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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Out-of-plane contact stress distributions (μ=0)  
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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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