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TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

High-Temperature Fatigue Properties of Single Crystal Superalloys in Air and Hydrogen

[+] Author and Article Information
N. K. Arakere

Mechanical Engineering Department, University of Florida, Gainesville, FL 32611-6300e-mail: nagaraj@ufl.edu

J. Eng. Gas Turbines Power 126(3), 590-603 (Aug 11, 2004) (14 pages) doi:10.1115/1.1501075 History: Received December 01, 2000; Revised March 01, 2001; Online August 11, 2004
Copyright © 2002 by ASME
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References

Cowles, B. A., 1996, “High Cycle Fatigue in Aircraft Gas Turbines—An Industry Perspective,” Int. J. Fatigue, pp. 1–16.
Deluca, D., and Annis, C., 1995, “Fatigue in Single Crystal Nickel Superalloys,” Office of Naval Research, Department of the Navy FR23800, Aug.
VerSnyder,  F. L., and Guard,  R. W., 1960, “Directional Grain Structure for High Temperature Strength,” Trans. ASM, 52, p. 485.
McLean, M., 1983, “Mechanical Behavior: Superalloys,” Directionally Solidified Materials for High Temperature Service, The Metals Society, London, p. 151.
Moroso, J., 1999, “Effect of Secondary Orientation on Fatigue Crack Growth in Single Crystal Turbine Blades,” M. S. thesis, Mechanical Engineering Department, University of Florida, Gainesville, FL, May.
Arakere, N. K., and Swanson, G., 2000, “Effect of Crystal Orientation on Fatigue Failure of Single Crystal Nickel Base Turbine Blade Superalloys,” presented at the ASME IGTI conference May 8–11, Munich, and accepted for publication in the ASME Journal of Gas Turbines and Power. ASME J. Eng. Gas Turbines Power.
Swanson, G., and Arakere, N. K., 2000, “Fatigue Failure of Single Crystal Nickel Base Turbine Blade Superalloys,” NASA Technical Paper TP-2000-210074.
Cunningham, S., DeLuca, D., and Haake, F., 1996, “Crack Growth and Life Prediction in Single-Crystal Nickel Superalloys, Vol. 1,” Wright Laboratory WL-TR-94-4089, Feb.
Cunningham, S., DeLuca, D., and Haake, F., 1994, “Crack Growth and Life Prediction in Single-Crystal Nickel Superalloys, Vol. 2,” Wright Laboratory WL-TR-96-4048, Aug.
Telesman, J., and Ghosn, L., 1995, “Fatigue Crack Growth Behavior of PWA 1484 Single Crystal Superalloy at Elevated Temperatures,” International Gas Turbine and Aeroengine Congress and Exposition, June.
Pratt & Whitney, 1998, “SSME-AT HPFTP 1st Stage Blade Failure Investigation Final Report,” Pratt & Whitney, West Palm Beach, FL, Feb.
Pratt & Whitney, 1996, “SSME Alternate Turbopump Development Program HPFTP Critical Design Review,” P&W FR24581-1 Dec. 23, NASA Contract NAS8-36801.
Kear,  B. H., and Piearcey,  B. J., 1967, “Tensile and Creep Properties of Single Crystals of the Nickel-Base Superalloy Mar-M 200,” Trans. AIME, 239, p. 1209.
Dalal, R. P., Thomas, C. R., and Dardi, L. E., 1984, “The Effect of Crystallographic Orientation on the Physical and Mechanical Properties of an Investment Cast Single Crystal Nickel-Base Superalloy,” Superalloys, M. Gell, C. S. Kortovich, R. H. Bricknell, W. B. Kent, and J. F. Radavich, eds., TMS-AIME, Warrendale, OH, pp. 185–197.
Stouffer, D. C., and Dame, L. T., 1996, Inelastic Deformation of Metals, John Wiley and Sons, New York.
Deluca, D. P., and Cowles, B. A., 1989, “Fatigue and Fracture of Single Crystal Nickel in High Pressure Hydrogen,” Hydrogen Effects on Material Behavior, N. R. Moody and A. W. Thomson, eds., TMS, Warrendale, PA.

Figures

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Stage I type global octahedral failure mode (289)
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Noncrystallographic stage II type of failure (289)
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Blade LE tip cracks discovered during inspection in AHPFTP units (511)
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Population of cracked blades relative to geometry (511)
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Tip crack depth versus secondary orientation (β) for AHPFTP first blades (511)
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Variation in pressure and suction side wall thickness unbalance in the AHPFTP first stage blade (511)
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Simple three-dimensional airfoil model of blade geometry (5)
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First-Stage blade finite element model and casting or material coordinate system (6)
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Strain range versus cycles to failure for low cycle fatigue test data (PWA 1480 at 1200°F)
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Shear stress amplitude [Δτmax] versus N
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Low cycle fatigue data for PWA 1493 at room temperature in 5000 psi high-pressure hydrogen: strain amplitude versus cycles to failure
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Shear stress amplitude (Δτmax) versus cycles to failure for PWA 1493 at room temperature in 5000 psi hydrogen power-law curve fit (R2=0.246): Δτ=238,349 N−0.1095
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Low cycle fatigue data for PWA 1493 at 1400°F in 5000 psi high-pressure hydrogen: strain amplitude versus cycles to failure
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Low cycle fatigue data for PWA 1493 at 1600°F in 5000 psi high-pressure hydrogen: strain amplitude versus cycles to failure
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Shear stress amplitude (Δτmax) versus cycles to failure for PWA 1493 at 1400°F in 5000 psi hydrogen power-law curve fit (R2=0.661): Δτ=223,516 N−0.1023
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Shear stress amplitude (Δτmax) versus cycles to failure for PWA 1493 at 1600°F in 5000 psi hydrogen power-law curve fit (R2=0.9365): Δτ=381,241 N−0.2034
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Low cycle fatigue data for SC 7-14-6 at 1800°F in air: strain amplitude versus cycles to failure (14)
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Shear stress amplitude (Δτmax) versus cycles to failure for SC 7-14-6 at 1800°F in air power-law curve fit (R2=0.7931): Δτ=230,275 N−0.1675

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