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TECHNICAL PAPERS

Aerodynamic Response of Turbomachinery Blade Rows to Convecting Density Wakes

[+] Author and Article Information
H. S. Wijesinghe, C. S. Tan, E. E. Covert

Gas Turbine Laboratory, Department of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA 02139

J. Turbomach 124(2), 269-274 (Apr 09, 2002) (6 pages) doi:10.1115/1.1311287 History: Received February 01, 2000; Online April 09, 2002
Copyright © 2002 by ASME
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References

Basic Research Issues in Aerodynamics, Structural Dynamics and Control of High Cycle Fatigue. Summary of a Workshop held at the Gas Turbine Laboratory, MIT, October 1995.
Kerrebrock, J. L., and Mikolajczak, A. A., 1970, “Intra-Stator Transport of Rotor Wakes and its Effect on Compressor Performance,” ASME Paper No. 70-GT-39.
Valkov, Theodore V., 1992, “Control of Unsteady Flow in a Stator Blade Row Interacting With Upstream Moving Wakes.” S. M. Thesis, Massachusetts Institute of Technology, Department of Aeronautics and Astronautics; also GTL Report No. 255, May.
Platzer, M. F., 1978, “Unsteady Flows In Turbomachines—A Review of Current Developments,” AGARD CP-227, Paper 33.
Marble,  F. E., 1993, “Response of a Thin Airfoil Encountering a Strong Density Discontinuity,” ASME J. Fluids Eng., 115, pp. 580–589.
Ramer, B. E., Wijesinghe, H. S., Tan, C. S. and Covert, E. E., 1997, “Aerodynamic Response of Turbomachinery Blade Rows to Convecting Density Wakes,” Proc. ASME Aerospace Division, ASME AD-Vol. 55.
Wisler, D. C., 1977, “Core Compressor Exit Stage Study, Volume I—Design Report,” NASA CR-135391, NASA Lewis Research Center, Dec.
Hoying, D. A., 1996, “Blade Passage Flow Structure Effects on Axial Compressor Rotating Stall Inception,” Ph.D. thesis, Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, Sept.
Tam,  C. K. W., and Webb,  J. C., 1993, “Dispersion-Relation-Preserving Finite Difference Schemes for Computational Acoustics,” J. Comput. Phys., 107, pp. 262–281.
Chieng,  C. C., and Launder,  B. E., 1980, “On the Calculation of Turbulent Heat Transport Downstream From an Abrupt Pipe Expansion,” Numer. Heat Transfer, Part A, 3, pp. 189–207.
Giles, M. B., 1988, “Non-Reflecting Boundary Conditions for the Euler Equations,” CFDL-TR-88-1, Computational Fluid Dynamics Laboratory, Massachusetts Institute of Technology, Feb.

Figures

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Density wake convecting through a compressor blade row
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Schematic of the computational domain and boundary conditions
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Fluctuations in (1) azimuthal force coefficient, (2) axial force coefficient, and (3) moment coefficient (positive clockwise about the midchord) during passage of a density wake. Three distinct regions can be identifies in the response. w/c=0.2,ρ*=−0.333,M=0.15.
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Suction surface pressure distribution during passage of a density wake width, w/c=0.2 and ρ*=−0.333
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Perturbation velocity vectors indicate a pair of counterrotating vortices in the blade passage; w/c=0.2,ρ*=−0.333,M=0.15,τ=0.78.
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Maximum fluctuation in the azimuthal force coefficient as functions of density wake width and density parameter; M=0.15
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Blade suction surface pressure contours show the upstream motion of the blade passage shock wave during passage of a density wake, w/c=0.2 and ρ*=−0.333. The dark band initially at x/c=0.25 is the shock front. M=0.87.
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Blade suction surface pressure contours show the temporary suppression of the blade passage shock wave during passage of a density wake, w/c=0.4 and ρ*=−0.6. The dark band at x/c=0.25 is the shock front. M=0.87.
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Density contour image showing trapped density wake fluid at the blade trailing edge; w/c=0.2,ρ*=−0.333,M=0.15,τ=1.28
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Fluctuation of the suction surface flow separation and re-attachment points during passage of a density wake; w/c=0.2,ρ*=−0.333,M=0.15.
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Maximum change in the suction surface separation point from the mean baseline position as a function of wake width and density ratio; M=0.15.
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Maximum fluctuation in the blade azimuthal force coefficient in the secondary response region as a function of wake width and density ratio; M=0.15 (amp=amplitude)

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