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TECHNICAL PAPERS: Gas Turbines: Manufacturing, Materials, and Metallurgy

Effect of Crystal Orientation on Fatigue Failure of Single Crystal Nickel Base Turbine Blade Superalloys

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

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

G. Swanson

NASA Marshall Space Flight Center, ED22/Strength Analysis Group, MSFC, AL 35812

J. Eng. Gas Turbines Power 124(1), 161-176 (Feb 01, 2000) (16 pages) doi:10.1115/1.1413767 History: Received November 01, 1999; Revised February 01, 2000
Copyright © 2002 by ASME
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References

Cowles,  B. A., 1996, “High Cycle Fatigue Failure in Aircraft Gas Turbines: An Industry Perspective,” Int. J. Fract., 80, pp. 147–163.
Moroso, J., 1999, “Effect of Secondary Crystal Orientation on Fatigue Crack Growth in Single Crystal Nickel Turbine Blade Superalloys,” M. S. thesis, Mechanical Engineering Department, University of Florida, Gainesville, FL, May.
Deluca, D., and Annis, C., 1995, “Fatigue in Single Crystal Nickel Superalloys,” Office of Naval Research, Department of the Navy FR23800, Aug.
Stouffer, D. C., and Dame, L. T., 1996, Inelastic Deformation of Metals, John Wiley and Sons, New York.
Milligan, W. W., and Antolovich, S. D., 1985, “Deformation Modeling and Constitutive Modeling for Anisotropic Superalloys,” NASA Contractor Report 4215, Feb.
Telesman,  J., and Ghosn,  L., 1989, “The Unusual Near Threshold FCG Behavior of a Single Crystal Superalloy and the Resolved Shear Stress as the Crack Driving Force,” Eng. Fract. Mech., 34, No. 5–6, pp. 1183–1196.
Deluca, D. P., and Cowles, B. A., 1989, “Fatigue and Fracture of Single Crystal Nickel in High Pressure Hydrogen,” Hydrogen Effects on Material Behavior, By N. R. Moody and A. W. Thomson, eds., TMS., Warrendale, PA.
Kandil, F. A., Brown, M. W., and Miller, K. J., 1982, Biaxial Low Cycle Fatigue of 316 Stainless Steel at Elevated Temperatures, Metals Soc., London. pp. 203–210.
Socie, D. F., Kurath, P., and Koch, J., 1985, “A Multiaxial Fatigue Damage Parameter,” presented at the Second International Symposium on Multiaxial Fatigue, Sheffield, U.K.
Fatemi,  A., and Socie,  D., 1998, “A Critical Plane Approach to Multiaxial Fatigue Damage Including Out-of-Phase Loading,” Fatigue Fracture in Engineering Materials, 11, No. 3, pp. 149–165.
Smith,  K. N., Watson,  P., and Topper,  T. M., 1970, “A Stress-Strain Function for the Fatigue of Metals,” J. Mater., 5, No. 4 pp 767–778.
Banantine, J. A., and Socie, D. F., 1985, “Observations of Cracking Behavior in Tension and Torsion Low Cycle Fatigue,” presented at ASTM Symposium on Low Cycle Fatigue—Directions for the Future, Philadelphia, PA.
Lekhnitskii, S. G., 1963, “Theory of Elasticity of an Anisotropic Elastic Body,” Holden-Day, San Francisco, pp. 1–40.
Pratt and Whitney, 1996, “SSME Alternate Turbopump Development Program HPFTP Critical Design Review.” P&W FR24581-1 Dec. 23, NASA Contract NAS8-36801.
Sayyah, T., 1999, “Alternate Turbopump Development Single Crystal Failure Criterion for High Pressure Fuel Turbopump First Stage Blades,” Report No.: 621-025-99-001, NASA Contract NAS 8-40836, May 27.

Figures

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Convention for defining crystal orientation in turbine blades (2)
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Primary (close-packed) and secondary (non-close-packed) slip directions on the octahedral planes for a FCC crystal (4)
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Cube slip planes and slip directions for a FCC crystal (4)
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Material (x,y,z) and specimen (x,y,z) coordinate systems
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Strain range versus cycles to failure for LCF test data (PWA 1493 at 1200°F)
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maxn] (Eq. (1)) versus N
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[Δγ/2+Δεn/2+σno/E] (Eq. (2)) versus N
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[Δγ/2(1+k(σnmaxy))] (Eq. (3)) versus N
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[Δε1/2(σmax)] (Eq. (4)) versus N
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Shear stress amplitude [Δτmax] versus N
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[Δτmax (Δγmax/2)] versus N
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max (Δγmax/2)] versus N
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Secondary crystallographic orientation, β, versus crack depth for the SSME AHPFTP first stage turbine blade (2)
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Three-dimensional ANSYS model of HPFTP/AT rotating turbine components
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First-stage bla1de finite element model and casting coordinate system
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33 primary axis cases (Γ and Δ variations shown in Table 5) with nine secondary axis cases (β or θ values) each, for a total of 297 material orientations
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Representative von Mises stress distribution results in the blade attachment region
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Maximum shear stress amplitude (Δτmax,ksi) contour plot at the blade-tip critical point
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Normalized HCF life (contour plot) at the blade-tip critical point, as a function of primary and secondary orientation

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