TECHNICAL PAPERS: Gas Turbines: Structures and Dynamics

Contact Stresses in Dovetail Attachments: Alleviation via Precision Crowning

[+] Author and Article Information
G. B. Sinclair

Department of Mechanical Engineering, Louisiana State University, Baton Rouge, LA 70803-0100  

N. G. Cormier

General Electric Aircraft Engines, Evendale, Cincinnati, OH 45215

J. Eng. Gas Turbines Power 125(4), 1033-1041 (Nov 18, 2003) (9 pages) doi:10.1115/1.1584477 History: Received December 01, 2000; Revised March 01, 2001; Online November 18, 2003
Copyright © 2003 by ASME
Topics: Stress , Blades
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Sinclair, G. B., Cormier, N. G., Griffin, J. H., and Meda, G., 2002, “Contact Stresses in Dovetail Attachments: Finite Element Modeling,” ASME J. Eng. Gas Turbines Power, 124 , pp. 182–189.
Sinclair, G. B., and Cormier, N. G., 2002, “Contact Stresses in Dovetail Attachments: Physical Modeling,” ASME J. Eng. Gas Turbines Power, 124 , pp. 325–331.
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Cormier,  N. G., Smallwood,  B. S., Sinclair,  G. B., and Meda,  G., 1999, “Aggressive Submodelling of Stress Concentrations,” Int. J. Numer. Methods Eng., 46, pp. 889–909.
Poritsky,  H., 1950, “Stresses and Deflections of Cylindrical Bodies in Contact With Application to Contact of Gears and Locomotive Wheels,” ASME J. Appl. Mech., 17, pp. 191–201.
Hertz,  H., 1882, “On the Contact of Elastic Solids,” Journal für die reine und angewandte Mathematik, 92, pp. 156–171 (in German; for an account in English, see Johnson, 10, Chap. 4).
Evans, N. M., 1992, “Attachment of a Gas Turbine Engine Blade to a Turbine Rotor Disc,” Patent No. 5, 110, 262, U.S. Patent Office.
Pape,  J. A., and Neu,  R. W., 1999, “Influence of Contact Configuration in Fretting Fatigue Testing,” Wear, 225–229, pp. 1205–1214.
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Dovetail attachment configuration: (a) section of overall attachment, (b) closeup of disk near lower contact point with stresses acting, (c) in-plane crown on blade flat, (d) out-of-plane section BB
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Free-body diagram of half of the blade section
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Contact stress distributions (μ=0)
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Hoop stress variation near the edge of contact for 20% unloading (μ=0.4)
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Coarse finite element grid for in-plane analysis
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Nominal pressure and stress resultants acting on a segment of the disk above contact flat
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Comparison of normal stress with shear load transfer and simulating body force
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Coarse finite element grids for out-of-plane analysis: (a) without crown, (b) with circular crown
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Out-of-plane contact stress distributions (μ=0)  



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