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Crack Propagation Life Calculation of an Aircraft Compressor Blade due to Bird Ingestion

[+] Author Affiliations
Srinivasa R. Jammi

Kumaraguru College of Technology, Coimbatore, India

R. Rzadkowski

The Szewalski Institute of Fluid Flow Machinery, Gdansk, Poland

Paper No. GT2014-25010, pp. V07AT29A001; 8 pages
doi:10.1115/GT2014-25010
From:
  • ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
  • Volume 7A: Structures and Dynamics
  • Düsseldorf, Germany, June 16–20, 2014
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4576-9
  • Copyright © 2014 by ASME

abstract

Bird ingestion is simulated by blade passage blocks in the incoming flow and the pressure field is obtained from a CFD code. The alternating pressure field corresponding to the identified critical speed of the first stage rotor blade is obtained from an FFT. A nonlinear damping model is developed using Lazan’s hysteresis law; the equivalent viscous damping model is determined as a function of reference strain amplitude in the given mode of vibration at the rotational speed. An iterative process is developed with the nonlinear damping model and the resonant stress and location is determined. The Fracture Mechanics approach is used to estimate the crack propagation life of the blade.

Copyright © 2014 by ASME

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