Failure analysis of J85-CAN-15 turbojet engine compressor disc

Saraçyakupoğlu T.

Engineering Failure Analysis, vol.119, 2021 (SCI-Expanded, Scopus) identifier

  • Publication Type: Article / Article
  • Volume: 119
  • Publication Date: 2021
  • Doi Number: 10.1016/j.engfailanal.2020.104975
  • Journal Name: Engineering Failure Analysis
  • Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Academic Search Premier, Aerospace Database, Communication Abstracts, Compendex, INSPEC, Metadex, DIALNET, Civil Engineering Abstracts
  • Keywords: Crack, Dovetail post, Fatigue failure, J85-CAN-15, Manufacturing defect
  • Istanbul Gelisim University Affiliated: Yes

Abstract

© 2020 Elsevier LtdThis paper analyzes the J85-CAN-15 engine damage due to fracture of the compressor disc 8th stage dovetail post. An Inner Object Damage (IOD) phenomenon was identified. The damaged compressor disc material is Incoloy 901 forging. The composition of the disc is determined as 42.7%-Ni, 34%-Fe, 13.5%-Cr, 6.2% Mo, 2.5%Ti, 0.1%-Cu, and 0.05%-C. The average hardness value of the material is 44 HRC. The burrs have been observed under Field Emission Scanning Electron Microscope (SEM) and they are considered as the origin of the fatigue on the engine compressor disc. The metallurgical analysis results show that manufacturing defect was propagated under the repeated low and high cyclic loads.