This paper presents the first phase of numerical modeling of a gas turbine blade subjected to a high temperature flow stream. Continuity, momentum, and energy equations along with high Reynolds number k-E turbulence model were solved using a finite-element numerical computer program (ANSYS 5.3). Temperature and velocity fields were presented at different Reynolds numbers for a turbine blade airfoil and compared with the available experimental results. Results from flow computations around the turbine blade were used as a third kind boundary conditions for a coupled field
thermal- structure analysis. The thermal stress due to the computed temperature distribution was obtained throughout the turbine blade airfoil with and without convection cooling configuration, the turbine blade service life, combined., thermal fatigue-creep failure mode, was predicted using strain ranges partitioning method. A Sun workstation was used to get a numerical solution of the governihg equations. The numerical model provide quite detailed information that help in understanding the physics of the problem. The results showed good agreement with the experimental data available in the literature. The present numerical investigation presents an efficient and more economical technique, which has a great influence on-ihe concurrent engineering concept.