Full Content is available to subscribers

Subscribe/Learn More  >

Investigation of Loss Generation in an Embedded Transonic Fan Stage at Several Gaps Using High Fidelity, Time-Accurate CFD

[+] Author Affiliations
Michael G. List

Air Force Research Laboratory, Wright-Patterson AFB, OH

Steven E. Gorrell

Brigham Young University, Provo, UT

Mark G. Turner

University of Cincinnati, Cincinnati, OH

Paper No. GT2008-51220, pp. 2599-2609; 11 pages
  • ASME Turbo Expo 2008: Power for Land, Sea, and Air
  • Volume 6: Turbomachinery, Parts A, B, and C
  • Berlin, Germany, June 9–13, 2008
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4316-1 | eISBN: 0-7918-3824-2
  • Copyright © 2008 by ASME and U.S. Government


The Blade-Row Interaction (BRI) rig at the Air Force Research Laboratory (AFRL), Compressor Aero Research Laboratory (CARL), has been simulated at three axial gaps between the highly loaded upstream stator row and the downstream transonic rotor using TURBO. Previous work with the Stage Matching Investigation (SMI) demonstrated a strong dependence of mass flow rate, efficiency, and pressure ratio on the axial spacing between an upstream wake generator and the downstream rotor through the variation of the axial gap. Several loss producing mechanisms were discovered and related to the spacings, referred to as close, mid, and far. In the SMI work, far spacing had the best performance. The BRI experiments were a continuation of the SMI work with the wake generator replaced by a swirler row to turn the flow and a deswirler row to create a wake by diffusion. Results of the BRI experiments showed a performance degradation between mid and far spacing which was not observed in SMI. This trend is seen in the numerical work as well, and the time-averaged data shows that the majority of this performance change occurred in the rotor. An unsteady separation bubble periodically forms and collapses as shocks reflect through the stator passage, creating additional aerodynamic blockage. The shed vortices induced by the unsteady loading and unloading of the stator trailing edge are chopped, with a frequency related to the spacing, by the rotor leading edge and ingested by the rotor. Once ingested the vortices interact in varying degrees with the rotor boundary layer. A treatment of the loss production in the BRI rig is given based on the time-accurate and time-averaged, high-fidelity TURBO results.

Copyright © 2008 by ASME and U.S. Government



Interactive Graphics


Country-Specific Mortality and Growth Failure in Infancy and Yound Children and Association With Material Stature

Use interactive graphics and maps to view and sort country-specific infant and early dhildhood mortality and growth failure data and their association with maternal

Citing articles are presented as examples only. In non-demo SCM6 implementation, integration with CrossRef’s "Cited By" API will populate this tab (http://www.crossref.org/citedby.html).

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In