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Journal of Engineering for Gas Turbines and Power | Volume 133 | Issue 12 | Research Paper
Research Papers: Gas Turbines: Structures and Dynamics

Dynamic Loading on Turbofan Blades Due to Bird-Strike

[+] Author and Article Information
Sunil K. Sinha

Kevin E. Turner

 GE Aviation, M.D.: G-36, General Electric, 1 Neumann Way, Cincinnati, OH 45215Kevin.Turner1@.ge.com

Nitesh Jain

 Bangalore Engineering Center, JFWTC, Whitefield Road, Bangalore-560066, Karnataka, IndiaNitesh.Jain@ge.com

J. Eng. Gas Turbines Power 133(12), 122504 (Sep 01, 2011) (13 pages) doi:10.1115/1.4004126 History: Received April 09, 2011; Revised April 11, 2011; Published September 01, 2011; Online September 01, 2011
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In the present paper, a hydrodynamic bird material model made up of water and air mixture is developed, which produces good correlation with the measured strain-gauge test data in a panel test. This parametric bird projectile model is used to generate the time-history of the transient dynamic loads on the turbofan engine blades for different size birds impacting at varying span locations of the fan blade. The problem is formulated in 3D vector dynamics equations using a nonlinear trajectory analysis approach. The analytical derivation captures the physics of the slicing process by considering the incoming bird in the shape of a cylindrical impactor as it comes into contact with the rotating fan blades modeled as a pretwisted plate with a camber. The contact-impact dynamic loading on the airfoil produced during the bird-strike is determined by solving the coupled nonlinear dynamical equations governing the movement of the bird-slice in time-domain using a sixth-order Runge-Kutta technique. The analytically predicted family of load time-history curves enables the blade designer to readily identify the critical impact location for peak dynamic loading condition during the bird-ingestion tests mandated for certification by the regulatory agencies.
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Copyright © 2011 by American Society of Mechanical Engineers
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Figures

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+A typical plastically deformed bulge in the leading edge of a metal turbofan blade after slicing action during bird-strike
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A typical plastically deformed bulge in the leading edge of a metal turbofan blade after slicing action during bird-strike
Figure 1

A typical plastically deformed bulge in the leading edge of a metal turbofan blade after slicing action during bird-strike

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+Bird cylinder coming in contact with rotating turbofan blades and local coordinate system
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Bird cylinder coming in contact with rotating turbofan blades and local coordinate system
Figure 2

Bird cylinder coming in contact with rotating turbofan blades and local coordinate system

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+Effect of relative velocity vector during slicing action of the fan blade
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Effect of relative velocity vector during slicing action of the fan blade
Figure 3

Effect of relative velocity vector during slicing action of the fan blade

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+A pretwisted and curved airfoil surface as viewed from the blade tip-side
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A pretwisted and curved airfoil surface as viewed from the blade tip-side
Figure 4

A pretwisted and curved airfoil surface as viewed from the blade tip-side

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+Analytically computed bird-slice trajectory on the concave surface of an airfoil blade for a typical 75% span-shot
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Analytically computed bird-slice trajectory on the concave surface of an airfoil blade for a typical 75% span-shot
Figure 5

Analytically computed bird-slice trajectory on the concave surface of an airfoil blade for a typical 75% span-shot

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+(a) 25% span impact, (b) 50% span impact, (c) 75% span impact. Time-history of contact-impact loads (F(t)Bird-slice ) on a typical fan blade (L/C = 2), by different size birds at the leading edge span locations (a) 25%, (b) 50%, (c) 75%.
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(a) 25% span impact, (b) 50% span impact, (c) 75% span impact. Time-history of contact-impact loads (F(t)Bird-slice ) on a typical fan blade (L/C = 2), by different size birds at the leading edge span locations (a) 25%, (b) 50%, (c) 75%.
Figure 6

(a) 25% span impact, (b) 50% span impact, (c) 75% span impact. Time-history of contact-impact loads (F(t)Bird-slice ) on a typical fan blade (L/C = 2), by different size birds at the leading edge span locations (a) 25%, (b) 50%, (c) 75%.

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+Time-history of contact-impact loads (FBird-slice) on a typical fan blade (L/C =2), by different size birds at the critical impact location of 43% of span
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Time-history of contact-impact loads (FBird-slice) on a typical fan blade (L/C =2), by different size birds at the critical impact location of 43% of span
Figure 7

Time-history of contact-impact loads (FBird-slice) on a typical fan blade (L/C =2), by different size birds at the critical impact location of 43% of span

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+(a) Rectangular composite panel with strain gauges (SG3 and SG 8) being impacted by a bird-cylinder moving at 92.66 m/s. (b) LS-DYNA results showing the deformation of a bird cylinder during the bird-strike after 0.4 ms of initial contact.
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(a) Rectangular composite panel with strain gauges (SG3 and SG 8) being impacted by a bird-cylinder moving at 92.66 m/s. (b) LS-DYNA results showing the deformation of a bird cylinder during the bird-strike after 0.4 ms of initial contact.
Figure 8

(a) Rectangular composite panel with strain gauges (SG3 and SG 8) being impacted by a bird-cylinder moving at 92.66 m/s. (b) LS-DYNA results showing the deformation of a bird cylinder during the bird-strike after 0.4 ms of initial contact.

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+Comparison of strain gauge dynamic response from LS-DYNA vs test data (lengthwise strain gauge – SG3)
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Comparison of strain gauge dynamic response from LS-DYNA vs test data (lengthwise strain gauge – SG3)
Figure 9

Comparison of strain gauge dynamic response from LS-DYNA vs test data (lengthwise strain gauge – SG3)

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+Comparison of strain gauge dynamic response from LS-DYNA vs test data (widthwise strain gauge - SG8)
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Comparison of strain gauge dynamic response from LS-DYNA vs test data (widthwise strain gauge - SG8)
Figure 10

Comparison of strain gauge dynamic response from LS-DYNA vs test data (widthwise strain gauge - SG8)

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+LS-DYNA simulation of a 2 kg bird-strike on a 3-bladed sector of a typical turbofan rotor
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LS-DYNA simulation of a 2 kg bird-strike on a 3-bladed sector of a typical turbofan rotor
Figure 11

LS-DYNA simulation of a 2 kg bird-strike on a 3-bladed sector of a typical turbofan rotor

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+Time-history of the bird-slice load in the tangential direction of the fan-rotor on a 20 bladed rotor due to 2 kg bird at 100 m/s
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Time-history of the bird-slice load in the tangential direction of the fan-rotor on a 20 bladed rotor due to 2 kg bird at 100 m/s
Figure 12

Time-history of the bird-slice load in the tangential direction of the fan-rotor on a 20 bladed rotor due to 2 kg bird at 100 m/s

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