There are several structural parts in aero engines with demands on high containment capability. The demand is that the structure that surrounds the engines rotating parts must prevent that loose parts, for instance turbine blades during a fan blade off event, perforate the structure causing failure on the surrounding aircraft structure. Today only limited calculation methods exist for containment dimensioning that incorporates the complicated physics that arises in the structure during a fan blade off event. To analyze and simulate the ability for the containment structure to contain the turbine blade during a fan blade off event more effectively, a numeric method (Finite Element Method) is desirable.
During the research an analysis method will be developed for containment dimensioning. The analysis method is based on tests on the material Inconel 718. The revealed method will then be implemented in commercial software for use within the flight industry. The aim is that the dimensioning tool, based on explicit FEM, incorporates the physical phenomenon during a fan blade off event whereby flight turbines sustain safer margins combined with a reduced weight on the containment structure. The expected result will lead to enhanced knowledge about containment dimensioning, but also increased awareness concerning material behavior during high strain rates under the influence of high temperatures.
The research started in the beginning of 2010 in co work with Volvo Aero Company and the Solid Mechanics at LTU. The project is financed by VINNOVA within the program NFFP5, the fifth round of the National Flight technical Research Program.