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An Investigation of Wake-Shock Interactions in a Transonic Compressor With DPIV and Time-Accurate CFD

[+] Author Affiliations
Steven E. Gorrell, David Car, Steven L. Puterbaugh

Air Force Research Laboratory, Wright-Patterson AFB, OH

Jordi Estevadeordal

Innovative Scientific Solutions, Inc., Dayton, OH

Theodore H. Okiishi

Iowa State University, Ames, IA

Paper No. GT2005-69107, pp. 1499-1511; 13 pages
doi:10.1115/GT2005-69107
From:
  • ASME Turbo Expo 2005: Power for Land, Sea, and Air
  • Volume 6: Turbo Expo 2005, Parts A and B
  • Reno, Nevada, USA, June 6–9, 2005
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4730-6 | eISBN: 0-7918-3754-8
  • Copyright © 2005 by ASME

abstract

The effects of varying axial gap on the unsteady flow field between the stator and rotor of a transonic compressor stage are important because they can result in significant changes in stage mass flow rate, pressure rise and efficiency. Some of these effects are analyzed with measurements using Digital Particle Image Velocimetry (DPIV) and with time-accurate simulations using the 3D unsteady Navier-Stokes CFD solver TURBO. Generally there is excellent agreement between the measurements and simulations, instilling confidence in both. Strong vortices of the wake can break up the rotor bow shock and contribute to loss. At close spacing vortices are shed from the trailing edge of the upstream stationary blade row in response to the unsteady, discontinuous pressure field generated by the downstream rotor bow shock. Shed vortices increase in size and strength and generate more loss as spacing decreases, a consequence of the effective increase in rotor bow shock strength at the stationary blade row trailing edge. A relationship for the change in shed vorticity as a function of rotor bow shock strength is presented that predicts the difference between close and far spacing TURBO simulations.

Copyright © 2005 by ASME

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