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TECHNICAL PAPERS

The Effect of Variable Chord Length on Transonic Axial Rotor Performance

[+] Author and Article Information
William B. Roberts, Albert Armin, George Kassaseya

Airfoil Management Co. and Airfoil Technologies International, Compton, CA 90220

Kenneth L. Suder, Scott A. Thorp, Anthony J. Strazisar

NASA Glenn Research Center, Cleveland, OH

J. Turbomach 124(3), 351-357 (Jul 10, 2002) (7 pages) doi:10.1115/1.1459734 History: Received January 18, 2001; Online July 10, 2002
Copyright © 2002 by ASME
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References

Sallee, G. P., Kruckenburg, H. D., and Toomey, E. H., 1978, “Analysis of Turbofan Engine Performance Deterioration and Proposed Follow-on Tests,” NASA CR-134769.
Kramer, W. H., Paas, J. E., Smith, J. J., and Wulf, R. H., 1980, “CF6-6D Engine Short-term Performance Deterioration,” NASA CR-159830.
Covey, R. R., Mascetti, G. J., and Roessler, W. U., 1978, “Examination of Commercial Aviation Operational Energy Conservation Strategies,” The Aerospace Corporation, Aerospace Report No. ATR-79 (7761)-1, Vol. 2.
Proc., DOE/FAA Symposium on Commercial Aviation Energy Conservation Strategies, Apr., 1981.
Suder,  K. L., Chima,  R. V., Strazisar,  A. J., and Roberts,  W. B., 1994, “The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor,” ASME J. Turbomach., 117, pp. 491–505.
Roberts,  W. B., 1995, “Advanced Turbofan Blade Refurbishment Technique,” ASME J. Turbomach., Tech. Brief, 117, pp. 666–667.
Reid,  L., and Urasek,  D. C., 1973, “Experimental Evaluation of the Effects of a Blunt Leading Edge on the Performance of a Transonic Rotor,” ASME J. Eng. Power, 95, pp. 199–204.
Roberts, W. B., 1984, “Axial Compressor Performance Restoration by Blade Profile Control,” ASME Paper No. 84-GT-232.
Roberts, W. B., 1995, “A Study of the Performance and Stalling Behavior of JT8D Short Chord Compressor Blade Elements,” Airfoil Management-Airfoil Technologies International Internal Note (Oct.).
Roberts, W. B., 1996, “A Study of the Performance and Stalling Behavior of CF6-80C2 Short Chord Compressor Blade Elements,” Airfoil Technologies International Internal Note (May).
Reid, L., and Moore, R. D., 1978, “Design and Overall Performance of Four Highly-Loaded, High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor,” NASA Tech. Memo., 1337.
Reid, L., and Moore, R. D., 1978, “Performance of a Single-Stage Axial-Flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1.19 and 1.26, Respectively, and with Design Pressure Ratio of 1.82,” NASA Tech. Memo., 1338.
Model, D., and Roberts, W. B., 1997, “A New Lease of Life for Gas Turbine Airfoils,” Aircraft Technology Engineering and Maintenance Engine Yearbook, 1996–1997.

Figures

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Schematic of blade leading edge—(a) Blunt leading edge due to erosion, (b) Recontoured leading edge
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NASA-Glenn single-stage transonic compressor test facility
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Location of aerodynamic survey stations
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Simulated erosion of 5% of chord over the outer 50% of span
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Schematic of tested blade installation configurations
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Rotor overall performance at 60, 80, and 100% speed for three blade installation configurations. Stalling massflow denoted by vertical bars. Crosses denote error bars. □, halves; ▵, quadrants; * alternating.
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Radial profiles of efficiency for 80% speed at a massflow rate of 17.5 kg/s
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Rotor performance at 100% speed, maximum massflow operating point—□, halves; ▵, quadrants; *, alternating
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Rotor performance at 100% speed, midway between maximum and near-stall operating points—□, halves; ▵, quadrants; *, alternating
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Rotor performance at 100% speed, near-stall operating point—□, halves; ▵, quadrants; *, alternating
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Static pressure distributions over the blade tip for three operating conditions at 100% design speed

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