Research Papers: Flows in Complex Systems

Large-Eddy Simulation of a Tunnel Ventilation Fan

[+] Author and Article Information
Mario Fiorito

Dipartimento di Ingegneria Meccanica e Aerospaziale,
Sapienza Università di Roma,
Via Eudossiana 18,
Rome 00184, Italy

Anthony G. Sheard

Fläkt Woods Ltd.,
Colchester, Essex, CO4 5ZD, UK

Contributed by the Fluids Engineering Division of ASME for publication in the Journal of Fluids Engineering. Manuscript received October 10, 2012; final manuscript received February 11, 2013; published online April 17, 2013. Assoc. Editor: Chunill Hah.

J. Fluids Eng 135(7), 071102 (Apr 17, 2013) (9 pages) Paper No: FE-12-1509; doi: 10.1115/1.4023686 History: Received October 10, 2012; Revised February 11, 2013

In this paper we discuss a computational method focused on the prediction of unsteady aerodynamics, adequate for industrial turbomachinery. Here we focus on a single rotor device selected from a new family of large tunnel ventilation axial flow fans. The flow field in the fan was simulated using the open source code OpenFOAM, with a large-eddy simulation (LES) approach. The sub-grid scale (SGS) closure relied on a one-equation model, that requires us to solve a differential transport equation for the modeled SGS turbulent kinetic energy. The use of such closure was here considered as a remedial strategy in LES of high-Reynolds industrial flows, being able to tackle the otherwise insufficient resolution of turbulence spectrum. The results show that LES of the fan allows to predict the pressure rise capability of the fan and to reproduce the most relevant flow features, such as three-dimensional separation and secondary flows.

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Fig. 1

Rotating channel flow

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Fig. 2

Rotating channel flow: normalized velocity distribution u+. Blue: standard Smagorinsky, green: dynamic Smagorinsky, red, purple: locDynbound, symbols: DNS (see online version for color).

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Fig. 3

Q isolines in fully developed channel flow. Top: rotating channel, streamwise section (left) and crosswise section (right). Bottom: nonrotating channel streamwise section (left) and crosswise section (right).

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Fig. 4

Linear compressor cascade. Top: geometry [36]; bottom left: computational domain; bottom right: grid detail.

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Fig. 5

Streamwise velocity in a reference plane placed at 37% of chord downstream of the trailing edge. Top: exp, middle: LES, bottom: SAS.

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Fig. 6

Ratio between SGS and molecular viscosity at different locations of blade span: top 5%; middle 50%; bottom 95%

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Fig. 7

Large high temperature fan prototype [15]

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Fig. 8

Power (left y-axis) and total pressure rise maps (right y-axis) at 4 pole speed

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Fig. 9

Fan JFM 224: computational domain (left) and discretization of the hub wall (right)

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Fig. 10

Fan JFM 224: ratio between resolved and total k

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Fig. 11

Isosurface of Q = 200 colored with Urel,mag

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Fig. 12

Isosurface of Q = 200 and streamlines—hub region

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Fig. 13

Isosurface of Q = 200 and streamlines—tip region

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Fig. 14

Ratio of νsgs/ν in two different time steps (at a distance of 0.5 FTT) and time averaged value (right)

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Fig. 15

Urel magnitude in two different time steps (at a distance of 0.5 FTT) and time averaged value (right)

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Fig. 16

Urel magnitude in three axial sections: on the blade, in the near wake, and in the far wake

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Fig. 17

Total pressure contours at different cross-planes (S1 to S3, top to bottom) for three consecutive time steps (t1 to t3, left to right)



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