Additively manufactured Ti-6Al-4V replacement parts for military aircraft

R. Jones, R. K.Singh Raman, A. P. Iliopoulos, J. G. Michopoulos, N. Phan, D. Peng

Research output: Contribution to journalArticleResearchpeer-review

Abstract

This paper is motivated by the need to better understand the potential of Additively Manufactured (AM) Ti6-Al-4V replacement parts for future use on operational aircraft. Unfortunately, the interaction between surface and near surface (sub-surface) breaking material discontinuities, i.e. porosity due to and lack of fusion or keyholing, and the rough surface that is associated with AM parts complicates the analysis needed for certification. The present paper attempts to cut through this “Gordian knot”.1 To this end this paper presents a computational investigation into the fatigue life of AM Ti6-Al-4V parts subjected to two (quite different) representative flight load spectra that does not require the explicit modelling of the surface and subsurface porosity. Given the susceptibility of the “as manufactured” AM Ti6-Al-4V to fatigue crack nucleation and fleet experience from with conventionally manufactured parts, it is assumed that cracks in AM Ti6-Al-4V will initiate and grow from the day that the part enters service. The results of the present analysis suggest that for many parts of F/A-18 Classic Hornet and P3C (Orion) aircraft AM Ti-6Al-4V replacement parts may have an acceptable fatigue life. It also illustrates the potential for using fracture toughness measurements to guide the choice of the AM process and the associated post manufacture treatment.

Original languageEnglish
Pages (from-to)227-235
Number of pages9
JournalInternational Journal of Fatigue
Volume124
DOIs
Publication statusPublished - 1 Jul 2019

Keywords

  • AM Ti-6Al-4V
  • EIFS
  • Fatigue crack growth
  • Replacement parts

Cite this

Jones, R. ; Raman, R. K.Singh ; Iliopoulos, A. P. ; Michopoulos, J. G. ; Phan, N. ; Peng, D. / Additively manufactured Ti-6Al-4V replacement parts for military aircraft. In: International Journal of Fatigue. 2019 ; Vol. 124. pp. 227-235.
@article{702fd33462a0404eb0c9878653e23033,
title = "Additively manufactured Ti-6Al-4V replacement parts for military aircraft",
abstract = "This paper is motivated by the need to better understand the potential of Additively Manufactured (AM) Ti6-Al-4V replacement parts for future use on operational aircraft. Unfortunately, the interaction between surface and near surface (sub-surface) breaking material discontinuities, i.e. porosity due to and lack of fusion or keyholing, and the rough surface that is associated with AM parts complicates the analysis needed for certification. The present paper attempts to cut through this “Gordian knot”.1 To this end this paper presents a computational investigation into the fatigue life of AM Ti6-Al-4V parts subjected to two (quite different) representative flight load spectra that does not require the explicit modelling of the surface and subsurface porosity. Given the susceptibility of the “as manufactured” AM Ti6-Al-4V to fatigue crack nucleation and fleet experience from with conventionally manufactured parts, it is assumed that cracks in AM Ti6-Al-4V will initiate and grow from the day that the part enters service. The results of the present analysis suggest that for many parts of F/A-18 Classic Hornet and P3C (Orion) aircraft AM Ti-6Al-4V replacement parts may have an acceptable fatigue life. It also illustrates the potential for using fracture toughness measurements to guide the choice of the AM process and the associated post manufacture treatment.",
keywords = "AM Ti-6Al-4V, EIFS, Fatigue crack growth, Replacement parts",
author = "R. Jones and Raman, {R. K.Singh} and Iliopoulos, {A. P.} and Michopoulos, {J. G.} and N. Phan and D. Peng",
year = "2019",
month = "7",
day = "1",
doi = "10.1016/j.ijfatigue.2019.02.041",
language = "English",
volume = "124",
pages = "227--235",
journal = "International Journal of Fatigue",
issn = "0142-1123",
publisher = "Elsevier",

}

Additively manufactured Ti-6Al-4V replacement parts for military aircraft. / Jones, R.; Raman, R. K.Singh; Iliopoulos, A. P.; Michopoulos, J. G.; Phan, N.; Peng, D.

In: International Journal of Fatigue, Vol. 124, 01.07.2019, p. 227-235.

Research output: Contribution to journalArticleResearchpeer-review

TY - JOUR

T1 - Additively manufactured Ti-6Al-4V replacement parts for military aircraft

AU - Jones, R.

AU - Raman, R. K.Singh

AU - Iliopoulos, A. P.

AU - Michopoulos, J. G.

AU - Phan, N.

AU - Peng, D.

PY - 2019/7/1

Y1 - 2019/7/1

N2 - This paper is motivated by the need to better understand the potential of Additively Manufactured (AM) Ti6-Al-4V replacement parts for future use on operational aircraft. Unfortunately, the interaction between surface and near surface (sub-surface) breaking material discontinuities, i.e. porosity due to and lack of fusion or keyholing, and the rough surface that is associated with AM parts complicates the analysis needed for certification. The present paper attempts to cut through this “Gordian knot”.1 To this end this paper presents a computational investigation into the fatigue life of AM Ti6-Al-4V parts subjected to two (quite different) representative flight load spectra that does not require the explicit modelling of the surface and subsurface porosity. Given the susceptibility of the “as manufactured” AM Ti6-Al-4V to fatigue crack nucleation and fleet experience from with conventionally manufactured parts, it is assumed that cracks in AM Ti6-Al-4V will initiate and grow from the day that the part enters service. The results of the present analysis suggest that for many parts of F/A-18 Classic Hornet and P3C (Orion) aircraft AM Ti-6Al-4V replacement parts may have an acceptable fatigue life. It also illustrates the potential for using fracture toughness measurements to guide the choice of the AM process and the associated post manufacture treatment.

AB - This paper is motivated by the need to better understand the potential of Additively Manufactured (AM) Ti6-Al-4V replacement parts for future use on operational aircraft. Unfortunately, the interaction between surface and near surface (sub-surface) breaking material discontinuities, i.e. porosity due to and lack of fusion or keyholing, and the rough surface that is associated with AM parts complicates the analysis needed for certification. The present paper attempts to cut through this “Gordian knot”.1 To this end this paper presents a computational investigation into the fatigue life of AM Ti6-Al-4V parts subjected to two (quite different) representative flight load spectra that does not require the explicit modelling of the surface and subsurface porosity. Given the susceptibility of the “as manufactured” AM Ti6-Al-4V to fatigue crack nucleation and fleet experience from with conventionally manufactured parts, it is assumed that cracks in AM Ti6-Al-4V will initiate and grow from the day that the part enters service. The results of the present analysis suggest that for many parts of F/A-18 Classic Hornet and P3C (Orion) aircraft AM Ti-6Al-4V replacement parts may have an acceptable fatigue life. It also illustrates the potential for using fracture toughness measurements to guide the choice of the AM process and the associated post manufacture treatment.

KW - AM Ti-6Al-4V

KW - EIFS

KW - Fatigue crack growth

KW - Replacement parts

UR - http://www.scopus.com/inward/record.url?scp=85062682547&partnerID=8YFLogxK

U2 - 10.1016/j.ijfatigue.2019.02.041

DO - 10.1016/j.ijfatigue.2019.02.041

M3 - Article

VL - 124

SP - 227

EP - 235

JO - International Journal of Fatigue

JF - International Journal of Fatigue

SN - 0142-1123

ER -