Research Papers

Airfoil Deflection Characteristics During Rub Events

[+] Author and Article Information
Kevin E. Turner1

 GE Aviation, 1 Neumann Way, Cincinnati, OH 45215kevin.turner1@ge.com

Michael Dunn, Corso Padova

Department of Mechanical Engineering, The Ohio State University, Gas Turbine Laboratory, 2300 West Case Rd., Columbus, OH, 43235

ANSYS® is a registered trademark of SAS IP, Inc., Canonsburg, PA.

LS-DYNA® is a registered trademark of Livermore Software Technology, Corp., Livermore, CA.


Corresponding author.

J. Turbomach 134(1), 011018 (May 31, 2011) (8 pages) doi:10.1115/1.4003257 History: Received October 10, 2010; Revised November 09, 2010; Published May 31, 2011; Online May 31, 2011

The turbomachinery industry continually struggles with the adverse effects of contact rubs between airfoils and casings. The key parameter controlling the severity of a given rub event is the contact load produced when the airfoil tips incur into the casing. These highly nonlinear and transient forces are difficult to calculate and their effects on the static and rotating components are not well understood. To help provide this insight, experimental and analytical capabilities have been established and exercised through an alliance between GE Aviation and The Ohio State University Gas Turbine Laboratory. One of the early findings of the program is the influence of blade flexibility on the physics of rub events. The focus of this paper is to quantify the influence of airfoil flexibility through a novel modeling approach that is based on the relationship between the applied force duration and maximum tip deflection. Results from the model are compared with experimental results, providing sound verification.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 13

Comparison of predicted F̃θ to measured

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Figure 1

Schematic of tip loading: (a) rotor view and (b) blade alone view

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Figure 2

Pulse width definition

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Figure 3

Series of tip deflection curves

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Figure 4

Build up of pulse deflection curve

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Figure 5

κθ versus τ for a small flat plate

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Figure 6

κ curves for a small flat plate under various loadings

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Figure 7

Comparison of κ for a small and large flat plate

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Figure 8

Effect of rotor speed

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Figure 9

Effect of rotor spin on κr for a small flat plate

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Figure 10

Comparison of κ for simulated HPC airfoil and small flat plate under rotation

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Figure 12

Pulse width for CSPF experiments



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