "Numerical study of unsteady flow and exciting force for swept turbomachinery blades." Thermal Science 20, suppl. 3 (2016): 669–76. http://dx.doi.org/10.2298/tsci160205199z.

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The aerodynamic performance of blade affects the vibration characteristics and stable operation of turbomachinery closely. The aerodynamic performance of turbine stage can be improved by using swept blade. In this paper, the RANS method and the RNG k-? turbulence mode were adopted to investigate the unsteady flow characteristics and excitation force of swept blade stage. According to the results, for the swept blade, the fluid of boundary layer shifts in radial direction due to the influence of geometric construction. It is observed that there is similar wake development for several kinds of s

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4

Yang, Xiaolei, Daniel Foti, Christopher Kelley, David Maniaci, and Fotis Sotiropoulos. "Wake Statistics of Different-Scale Wind Turbines under Turbulent Boundary Layer Inflow." Energies 13, no. 11 (2020): 3004. http://dx.doi.org/10.3390/en13113004.

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Subscale wind turbines can be installed in the field for the development of wind technologies, for which the blade aerodynamics can be designed in a way similar to that of a full-scale wind turbine. However, it is not clear whether the wake of a subscale turbine, which is located closer to the ground and faces different incoming turbulence, is also similar to that of a full-scale wind turbine. In this work we investigate the wakes from a full-scale wind turbine of rotor diameter 80 m and a subscale wind turbine of rotor diameter of 27 m using large-eddy simulation with the turbine blades and n

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5

Ames, F. E., and M. W. Plesniak. "The Influence of Large-Scale, High-Intensity Turbulence on Vane Aerodynamic Losses, Wake Growth, and the Exit Turbulence Parameters." Journal of Turbomachinery 119, no. 2 (1997): 182–92. http://dx.doi.org/10.1115/1.2841100.

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An experimental research program was undertaken to examine the influence of large-scale high-intensity turbulence on vane exit losses, wake growth, and exit turbulence characteristics. The experiment was conducted in a four-vane linear cascade at an exit Reynolds number of 800,000 based on chord length and an exit Mach number of 0.27. Exit measurements were made for four inlet turbulence conditions including a low-turbulence case (Tu ≈ 1 percent), a grid-generated turbulence case (Tu ≈ 7.5. percent) and two levels of large-scale turbulence generated with a mock combustor (Tu ≈ 12 and 8 percent

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6

O’Brien, J. E., and S. P. Capp. "Two-Component Phase-Averaged Turbulence Statistics Downstream of a Rotating Spoked-Wheel Wake Generator." Journal of Turbomachinery 111, no. 4 (1989): 475–82. http://dx.doi.org/10.1115/1.3262296.

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Measurements of the axial and tangential components of the unsteady turbulent flow downstream of a rotating spoked-wheel wake generator have been obtained. The results of this study have implications for the use of this type of wake generator to produce simulated turbine guide vane wakes. Instantaneous velocity information was phase averaged based on a signal synchronized with the bar-passing frequency. Mean velocity profiles and phase-averaged Reynolds stress results were found to be consistent with measurements obtained behind a stationary cylinder. Reynolds stresses were significantly highe

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7

Chow, Yi-Chih, Oguz Uzol, and Joseph Katz. "Flow Nonuniformities and Turbulent “Hot Spots” Due to Wake-Blade and Wake-Wake Interactions in a Multi-Stage Turbomachine." Journal of Turbomachinery 124, no. 4 (2002): 553–63. http://dx.doi.org/10.1115/1.1509078.

