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Influence of Rotor Tip Blockage on Near Stall Blade Vibrations in an Axial Compressor Rig

[+] Author Affiliations
Daniel Möller, Maximilian Jüngst, Heinz-Peter Schiffer

Technische Universität Darmstadt, Darmstadt, Germany

Thomas Giersch, Frank Heinichen

Rolls-Royce Deutschland, Blakenfelde-Mahlow, Germany

Paper No. GT2017-63660, pp. V07BT36A009; 15 pages
doi:10.1115/GT2017-63660
From:
  • ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition
  • Volume 7B: Structures and Dynamics
  • Charlotte, North Carolina, USA, June 26–30, 2017
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-5093-0
  • Copyright © 2017 by Rolls-Royce Deutschland Ltd & Co KG

abstract

Rotor blade vibrations observed in the Darmstadt transonic compressor rig are investigated in this paper. The vibrations are non-synchronous and occur in the near stall operating region. Rotor tip flow fluctuations traveling near the leading edge against the direction of rotation (in the rotor relative frame of reference) with about 50% blade tip speed are found to be the reason for the occurrence of the vibrations. The investigations show, that the blockage at the rotor tip is an important factor for the aeroelastic stability of the compressor in the near stall region. It is found, that by application of a recirculating tip injection casing treatment, the aeroelastic stability increases as a result of reduced blockage in the rotor tip region.

Copyright © 2017 by Rolls-Royce Deutschland Ltd & Co KG

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