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Numerical Study of the Stagger Angle Effects in Forward Swept Axial Compressor Rotor Passages

[+] Author Affiliations
P. V. Ramakrishna, M. Govardhan

Indian Institute of Technology Madras, Chennai, India

Paper No. GT2010-23160, pp. 443-453; 11 pages
doi:10.1115/GT2010-23160
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

In the present numerical work, an axial compressor rotorstator stage is studied for three rotor sweep configurations (Unswept, 20° Tip chordline swept and 20° Axially swept) and for three stagger configurations (0°, + 3° and +5°). CFD results with the unswept rotor and the 20° TCS rotor are well validated with the experiments for the designed stagger angle case. Results show that sections near the tip are subjected to lower incidences and the opposite effect is observed with increasing the stagger angle. The included sweep and dihedral schemes in axial sweeping resulted in the AXS rotor to undergo high degree of variations in the performance with stagger angle. TCS passages are subjected to low loss levels when compared with the UNS rotor at the designed stagger. This ability is found to diminish with increase in the stagger angle. AXS rotor passages are subjected to the low loss levels always. The idea of employing positive dihedral in addition to forward sweeping is thus thoughtful with regard to the stagger variations as well. As the stagger angle is increased, the tipward centrifugation of the boundary layer fluid is reduced, but the hub endwall boundary layer migration is observed to increase towards the suction side corner for some rotors resulting in corner vortex like structure towards the hub trailing edge. These secondary flows are less with the true sweeping. The separation point is shifted to upstream locations on the blade at higher stagger angles due to low streamwise velocities and higher adverse pressure gradients.

Copyright © 2010 by ASME
Topics: Compressors , Rotors

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