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

Failure Analysis of Inlet Guide Vanes

[+] Author and Article Information
R. L. McAlpin, P. L. Talley, H. L. Bernstein

Gas Turbine Materials Associates, San Antonio, TX 78279e-mail: gtma@texas.net

R. E. Holm

Occidental Chemical Corporation, Houston, TX 77227-7702e-mail: Robert_e._holm@oxy.com

J. Eng. Gas Turbines Power 125(1), 236-240 (Dec 27, 2002) (5 pages) doi:10.1115/1.1494095 History: Received December 01, 2000; Revised March 01, 2001; Online December 27, 2002
Copyright © 2003 by ASME
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Haskell, R. W., “Gas Turbine Compressor Operating Environment and Material Evaluation,” GE Reference No. GER-3601, GE Company, Schenectady, New York.
Henthorne, M., T. Debold, and R. Yinger, 1972, “Custom 450, A New High-Strength Steel,” Corrosion/72, NACE.
Kolkman, H. J., and Mom, A. J. A., 1984, “Corrosion and Corrosion Control in Gas Turbines Part I: The Compressor Section,” ASME Paper No. 84-GT-255.


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Diagram of variable inlet guide vane (IGV), viewed from suction side
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Failed IGV. The inner end segment includes the bushing in place on the button. Arrows located at the crack initiation point.
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Plan view of opened crack segment. Arrows locate two origins at the bottom corners on opposite sides of the airfoil. (Scale divisions=0.01 in.)
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Large corrosion pit (arrow) at IGV crack origin
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Button surface conditions on suctions side (a) and pressure side (b) surfaces. (Scale divisions=0.1 in.)
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Microstructure of galling layer (between arrows) on button contact surface (original 1000X—Vilella’s reagent)
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Adhesive wear features (arrow) on button contact surface (original 1000X—Vilella’s reagent)
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Metallic wear particles (bright) on bushing contact surface (original 20X)
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Results of the simplified stress analysis showing the equivalent, or Von Mises, stress contours. Maximum stress occurs at the crack origin.



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