Modeling, Fatigue Crack Growth Assessment and Modal Analysis for a Gas Turbine Compressor Blade

Document Type : Solid Mechanics

Authors

1 Department of Mechanical Engineering, Parand Branch, Islamic Azad University, Parand, Iran

2 Corresponding author: Associate Professor, Department of Mechanical Engineering, Parand Branch, Islamic Azad University, Parand, Iran

Abstract

In this study, the fracture mechanics analysis for the 16th stage of a Siemens V94.2 gas turbine compressor blade under mechanical and thermal stresses due to rotation, pressure and temperature distributions in the full load steady state condition is studied using ANSYS finite element software. Modeling a symmetric sector of a balde-disk assembly with a ratio of 1 to 79 with applying thermomechanical loading, boundary conditions and initial conditions, locations with high stress levels on the blade airfoil are recognized. Then, using ANSYS software to model cracks with different sizes in two specified locations on the airfoil, the stress intensity factors are calculated. Moreover, by applying Paris relation, crack growth rate with respect to the stress intensity factors are obtained to estimate remaining life in the fatigue crack growth for the cracks with initial dimensions in these two locations. Finally, doing modal analysis, the operating frequencies of the blade have been calculated and according to obtained Campbell diagram, the interacting frequencies for the blade are also specified. The obtained results show that for these two cracks locations on the pressure side of the blade airfoil, by increasing the distance from the root of the compressor blade, the remaining life of the cracked compressor blade increases, accordingly.

Keywords

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References

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Aerospace Mechanics
Volume 18, Issue 1 - Serial Number 67
Serial No. 67, Spring Quarterly
July 2022
Pages 1-19

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History

  • Receive Date: 30 March 2020
  • Revise Date: 01 August 2020
  • Accept Date: 03 October 2021
  • Publish Date: 21 April 2022

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