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This experimental study provides striking examples of the complex flow and turbulence structure resulting from blade-wake and wake-wake interactions in a multi-stage turbomachine. Particle image velocimetry (PIV) measurements are performed within the entire 2nd stage of a two-stage turbomachine. The experiments are performed in a facility that allows unobstructed view of the entire flow field, facilitated using transparent rotor and stator and a fluid that has the same optical index of refraction as the blades. This paper contains data on the phase-averaged flow structure including velocity, v

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8

Abramian, M., and J. H. G. Howard. "A Rotating Laser-Doppler Anemometry System for Unsteady Relative Flow Measurements in Model Centrifugal Impellers." Journal of Turbomachinery 116, no. 2 (1994): 260–68. http://dx.doi.org/10.1115/1.2928360.

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The behavior of the relative flow in centrifugal turbomachines is extremely complex due to the existence of various fluid dynamic phenomena and their interaction. At design and off-design operating conditions, the relative flow is subject to stationary unsteadiness, which includes the flow separation and wakes associated with passage pressure gradients, secondary flows, and boundary layer stability. It is also subject to periodic unsteadiness from the rotating stall and the cyclic flow phenomena induced by the casing. This paper describes the mechanical and optical design of a rotating laser-D

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9

Langtry, R. B., F. R. Menter, S. R. Likki, Y. B. Suzen, P. G. Huang, and S. Völker. "A Correlation-Based Transition Model Using Local Variables—Part II: Test Cases and Industrial Applications." Journal of Turbomachinery 128, no. 3 (2004): 423–34. http://dx.doi.org/10.1115/1.2184353.

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A new correlation-based transition model has been developed, which is built strictly on local variables. As a result, the transition model is compatible with modern computational fluid dynamics (CFD) methods using unstructured grids and massive parallel execution. The model is based on two transport equations, one for the intermittency and one for the transition onset criteria in terms of momentum thickness Reynolds number. The proposed transport equations do not attempt to model the physics of the transition process (unlike, e.g., turbulence models), but form a framework for the implementatio

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10

Schobeiri, Meinhard T., Burak Öztürk, and David E. Ashpis. "On the Physics of Flow Separation Along a Low Pressure Turbine Blade Under Unsteady Flow Conditions." Journal of Fluids Engineering 127, no. 3 (2005): 503–13. http://dx.doi.org/10.1115/1.1905646.

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The present study, which is the first of a series of investigations dealing with specific issues of low pressure turbine (LPT) boundary layer aerodynamics, is aimed at providing detailed unsteady boundary flow information to understand the underlying physics of the inception, onset, and extent of the separation zone. A detailed experimental study on the behavior of the separation zone on the suction surface of a highly loaded LPT-blade under periodic unsteady wake flow is presented. Experimental investigations were performed at Texas A&M Turbomachinery Performance and Flow Research Laborat

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11

Prosser, Daniel T., and Marilyn J. Smith. "Numerical characterization of three-dimensional bluff body shear layer behaviour." Journal of Fluid Mechanics 799 (June 21, 2016): 1–26. http://dx.doi.org/10.1017/jfm.2016.344.

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Three-dimensional bluff body aerodynamics are pertinent across a broad range of engineering disciplines. In three-dimensional bluff body flows, shear layer behaviour has a primary influence on the surface pressure distributions and, therefore, the integrated forces and moments. There currently exists a significant gap in understanding of the flow around canonical three-dimensional bluff bodies such as rectangular prisms and short circular cylinders. High-fidelity numerical experiments using a hybrid turbulence closure that resolves large eddies in separated wakes close this gap and provide new

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12

Mahallati, Ali, and Steen A. Sjolander. "Aerodynamics of a Low-Pressure Turbine Airfoil at Low Reynolds Numbers—Part II: Blade-Wake Interaction." Journal of Turbomachinery 135, no. 1 (2012). http://dx.doi.org/10.1115/1.4006320.

