Simulation of Heat Transfer and Temperature Distribution in Jet Engine Rotating Disks

Rotating disks function at high temperatures, thermal gradients and angular velocities in aerial or land gas turbines such as turbojets, turbofans, turboprops and turbojets. These working conditions result in reduced strength of disk material, increased amount of thermal stresses and creation of large centrifugal forces that leads to an increased level of radial and angular stresses. Therefore, thermal analysis of the disk in order to establish appropriate temperature distribution and adequate heat transfer using an effective cooling mechanism is of peculiar importance. In this paper rotating disk problem is modeled in accordance with reality. The problem which consists of a rotating disk and cavity in order to cool the disk surface is considered. After that problem is simulated by simultaneously solving flow and energy equations numerically. The results of the velocity distribution, heat transfer and temperature distribution are comprehensively explained. Furthermore, temperature distribution contours and polynomial approximation to describe the temperature of the disk in terms of its radius are derived for various flight cycles. Also, a comprehensive analysis of the parameters affecting heat transfer and temperature distribution is proposed. The polynomial approximation of temperature profiles of the disk, makes it possible to anticipate disk temperature at any rotational speed. Furthermore, based on the results of this research, outer diameter of the disk is identified as the most critical part of the disk, which is under the most severe thermal-mechanical stress.