Skip to Main Content
Skip Nav Destination
ASME Press Select Proceedings

International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3

Yi Xie
Yi Xie
Search for other works by this author on:
No. of Pages:
ASME Press
Publication date:

There are numerous applications of gas turbine in the aerospace industry such as in liquid rocket engines. In this paper, stresses of gas turbine blade of turbopump unit used in liquid rocket engine are investigated using finite element (FE) analysis. Due to the complexity of the geometry, a three-dimensional (3-D) solid modeling of the blade and a part of the disc was first created on CAD software and subsequently exported to a FE package for analysis. Stresses developed due to the real turbine operating conditions were analyzed, taking into consideration the material behavior at elevated temperatures. The FE results reveals that the greatest stresses in the blade result from thermal and rotational loads owing to the relatively high operating speed and temperature of the turbine, while bending stresses on the blade due to gas pressure are significantly lower than those due to rotation and thermal. Finally the stresses at the blade due to thermal load are shown to be higher than those for all the mechanical loads rotation and gas pressure.

This content is only available via PDF.
You do not currently have access to this chapter.
Close Modal

or Create an Account

Close Modal
Close Modal