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Research Papers: Gas Turbines: Cycle Innovations

Effects of Swirl Velocities From Fan Assemblies Mounted on Lifting Surfaces

[+] Author and Article Information
Alexandros Terzis

 EPFL-STI-IGM-LTT, Lausanne CH-1015, Switzerlandalexandros.terzis@epfl.ch

Charilaos Kazakos

 Imperial College London, South Kensington Campus, London SW7 2AZ, UKcharilaos.kazakos09@imperial.ac.uk

Nikolaos Papadopoulos

 Imperial College London, South Kensington Campus, London SW7 2AZ, UKnikolaos.papadopoulos09@imperial.ac.uk

Anestis Kalfas

School of Engineering, Aristotle University of Thessaloniki, Building D, GR-54124 Thessaloniki, Greeceakalfas@auth.gr

Pavlos K. Zachos

Department of Power and Propulsion, Cranfield University, Bedfordshire MK43 0AL, UKp.zachos@cranfield.ac.uk

Pericles Pilidis

Department of Power and Propulsion, Cranfield University, Bedfordshire MK43 0AL, UKp.pilidis@cranfield.ac.uk

J. Eng. Gas Turbines Power 133(3), 031702 (Nov 11, 2010) (9 pages) doi:10.1115/1.4002099 History: Received May 10, 2010; Revised May 11, 2010; Published November 11, 2010; Online November 11, 2010

The penetration of a jet of fluid into a traversal moving stream is a basic configuration of a wide range of engineering applications, such as film cooling and V/STOL aircrafts. This investigation examines experimentally the effect of blowing ratio of fans in crossflow, and numerically, the effect of the swirl velocity of jets in crossflow, downstream of the injection hole. The experimental results indicated an agreement with typically straight jets in crossflow (no vorticity), illustrating that the trace of the jet, remains close to the wall and subsequently enhance cooling at low blowing ratios in the case of turbine blade applications. However, the rotation of the jet results in an imparity between the two parts of the counter rotating vortex pair and as a consequence, the injected fluid not only bends in the direction of the main stream but also diverts in the direction of the rotation in order to conserve its angular momentum. The induction of the swirl velocity on the injected jet destructs one of the two parts of the kidney vortex, which entrains fluid from the crossflow to the jet promoting the mixing between the two fluids while the trace of a swirled jet remains closer to the wall downstream of the injection hole. Finally, the use of contrarotating jet or fan configurations reduces the wall shear stress in a very great extent, leading to better thermal protection of turbine blades, as well as cancels out the yaw torques of each fan separately, resulting in better flight control of typical lift surface.

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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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Figure 2

Plane traversing system for probe access

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Figure 3

Comparison between the computational tool and the experimental results at three blowing rations (X=D/2+D and Y/D=0): (a) velocity profile X=D+D/2, Y=0, and BR=1.25, (b) velocity profile X=D+D/2, Y=0, and BR=1.00, and (c) velocity profile X=D+D/2, Y=0, and BR=0.75

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Figure 4

Mesh structure around the fan and control volume: (a) mesh structure near the cross section of the injection hole and (b) control volume for jet trace simulation by the use of periodic boundaries

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Figure 7

Horseshoe vortex and surface jet trace (a) BR=0.75 and (b) BR=1.25

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Figure 8

Effects of the swirl velocity on the CVP formed by the interaction between jet and crossflow X=0.5D: (a) BR=0.75, (b) BR=1.00, and (c) BR=1.25

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Figure 9

Normalized wall shear stress BR=1 and SR=0

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Figure 10

Normalized wall shear stress X/D=1.5 and BR=1

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Figure 11

Bias of the jet trace in the wake

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Figure 12

Effect of contrarotating fan-configuration: (a) wall shear stress X=1.5D and (b) velocity field X=2.5D and BR=1.00

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Figure 6

Vortical structures in the trailing edge of the fan for (a) BR=0.75 and (b) BR=1.25

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Figure 5

Total pressure charts: (a) swirl jet trace BR=0.75, (b) swirl jet trace BR=1.00, and (c) swirl jet trace BR=1.25

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Figure 1

Schematic of the test section with the plane measurements

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