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Advances in Acoustics and Vibration
Volume 2012 (2012), Article ID 316761, 13 pages
Research Article

Gas Turbine Blade Damper Optimization Methodology

1Vibration Engineering Group, Gas Turbine Research Establishment, CV Raman Nagar, Bangalore 560093, India
2Mechanical Engineering Department, Sri Venkateswara University, Tirupati 517502, India

Received 11 May 2011; Revised 2 January 2012; Accepted 10 January 2012

Academic Editor: Benjamin Soenarko

Copyright © 2012 R. K. Giridhar et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


The friction damping concept is widely used to reduce resonance stresses in gas turbines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. This paper presents a methodology that combines three essential phases of friction damping optimization in turbo-machinery. The first phase is to develop an analytical model of blade damper system. The second phase is experimentation and model tuning necessary for response studies while the third phase is evaluating damper performance. The reduced model of blade is developed corresponding to the mode under investigation incorporating the friction damper then the simulations were carried out to arrive at an optimum design point of the damper. Bench tests were carried out in two phases. Phase-1 deals with characterization of the blade dynamically and the phase-2 deals with finding optimal normal load at which the blade resonating response is minimal for a given excitation. The test results are discussed, and are corroborated with simulated results, are in good agreement.