The effect on rotor work of the phase of an upstream wake relative to the rotor is examined computationally and analytically for a transonic blade row. There can be an important impact on the time-mean performance when the time-dependent circulation of the shed vortices in the wake is phase-locked to the rotor position, as it occurs when there is strong interaction between the rotor static pressure field and the upstream vanes. The rotor work is found to depend on the path of the wake vortices as they travel through the blade passage; for the configurations examined, the calculated change in time-mean rotor work was approximately 3%. It is shown that the effect on work input can be analyzed in terms of the influence of the time-mean relative stagnation pressure nonuniformity associated with the unsteady (but phase-locked) wake vortex flow field, in that the changes in vortex path alter the location of the nonuniformity relative to the rotor. Lower pressure rise and work input occurs when the rotor blade is embedded in a region of low time-mean relative stagnation pressure than when immersed in a region of high relative stagnation pressure. In addition to the work changes, which are essentially two-dimensional effects, it is demonstrated that the location of the wake may affect the tip clearance flow, implying a potential impact on the pressure rise capability and rotor stability limits. Model calculations are presented to give estimates of the magnitude and nature of this phenomenon.
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e-mail: sprn@alum.mit.edu
e-mail: sgorrell@byu.edu
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April 2011
Research Papers
Effects of Upstream Wake Phasing on Transonic Axial Compressor Performance
S. P. R. Nolan,
S. P. R. Nolan
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
e-mail: sprn@alum.mit.edu
MIT
, Cambridge, MA 02139
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B. B. Botros,
B. B. Botros
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
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C. S. Tan,
C. S. Tan
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
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J. J. Adamczyk,
J. J. Adamczyk
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
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E. M. Greitzer,
E. M. Greitzer
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
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S. E. Gorrell
S. E. Gorrell
Department of Mechanical Engineering,
e-mail: sgorrell@byu.edu
Brigham Young University
, Provo, UT 84602
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S. P. R. Nolan
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139e-mail: sprn@alum.mit.edu
B. B. Botros
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
C. S. Tan
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
J. J. Adamczyk
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
E. M. Greitzer
Department of Aeronautics and Astronautics, Gas Turbine Laboratory,
MIT
, Cambridge, MA 02139
S. E. Gorrell
Department of Mechanical Engineering,
Brigham Young University
, Provo, UT 84602e-mail: sgorrell@byu.edu
J. Turbomach. Apr 2011, 133(2): 021010 (12 pages)
Published Online: October 21, 2010
Article history
Received:
July 20, 2009
Revised:
August 20, 2009
Online:
October 21, 2010
Published:
October 21, 2010
Citation
Nolan, S. P. R., Botros, B. B., Tan, C. S., Adamczyk, J. J., Greitzer, E. M., and Gorrell, S. E. (October 21, 2010). "Effects of Upstream Wake Phasing on Transonic Axial Compressor Performance." ASME. J. Turbomach. April 2011; 133(2): 021010. https://doi.org/10.1115/1.4000572
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