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Flutter and Forced Vibration Characteristics of a Turbo Fan Bladed Disk Rotor

[+] Author Affiliations
Madhavan Srinivasan, Sankarkumar Jeyaraman, Rajeev Jain

Gas Turbine Research Establishment, Bangalore, KA, India

Sujatha Chandramohan, Sekhar AnandaRao Seshadri

Indian Institute of Technology - Madras, Chennai, TN, India

Paper No. GTINDIA2013-3574, pp. V001T06A005; 7 pages
doi:10.1115/GTINDIA2013-3574
From:
  • ASME 2013 Gas Turbine India Conference
  • ASME 2013 Gas Turbine India Conference
  • Bangalore, Karnataka, India, December 5–6, 2013
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-3516-1
  • Copyright © 2013 by ASME

abstract

Aero-elastic excitation can result in excessive blade vibration, which can cause blades to fail in high cycle fatigue (HCF). A severe aero-elastic failure can result in a complete blade separation and loss of thrust and loss of a blade can mean the loss of an aircraft. The primary aeromechanical design concerns are blade flutter and forced vibration that need to be quantified at the early part of engine tests. This paper details the experimental investigation carried out on a transonic shroudless low aspect ratio fan bladed disk that experienced subsonic/transonic stall flutter and forced vibration excitation. Experiments are performed on a full scale engine using tip timing sensors flush mounted on the fan casing to characterize the vibratory responses during flutter and forced vibration conditions during engine operation. Numerical simulations are performed using computational fluid dynamic (CFD) analysis. Blade natural frequencies and mode shapes are obtained from finite element (FE) modal analysis. The experimental data captured from engine tests are used to validate the predicted results.

Copyright © 2013 by ASME

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