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The Numerical Technique for Turbine Blades and Underplatform Dampers Interaction Modeling Based on Substructure Method

[+] Author Affiliations
Irina Semenova

Technical University of Ostrava, Ostrava, Czech Republic

Nikolai Sazhenkov, Mikhail Nikhamkin, Sergey Semenov

Perm National Research Polytechnic University, Perm, Russia

Paper No. IMECE2016-67068, pp. V009T12A018; 8 pages
  • ASME 2016 International Mechanical Engineering Congress and Exposition
  • Volume 9: Mechanics of Solids, Structures and Fluids; NDE, Diagnosis, and Prognosis
  • Phoenix, Arizona, USA, November 11–17, 2016
  • Conference Sponsors: ASME
  • ISBN: 978-0-7918-5063-3
  • Copyright © 2016 by ASME


Friction dampers are commonly used in jet and turboprop engines to decrease vibration stresses of turbine blades by irreversible conversion of mechanical energy into heat. Effectiveness of the energy transfer depends on dampers design, material and operational conditions. Optimization of dampers design is a complex task usually associated with nonlinear contact problems analysis and complicated experimental verification. It also coupled with high time costs causing the engineering task to be modified into compound research problem. The paper presents time effective numerical technique for gas turbine blades underplatform dry-friction dampers efficiency study. The presented technique is based on finite-element method with a numerical model reduction by Craig-Bampton and Guyan algorithms. The model consisted of dummy blades pair with wedge damper between the platforms. Technique allows considering three dimensional shapes of parts, nonlinear contact forces, friction, various operational loads and conditions. The model was verified by experiment completed on special test rig based on vibration shaker and 3D laser vibrometer. Relationship between the blades oscillation amplitude and the centrifugal load on the damper was obtained. Optimal operational range with maximum damper efficiency was defined. Impact of so called anti-phase and in-phase modes of adjacent blades on damper efficiency was investigated.

Copyright © 2016 by ASME



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