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Part II of this two-part paper presents the aerodynamic behavior of a low-pressure high-lift turbine airfoil, PakB, under the influence of incoming wakes. The periodic unsteady effects of wakes from a single upstream blade-row were measured in a low-speed linear cascade facility at Reynolds numbers of 25,000, 50,000 and 100,000 and at two freestream turbulence intensity levels of 0.4% and 4%. In addition, eight reduced frequencies between 0.53 and 3.2, at three flow coefficients of 0.5, 0.7 and 1.0 were examined. The complex wake-induced transition, flow separation and reattachment on the suct

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13

Müller-Schindewolffs, Christoph, Ralf-D. Baier, Joerg R. Seume, and Florian Herbst. "Direct Numerical Simulation Based Analysis of RANS Predictions of a Low-Pressure Turbine Cascade." Journal of Turbomachinery 139, no. 8 (2017). http://dx.doi.org/10.1115/1.4035834.

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The state-of-the-art design of turbomachinery components is based on Reynolds-averaged Navier–Stokes (RANS) solutions. RANS solvers model the effects of turbulence and boundary layer transition and therefore allow for a rapid prediction of the aerodynamic behavior. The only drawback is that modeling errors are introduced to the solution. Researchers and computational fluid dynamics developers are working on reducing these errors by improved model calibrations which are based on experimental data. These experiments do not typically, however, offer detailed insight into three-dimensional flow fi

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14

Ashton, Ryan, Francesco Viola, Simone Camarri, Francois Gallaire, and Giacomo Valerio Iungo. "Hub vortex instability within wind turbine wakes: Effects of wind turbulence, loading conditions, and blade aerodynamics." Physical Review Fluids 1, no. 7 (2016). http://dx.doi.org/10.1103/physrevfluids.1.073603.

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15

Pacciani, Roberto, Michele Marconcini, Andrea Arnone, and Francesco Bertini. "Predicting High-Lift Low-Pressure Turbine Cascades Flow Using Transition-Sensitive Turbulence Closures." Journal of Turbomachinery 136, no. 5 (2013). http://dx.doi.org/10.1115/1.4025224.

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This paper discusses the application of different transition-sensitive turbulence closures to the prediction of low-Reynolds-number flows in high-lift cascades operating in low-pressure turbine (LPT) conditions. Different formulations of the well known γ-R˜eθt model are considered and compared to a recently developed transition model based on the laminar kinetic energy (LKE) concept. All those approaches have been coupled to the Wilcox k-ω turbulence model. The performance of the transition-sensitive closures has been assessed by analyzing three different high-lift cascades, recently tested ex

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16

Talnikar, Chaitanya, Qiqi Wang, and Gregory M. Laskowski. "Unsteady Adjoint of Pressure Loss for a Fundamental Transonic Turbine Vane." Journal of Turbomachinery 139, no. 3 (2016). http://dx.doi.org/10.1115/1.4034800.

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High-fidelity simulations, e.g., large eddy simulation (LES), are often needed for accurately predicting pressure losses due to wake mixing and boundary layer development in turbomachinery applications. An unsteady adjoint of high-fidelity simulations is useful for design optimization in such aerodynamic applications. In this paper, we present unsteady adjoint solutions using a large eddy simulation model for an inlet guide vane from von Karman Institute (VKI) using aerothermal objectives. The unsteady adjoint method is effective in capturing the gradient for a short time interval aerothermal

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17

Urca, Tomer, Anup Kumar Debnath, Jean Stefanini, Roi Gurka, and Gal Ribak. "The Aerodynamics and Power Requirements of Forward Flapping Flight in the Mango Stem Borer Beetle (Batocera rufomaculata)." Integrative Organismal Biology 2, no. 1 (2020). http://dx.doi.org/10.1093/iob/obaa026.

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Synopsis The need for long dispersal flights can drive selection for behavioral, physiological, and biomechanical mechanisms to reduce the energy spent flying. However, some energy loss during the transfer of momentum from the wing to the fluid is inevitable, and inherent to the fluid–wing interaction. Here, we analyzed these losses during the forward flight of the mango stem borer (Batocera rufomaculata). This relatively large beetle can disperse substantial distances in search of new host trees, and laboratory experiments have demonstrated continuous tethered flights that can last for up to

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