A simplified inelastic analysis computer program was developed for predicting the stress-strain history of a thermomechanically cycled structure from an elastic solution. The program uses an iterative and incremental procedure to estimate the plastic strains from the material stress-strain properties and a simulated plasticity hardening model. The simplified method was exercised on a number of problems involving uniaxial and multiaxial loading, isothermal and nonisothermal conditions, and different materials and plasticity models. Good agreement was found between these analytical results and nonlinear finite element solutions for these problems. The simplified analysis program used less than 1 percent of the CPU time required for a nonlinea...
Accomplishments are described for the 2-year program, to develop advanced 3-D inelastic structural s...
Advanced 3-D inelastic structural/stress analysis methods and solution strategies for more accurate ...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...
A simplified inelastic analysis computer program (ANSYPM) was developed for predicting the stress-st...
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...
The influence of inelastic material models on computed stress-strain states, and therefore predicted...
Strain redistribution corrections were developed for a simplified inelastic analysis procedure to ec...
A uniaxial approach was developed for calculating cyclic creep and stress relaxation at the critical...
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...
Three-dimensional, nonlinear, finite element structural analyses were performed for a simulated airc...
Effects of inelastic materials models on computed stress-strain solutions for thermally loaded struc...
The objective is to develop analytical tools capable of economically evaluating the cyclic time depe...
The most critical structural requirements that aircraft gas turbine engines must meet result from th...
Accomplishments are described for the 2-year program, to develop advanced 3-D inelastic structural s...
Advanced 3-D inelastic structural/stress analysis methods and solution strategies for more accurate ...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...
A simplified inelastic analysis computer program (ANSYPM) was developed for predicting the stress-st...
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...
The influence of inelastic material models on computed stress-strain states, and therefore predicted...
Strain redistribution corrections were developed for a simplified inelastic analysis procedure to ec...
A uniaxial approach was developed for calculating cyclic creep and stress relaxation at the critical...
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...
Three-dimensional, nonlinear, finite element structural analyses were performed for a simulated airc...
Effects of inelastic materials models on computed stress-strain solutions for thermally loaded struc...
The objective is to develop analytical tools capable of economically evaluating the cyclic time depe...
The most critical structural requirements that aircraft gas turbine engines must meet result from th...
Accomplishments are described for the 2-year program, to develop advanced 3-D inelastic structural s...
Advanced 3-D inelastic structural/stress analysis methods and solution strategies for more accurate ...
Hot section components of gas turbine engines are subject to severe thermomechanical loads during ea...