114. Parametric study to mitigate fretting fatigue in dovetail joint of aeroengine compressor

Sunita Kumari1, Srihari P V2, Bharatish A3, Narasimha Murthy H N4

R V College of Engineering, Bangalore, India

3Corresponding author

E-mail: 1sunitashri45@gmail.com, 2pvsrihari@gmail.com, 3bharatisha@rvce.edu.in, 4narasimhamurthyhn@rvce.edu.in

Received 22 February 2017; accepted 27 February 2017

DOI https://doi.org/10.21595/jme.2017.18270


Abstract. Fretting fatigue is most likely to occur in the dovetail joint of aero engine compressor resulting in small amplitude displacement of a few micrometers. This leads to degradation of the material in the form of fatigue strength and corrosion. This paper reports optimal conditions of blade geometrical parameters such as flank length, flank angle and coefficient of friction in order minimize the failure due to fretting fatigue. ANOVA indicated that Von-mises stresses, deformation, contact pressure and sliding distance were influenced by coefficient of friction and flank angle. While deformation, contact pressure and sliding distance decreased with increase in coefficient of friction and increased with increase in flank angle and flank length. Von-mises stress increased with increase in coefficient of friction. Response surface methodology results indicated that the optimum value of Von-mises stress (328.24 MPa), deformation (153.87 m), contact pressure (275.48 MPa) and sliding distance (80.66 m) were found at coefficient of friction 0.35, flank angle 65 and flank length of 12 mm which were in agreement with those of grey relational analysis results.

Keywords: dovetail, fretting fatigue, response surface methodology.


[1]        Papanikos P., Meguid S. A., Stjepanovic Z. Three dimensional nonlinear finite element analysis of dovetail joint in Aeroengine discs. Finite Element in Analysis and Design, Vol. 29, 1998, p. 173‑186.

[2]        Nandish R. V., Paul Vizhian S., Gopinath M., Rajeev Jain Elastic contact stress analysis of dovetail attachment in turbine engines. International Journal of Research in Mechanical Engineering and Technology, Vol. 3, 2013, p. 166‑170.

[3]        Hammouda M. M. I., Fayed A. S. Finite element simulation of the mechanics of flat contact pad fretting fatigue tests. Fatigue & Fracture of Engineering Materials & Structures, Vol. 26, 2003, p. 1‑13.

[4]        Eden E. M., Rose W. N. The endurance of metals. Proceeding of the Institute for Mechanical Engineers, Vol. 81, Issue 1, 1911, p. 839-974.

[5]        Tiago de oliveira Vale, Gustavo da Costa villar, Joao Carlos Menezes Methodology for structural integrity analysis of gas turbine blade. Journal of Aerospace Technology and Management, Vol. 4, 2012, p. 55‑59.

[6]        Malay Kumar Kheto, Mahendra Babu N. C., Madan J. Fretting fatigue analysis in dovetail joint of compressor though numerical simulation. SASTech Journal, Vol. 8, 2009, p. 71‑76.

[7]        Witek L. Numerical simulation of fatigue fracture of the turbine disc. Fatigue of Aircraft Structure, Vol. 2012, 2012, p. 114‑122.

[8]        Anandavel K., Prakash R. V. Effect of three-dimensional loading on macroscopic fretting aspects of an aero-engine blade-disc dovetail interface. Tribology International, Vol. 44, 1544, p. 1555‑2011.

[9]        Hammouda M. M. I., Fayed A. S. Numerical Approach to the Mechanics of Disc-Blade Dovetail Joints in Aero-Engine Compressors. Materials Engineering Department, Zagazig University, Egypt, 2005, p. 20-25.

[10]     Jabbar A. A., Rai A. K., Reedy P. R., Dakhil M. H. Design and analysis of gas turbine rotor blade using finite element method. International Journal of Mechanical and Production Engineering Research and Development, Vol. 4, p. 73-94, 2014.

[11]     Kotresh M., Srihari P. V., Ramachandra K. Fretting fatigue studies of aero engine dovetail roots using contact analysis. International Conference on Computer Aided Engineering CAE, IIT Madras India, 2013, p. 93-98.

[12]     ANSYS R14.5. Academic, Structural analysis Guide manual, 2014.

Cite this article

Kumari Sunita, P V Srihari, A Bharatish, H N Narasimha Murthy Parametric study to mitigate fretting fatigue in dovetail joint of aeroengine compressor. Journal of Measurements in Engineering, Vol. 5, Issue 1, 2017, p. 19‑28.


Journal of Measurements in Engineering. March 2017, Volume 5, Issue 1

JVE International Ltd. ISSN Print 2335-2124, ISSN Online 2424-4635, Kaunas, Lithuania