Research Papers

Combined Airfoil and Snubber Design Optimization of Turbine Blades With Respect to Friction Damping

[+] Author and Article Information
Matthias Hüls

Siemens AG,
Mellinghofer Straße 55,
Mülheim a. d. Ruhr 45473, Germany
e-mail: matthias.huels@siemens.com

Lars Panning-von Scheidt

Institute of Dynamics and Vibration Research,
Leibniz University Hannover,
Hannover 30167, Germany
e-mail: panning@ids.uni-hannover.de

Jörg Wallaschek

Institute of Dynamics and Vibration Research,
Leibniz University Hannover,
Hannover 30167, Germany
e-mail: wallaschek@ids.uni-hannover.de

1Corresponding author.

Manuscript received March 1, 2018; final manuscript received June 25, 2018; published online July 26, 2018. Assoc. Editor: Rakesh Srivastava.

J. Turbomach 140(8), 081007 (Jul 26, 2018) (11 pages) Paper No: TURBO-18-1048; doi: 10.1115/1.4040679 History: Received March 01, 2018; Revised June 25, 2018

A major concern for new generations of large turbine blades is forced and self-excited (flutter) vibrations, which can cause high-cycle fatigue (HCF). The design of friction joints is a commonly applied strategy for systematic reduction of resonance amplitudes at critical operational conditions. In this paper, the influence of geometric blade design parameters onto the damped system response is investigated for direct snubber coupling. A simplified turbine blade geometry is parametrized and a well-proven reduced-order model for turbine blade dynamics under friction damping is integrated into a 3D finite element tool-chain. The developed process is then used in combination with surrogate modeling to predict the effect of geometric design parameters onto the vibrational characteristics. As such, main and interaction effects of design variables onto static normal contact force and resonance amplitudes are determined for a critical first bending mode. Parameters were found to influence the static normal contact force based on their effect on elasticity of the snubber, torsional stiffness of the airfoil and free blade untwist. The results lead to the conclusion that geometric design parameters mainly affect the resonance amplitude equivalent to their influence on static normal contact force in the friction joint. However, it is demonstrated that geometric airfoil parameters influence blade stiffness and are significantly changing the respective mode shapes, which can lead to lower resonance amplitudes despite an increase in static contact loads. Finally, an evolutionary optimization is carried out and novel design guidelines for snubbered blades with friction damping are formulated.

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Fig. 1

Blade and snubber design parameter

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Fig. 2

Airfoil section design parameter

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Fig. 3

Effect of normalized airfoil parameters on hub (0) and tip (1) section

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Fig. 4

Contact interface geometry and discretization

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Fig. 5

Snubber blade twist-back geometry

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Fig. 6

Estimated closing speed nc as a function of standstill tangential snubber gap g0

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Fig. 7

Exemplary damping performance curve (resonance amplitude U as function of stimulus s) for first bending type vibrational motion

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Fig. 8

Meshed geometry of baseline design with monitor node

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Fig. 10

Relation between snubber normal contact force F0 and resonance amplitude at nominal stimulus U(s = snom) and frequency f1 for first bending type vibrational motion

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Fig. 11

Main effects of design parameter onto static normal snubber contact force F0 and resonance amplitude of first bending type vibrational motion at nominal stimulus U(s = snom)

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Fig. 12

Main effects of design parameter onto torsional stiffness Kt and free untwist δθ at full speed

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Fig. 13

(a) Resonance amplitude as function of stimulus, (b) equivalent logarithmic decrement damping, and (c) magnitude of generalized coordinates (participation of uncoupled modes) for modes one to four along with the ratio of dissipated energy in the friction joint Wfrict relative to the total dissipated energy including viscous damping Wvisc. Results shown for different snubber cross-sectional shapes and radial positions rn,s.

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Fig. 14

Uncoupled modeshapes of 1F, 2F, 1T, and 2T modes

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Fig. 15

Scatter plot of (a) resonance amplitude at maximum stimulus versus resonance amplitude at nominal stimulus with vertical snubber length. (b) resonance amplitude at nominal stimulus versus static normal contact force with radial snubber position. (c) required standstill snubber gap versus static normal contact force with radial snubber position.

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Fig. 16

Baseline and optimized design parameter with respect to baseline (0), minimum (–1), and maximum (1) values

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Fig. 17

Baseline and optimum blade geometry

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Fig. 18

Damping performance curves for baseline and optimized design parameters



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