Transient thermal cycle damage of thermal barrier type of functionally gradient material

Yuji Matsuzaki, Junzo Fujioka, Takao Yoshikawa

Research output: Contribution to journalArticle

2 Citations (Scopus)

Abstract

Functionally Gradient Materials (FGM) promise to be used for advanced thermal barrier coatings in gas turbine engines and for heat insulation systems in structural components in hypersonic aircraft. The damage mode associated with inelastic deformation of FGM in elevated thermal cycling conditions, however, must be clarified for the practical service environment use. The work reported herein describes the results of numerical experiments on the thermomechanical response of the FGM using Finite Element Methods (FEM) wherein the nonlinear inelasticity of Hastelloy X was utilized for the analysis model. Further experiments were conducted to illustrate the effects of thermal and mechanical properties of FGM constituent materials on the inelastic behavior in thermal cycling environments. The compressive inelastic strain at the hot side surface of FGM in the heat-up cycle causes a significant residual tensile stress generation after the cool-down cycle. Using ceramics with a low thermal expansion coefficient enables the residual tensile stress reduction owing to the less inelastic compressive deformation at the hot side surface of FGM in the heat-up cycle. FGM compositional distribution is less effective for controlling the residual stress. The effects of elastic modulus of the FGM constituent materials were also investigated.

Original languageEnglish
Pages (from-to)98-105
Number of pages8
JournalNippon Kinzoku Gakkaishi/Journal of the Japan Institute of Metals
Volume58
Issue number1
DOIs
Publication statusPublished - Jan 1 1994

Fingerprint

functionally gradient materials
damage
cycles
residual stress
Residual stresses
tensile stress
heat
Thermal cycling
hypersonic aircraft
Tensile stress
Hastelloy (trademark)
gas turbine engines
Hot Temperature
Hypersonic vehicles
Thermal barrier coatings
insulation
Thermal insulation
thermal expansion
modulus of elasticity
finite element method

All Science Journal Classification (ASJC) codes

  • Condensed Matter Physics
  • Mechanics of Materials
  • Metals and Alloys
  • Materials Chemistry

Cite this

Transient thermal cycle damage of thermal barrier type of functionally gradient material. / Matsuzaki, Yuji; Fujioka, Junzo; Yoshikawa, Takao.

In: Nippon Kinzoku Gakkaishi/Journal of the Japan Institute of Metals, Vol. 58, No. 1, 01.01.1994, p. 98-105.

Research output: Contribution to journalArticle

@article{419105b3c747415786c1480958d76987,
title = "Transient thermal cycle damage of thermal barrier type of functionally gradient material",
abstract = "Functionally Gradient Materials (FGM) promise to be used for advanced thermal barrier coatings in gas turbine engines and for heat insulation systems in structural components in hypersonic aircraft. The damage mode associated with inelastic deformation of FGM in elevated thermal cycling conditions, however, must be clarified for the practical service environment use. The work reported herein describes the results of numerical experiments on the thermomechanical response of the FGM using Finite Element Methods (FEM) wherein the nonlinear inelasticity of Hastelloy X was utilized for the analysis model. Further experiments were conducted to illustrate the effects of thermal and mechanical properties of FGM constituent materials on the inelastic behavior in thermal cycling environments. The compressive inelastic strain at the hot side surface of FGM in the heat-up cycle causes a significant residual tensile stress generation after the cool-down cycle. Using ceramics with a low thermal expansion coefficient enables the residual tensile stress reduction owing to the less inelastic compressive deformation at the hot side surface of FGM in the heat-up cycle. FGM compositional distribution is less effective for controlling the residual stress. The effects of elastic modulus of the FGM constituent materials were also investigated.",
author = "Yuji Matsuzaki and Junzo Fujioka and Takao Yoshikawa",
year = "1994",
month = "1",
day = "1",
doi = "10.2320/jinstmet1952.58.1_98",
language = "English",
volume = "58",
pages = "98--105",
journal = "Nippon Kinzoku Gakkaishi/Journal of the Japan Institute of Metals",
issn = "0021-4876",
publisher = "公益社団法人 日本金属学会",
number = "1",

}

TY - JOUR

T1 - Transient thermal cycle damage of thermal barrier type of functionally gradient material

AU - Matsuzaki, Yuji

AU - Fujioka, Junzo

AU - Yoshikawa, Takao

PY - 1994/1/1

Y1 - 1994/1/1

N2 - Functionally Gradient Materials (FGM) promise to be used for advanced thermal barrier coatings in gas turbine engines and for heat insulation systems in structural components in hypersonic aircraft. The damage mode associated with inelastic deformation of FGM in elevated thermal cycling conditions, however, must be clarified for the practical service environment use. The work reported herein describes the results of numerical experiments on the thermomechanical response of the FGM using Finite Element Methods (FEM) wherein the nonlinear inelasticity of Hastelloy X was utilized for the analysis model. Further experiments were conducted to illustrate the effects of thermal and mechanical properties of FGM constituent materials on the inelastic behavior in thermal cycling environments. The compressive inelastic strain at the hot side surface of FGM in the heat-up cycle causes a significant residual tensile stress generation after the cool-down cycle. Using ceramics with a low thermal expansion coefficient enables the residual tensile stress reduction owing to the less inelastic compressive deformation at the hot side surface of FGM in the heat-up cycle. FGM compositional distribution is less effective for controlling the residual stress. The effects of elastic modulus of the FGM constituent materials were also investigated.

AB - Functionally Gradient Materials (FGM) promise to be used for advanced thermal barrier coatings in gas turbine engines and for heat insulation systems in structural components in hypersonic aircraft. The damage mode associated with inelastic deformation of FGM in elevated thermal cycling conditions, however, must be clarified for the practical service environment use. The work reported herein describes the results of numerical experiments on the thermomechanical response of the FGM using Finite Element Methods (FEM) wherein the nonlinear inelasticity of Hastelloy X was utilized for the analysis model. Further experiments were conducted to illustrate the effects of thermal and mechanical properties of FGM constituent materials on the inelastic behavior in thermal cycling environments. The compressive inelastic strain at the hot side surface of FGM in the heat-up cycle causes a significant residual tensile stress generation after the cool-down cycle. Using ceramics with a low thermal expansion coefficient enables the residual tensile stress reduction owing to the less inelastic compressive deformation at the hot side surface of FGM in the heat-up cycle. FGM compositional distribution is less effective for controlling the residual stress. The effects of elastic modulus of the FGM constituent materials were also investigated.

UR - http://www.scopus.com/inward/record.url?scp=0027927148&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=0027927148&partnerID=8YFLogxK

U2 - 10.2320/jinstmet1952.58.1_98

DO - 10.2320/jinstmet1952.58.1_98

M3 - Article

AN - SCOPUS:0027927148

VL - 58

SP - 98

EP - 105

JO - Nippon Kinzoku Gakkaishi/Journal of the Japan Institute of Metals

JF - Nippon Kinzoku Gakkaishi/Journal of the Japan Institute of Metals

SN - 0021-4876

IS - 1

ER -