04-11-2014, 09:36 AM
Abstracts: A turbine disc plays a significant role in gas turbine. The disc on which blades are mounted transmitting this motion holds a key point to better efficiency of gas turbine. Thus more focus should be given to the design of turbine disc. Gas turbine discs are normally operated at high temperatures. Hot gases contact the blades and the rim of the turbine rotor and thus maintain the rim at higher temperature. The temperature gradient at rim and central portion of rotor causes the sources for thermal stresses. The disc is expected to perform well in spite of all stringent conditions. Also along with performing well, another requirement is weight reduction of disc. As we know increase of structural weight in aircraft costs very high both in terms of operation and maintenance. Also more weight causes more vibration and hence weight becomes a key parameter in design of turbine disc. Weight of the disc depends upon the volume and material of disc. If shape of disc is changed then there is change in material used and this can be used to reduce overall weight of disc. In this project an attempt has been made to compare two cross-sections of turbine disc. One is the original that is used in jet-engines and another is of uniform thickness. It is obvious that the stresses withstand by uniform thickness disc is more compared to varying cross-section. But it is shown by ANSYS analysis about the significance of using disc with variable cross-section in terms of various stresses withstand by both disc and burst margin of both cross-sections.