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TECHNICAL PAPERS

Some Aspects of Wake-Wake Interactions Regarding Turbine Stator Clocking

[+] Author and Article Information
Maik Tiedemann, Friedrich Kost

Institute of Propulsion Technology, German Aerospace Center (DLR), Göttingen, Germany

J. Turbomach 123(3), 526-533 (Feb 01, 2000) (8 pages) doi:10.1115/1.1370158 History: Received February 01, 2000
Copyright © 2001 by ASME
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References

Arndt,  N., 1993, “Blade Row Interaction in a Multistage Low-Pressure Turbine,” ASME J Turbomach., 115, pp. 137–146.
Barankiewicz, W. S., and Hathaway, M. D., 1997, “Effects of Stator Indexing on Performance in a Low Speed Multistage Axial Compressor,” ASME Paper No. 97-GT-496.
Saren, V. E., Savin, N. M., Dorney, D. J., and Sondak, D. L., 1998, “Experimental and Numerical Investigation of Airfoil Clocking and Inter-Blade-Row Gap Effects on Axial Compressor Performance,” AIAA Paper No. 98-3413.
Dorney, D. J., Sondak, D. L., Cizmas P. G. A., Saren, V. E., and Savin, N. M., 1999, “Full-Annulus Simulations of Airfoil Clocking in a 1-1/2 Stage Axial Compressor,” ASME Paper No. 99-GT-23.
Gundy-Burlet, Karen L., and Dorney, Daniel, J., 1997, “Physics of Airfoil Clocking in Axial Compressors,” ASME Paper No. 97-GT-444.
Dorney, D. J., Sharma, O. P., and Gundy-Burlet, K. L., 1998, “Physics of Airfoil Clocking in a High Speed Axial Compressor,” ASME Paper No. 98-GT-82.
Sharma, O. P., Ni, R. H., and Tanrikut, S., 1994, “Unsteady Flows in Turbines-Impact on Design Procedure,” AGARD-LS-195.
Huber,  F. W., Johnson,  P. D., Sharma,  O. P., Staubach,  J. B., and Gaddis,  S. W., 1996, “Performance Improvement Through Indexing of Turbine Airfoils: Part 1—Experimental Investigation,” ASME J. Turbomach., 118, pp. 630–635.
Griffin,  L. W., Huber,  F. W., and Sharma,  O. P., 1996, “Performance Improvement Through Indexing of Turbine Airfoils: Part 2—Numerical Simulation,” ASME J. Turbomach., 118, pp. 636–642.
Halstead,  D. E., Wisler,  D. C., Okiishi,  T. H., Walker,  G. J., Hodson,  H. P., and Shin,  H.-W., 1997, “Boundary Layer Development in Axial Compressors and Turbines,” Part 1 of 4—Composite Picture, ASME J. Turbomach., 119, pp. 114–127,Part 2 of 4—Compressors, ASME J. Turbomach., 119, pp. 426–444, 1997.Part 3 of 4—LP Turbines, ASME J. Turbomach, 119, pp. 225–237, 1997.Part 4 of 4—Computations and Analyses, ASME J. Turbomach., 119, pp. 128–139, 1997.
Eulitz, F., Engel, K., and Gebing, H., 1996, “Numerical Investigations of the Clocking Effects in a Multistage Turbine,” ASME Paper No. 96-GT-26.
Dorney, D. J., and Sharma, O. P., 1996, “A Study of Turbine Performance Increases Through Airfoil Clocking,” AIAA Paper No. 96-2816.
Blair,  M. F., Dring,  R. P., and Joslyn,  H. D., 1988, “The Effects of Turbulence and Stator/Rotor Interactions on Turbine Heat Transfer, Part I—Design Operating Conditions,” ASME J. Turbomach., 111, pp. 97–103.
Johnston, D. A., and Fleeter, S., 1999, “Turbine Blade Unsteady Heat Transfer Change Due to Stator Indexing,” ASME Paper No. 99-GT-376.
Hsu,  S. T., and Wo,  A. M., 1997, “Reduction of Unsteady Blade Loading by Beneficial Use of Vortical and Potential Disturbances in an Axial Compressor With Rotor Clocking,” ASME J. Turbomach., 120, pp. 705–713.
Walker,  G. J., Hughes,  J. D., Köhler,  I., and Solomon,  W. J., 1998, “The Influence of Wake-Wake Interactions on Loss Fluctuations of a Downstream Axial Compressor Blade Row,” ASME J. Turbomach., 120, pp. 695–704.
Kost, F., and Kapteijn, C., 1997, “Application of Laser-Two-Focus Velocimetry to Transonic Turbine Flows,” 7th Int. Conference on “Laser Anemometry—Advances and Applications,” Univ. of Karlsruhe, Germany, September 8–11.
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Figures

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Sketch of the “windtunnel for rotating cascades” (RGG)
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Stage configuration at midspan and measurement position. “Trigger” marks the rotor position at which the data acquisition was started, i.e., “rotor pitch 0.”
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The L2F measurement volume (s=207 μm)
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Fast response total pressure probe with pneumatic reference
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Time-averaged Mach number and total pressure data for NGV/rotor gap of 0.5 cax,NGV, where cm=3 percent. The circles mark NGV positions of time-resolved plots in Fig. 13.
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Time-averaged turbulence and total pressure fluctuations for a NGV/rotor gap of 0.5 cax,NGV, where cm=3 percent. The circles mark NGV positions of time-resolved plots in Fig. 14.
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Time-averaged absolute flow angle data for a NGV/rotor gap of 0.5cax,NGV, where cm=3 percent. The circles mark NGV positions of time-resolved plots in Fig. 15.
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Time-averaged Mach number and total pressure data for a NGV/rotor gap of 0.38 cax,NGV, where cm=3 percent
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Time-averaged turbulence and total pressure fluctuation data for a NGV/rotor gap of 0.38 cax,NGV, where cm=3 percent
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Time-averaged absolute flow angle data for a NGV/rotor gap of 0.38cax,NGV, where cm=3 percent
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Comparison of time-averaged total pressure data for 0 percent and 3 percent NGV coolant ejection, the NGV/rotor gap is 0.5 cax,NGV
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Comparison of time-averaged total pressure fluctuation data for 0 percent and 3 percent NGV coolant ejection, the NGV/rotor gap is 0.5 cax,NGV
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Ensemble-averaged Mach number and total pressure traces for five different NGV clocking positions; Cm=3 percent, and the axial gap is 0.5Cax,NGV
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Turbulence and total pressure fluctuation (normalized by the time-averaged total pressure) traces for five different NGV clocking positions; Cm=3 percent, and the axial gap is 0.5Cax,NGV
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Absolute flow angle traces for five different NGV clocking positions; Cm=3 percent, and the axial gap is 0.5Cax,NGV
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Comparison of total pressure and RMS values; Cm=3 percent, the axial gap is 0.5Cax,NGV and the NGV pitch is 1.104

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