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Effects of the Swirl Velocity of a Jet in Crossflow From Fan Assemblies Mounted on Lifting Surfaces

[+] Author Affiliations
Alexandros Terzis, Pavlos K. Zachos, Pericles Pilidis

Cranfield University, Bedfordshire, UK

Charilaos Kazakos, Nikolaos Papadopoulos, Anestis I. Kalfas

Aristotle University of Thessaloniki, Thessaloniki, Greece

Paper No. GT2010-23357, pp. 831-842; 12 pages
doi:10.1115/GT2010-23357
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 3: Controls, Diagnostics and Instrumentation; Cycle Innovations; Marine
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4398-7 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

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 cross flow, and numerically, the effect of the swirl velocity of jets in cross flow, downstream of the injection hole. The experimental results indicated an agreement with typically straight jets in cross flow (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 (CVP), 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 cross flow 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 contra rotating 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.

Copyright © 2010 by ASME

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