Laser velocity measurements are conducted in a swept propfan rotor in order to investigate the local transonic flow region on the suction surface at high subsonic inlet Mach numbers. The velocity measurements are accompanied by a three-dimensional Navier–Stokes calculation for a selected operating point. The good agreement between computed and measured flow field gives some confidence to study the local three-dimensional passage shock on the suction surface by using the numerical procedure. Apart from the computed three-dimensional shock, structure is investigated in detail. By considering streamlines, it is concluded whether the shock wave is normal or oblique. The results are compared with the one-dimensional shock conditions.
Issue Section:
Research Papers
1.
Chima
R. V.
Strazisar
A. J.
1983
, “Comparison of Two- and Three-Dimensional Flow Computations With Laser Anemometer Measurements in a Transonic Compressor Rotor
,” ASME Journal of Engineering for Power
, Vol. 105
, pp. 596
–605
.2.
Copenhaver
W. W.
Hah
C.
Puterbaugh
S. L.
1993
, “Three-Dimensional Flow Phenomena in a Transonic, High-Throughflow, Axial-Flow Compressor Stage
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 115
, pp. 240
–248
.3.
Dawes
W. N.
1987
, “A Numerical Analysis of the Three-Dimensional Viscous Flow in a Transonic Compressor Rotor and Comparison With Experiment
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 109
, pp. 83
–90
.4.
Dupslaff, M., Wehlitz, P., and Schimming, P., 1989, “Propfan Technology,” DGLR/AAAf/RAES European Forum: The Evaluation of Regional Aircraft Technologies and Certification, Apr.
5.
Epstein
A. H.
Kerrebrock
J. L.
Thompkins
W. T.
1979
, “Shock Structure in Transonic Compressor Rotors
,” AIAA Journal
, Vol. 17
, No. 4
, pp. 375
–379
.6.
Hah
C.
Wennerstrom
A. J.
1991
, “Three-Dimensional Flowfields Inside a Transonic Compressor With Swept Blades
,” ASME JOURNAL OF TURBOMACHINERY
, Vol. 113
, pp. 241
–251
.7.
Helming, K., 1994, “Numerical Analysis of Sweep and Dihedral Effects in Propfan Rotors,” Presented at AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, June 27–29, Indianapolis, IN.
8.
Melake, A., 1992, “Numerical Flow Simulation and Analysis of a Shrouded Propfan Rotor,” AIAA Paper No. 92-3773.
9.
Melling, A., 1986, “Seeding Gas Flows for Laser Anemometry,” Advanced Instrumentation for Aero Engine Components, AGARD CP-399.
10.
Miller
G. R.
Lewis
G. W.
Hartman
M. J.
1961
, “Shock Losses in Transonic Compressor Blade Rows
,” ASME Transactions
, Vol. 83
, No. 3
, pp. 235
–242
.11.
Pierzga
M. J.
Wood
J. R.
1985
, “Investigation of the Three-Dimensional Flow Field Within a Transonic Fan Rotor: Experiment and Analysis
,” ASME Journal of Engineering for Gas Turbines and Power
, Vol. 107
, pp. 437
–449
.12.
Prince
D. C.
1980
, “Three Dimensional Shock Structures for Transonic/Supersonic Compressor Rotors
,” Journal of Aircraft
, Vol. 17
, No. 1
, pp. 28
–37
.13.
Rabe, D., Hoying D., and Koff S., 1991, “Application of Sweep to Improve Efficiency of a Transonic Fan: Part II. Performance and Laser Test Results,” AIAA Paper No. 91-2544.
14.
Schodl, R., 1986, “Laser-Two-Focus Velocimetry,” Advanced Instrumentation for Aero Engine Components, AGARD-CP-399, Paper 7, Philadelphia, PA.
15.
Smith
L. H.
Yeh
Hsuan
1963
, “Sweep and Dihedral Effects in Axial-Flow Turbomachinery
,” ASME Journal of Basic Engineering
, Vol. 85
, pp. 401
–416
.16.
Strazisar, A. J., and Chima, R. V., 1980, “Comparison Between Optical Measurements and a Numerical Solution of the Flow Field Within a Transonic Axial-Flow Compressor Rotor,” AIAA Paper No. 80-1078.
17.
Wennerstrom
A. J.
Puterbaugh
S. L.
1984
, “A Three-Dimensional Model for the Prediction of Shock Losses in Compressor Blade Rows
,” ASME Journal of Engineering for Gas Turbines and Power
, Vol. 106
, No. 2
, pp. 295
–299
.18.
Wisler, D. C., 1977, “Shock Wave and Flow Velocity Measurement in a High-Speed Fan Rotor Using the Laser Velocimeter,” ASME Journal of Engineering for Power, pp. 181–188.
19.
Wuerker, R. F., Kobayashi, R. J., Heflinger, L. O., and Ware, T. C., 1974, “Application of Holography to Flow Visualization Within Rotating Compressor Blade Row,” NASA CR 121264.
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