Thermal and structural finite element analyses were performed for the turbopump turbine bladed disk model with and without the shroud of a liquid rocket engine. The single sector model was analyzed which consists of 3D eight node isoparametric solid elements. The applied loading history consists of a startup transient condition and a steady state. Heat transfer coefficient on the blade was predicted using the commercial unstructured Navier-Stokes solver, Fluent. Implicit time marching and second order spatial accurate upwind schemes with the $k-\omega$ turbulence closure were used. Heat transfer coefficient on the disk of the model was deduced from integral method of a free-disk for the turbulent flow with dissipation. During a startup condition, heat transfer coefficients were assumed to increase linearly. Transient thermal responses during startup and steady states were computed using the commercial finite element code, Ansys. Von Mises stress distributions under the influence of centrifugal and thermal loading were also determined.
