Strain redistribution corrections were developed for a simplified inelastic analysis procedure to economically calculate material cyclic response at the critical location of a structure for life prediction proposes. The method was based on the assumption that the plastic region in the structure is local and the total strain history required for input can be defined from elastic finite-element analyses. Cyclic stress-strain behavior was represented by a bilinear kinematic hardening model. The simplified procedure predicts stress-strain response with reasonable accuracy for thermally cycled problems but needs improvement for mechanically load-cycled problems. Neuber-type corrections were derived and incorporated in the simplified procedure to...
The problem of calculating turbine engine component durability is addressed. Nonlinear, finite-eleme...
The creep fatigue behavior of a fully impingement cooled blade for four cyclic cases was analyzed by...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...
Strain redistribution corrections were developed for a simplified inelastic analysis procedure to ec...
Simplified inelastic analysis procedures were developed at NASA Lewis and Pratt & Whitney Aircraft f...
A simplified inelastic analysis computer program was developed for predicting the stress-strain hist...
A simplified inelastic analysis computer program (ANSYPM) was developed for predicting the stress-st...
A uniaxial approach was developed for calculating cyclic creep and stress relaxation at the critical...
The influence of inelastic material models on computed stress-strain states, and therefore predicted...
Development of a simplified method for estimating structural inelastic stress and strain response to...
Anisotropic high-temperature alloys are used to meet the safety and durability requirements of turbi...
Estimation of inelastic strains in notched mechanical components and structures are necessary for lo...
Effects of inelastic materials models on computed stress-strain solutions for thermally loaded struc...
Three-dimensional, nonlinear, finite element structural analyses were performed for a simulated airc...
The objective is to develop analytical tools capable of economically evaluating the cyclic time depe...
The problem of calculating turbine engine component durability is addressed. Nonlinear, finite-eleme...
The creep fatigue behavior of a fully impingement cooled blade for four cyclic cases was analyzed by...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...
Strain redistribution corrections were developed for a simplified inelastic analysis procedure to ec...
Simplified inelastic analysis procedures were developed at NASA Lewis and Pratt & Whitney Aircraft f...
A simplified inelastic analysis computer program was developed for predicting the stress-strain hist...
A simplified inelastic analysis computer program (ANSYPM) was developed for predicting the stress-st...
A uniaxial approach was developed for calculating cyclic creep and stress relaxation at the critical...
The influence of inelastic material models on computed stress-strain states, and therefore predicted...
Development of a simplified method for estimating structural inelastic stress and strain response to...
Anisotropic high-temperature alloys are used to meet the safety and durability requirements of turbi...
Estimation of inelastic strains in notched mechanical components and structures are necessary for lo...
Effects of inelastic materials models on computed stress-strain solutions for thermally loaded struc...
Three-dimensional, nonlinear, finite element structural analyses were performed for a simulated airc...
The objective is to develop analytical tools capable of economically evaluating the cyclic time depe...
The problem of calculating turbine engine component durability is addressed. Nonlinear, finite-eleme...
The creep fatigue behavior of a fully impingement cooled blade for four cyclic cases was analyzed by...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...