Friday, February 26, 2010

Load incrementation of initially weak structures

I just worked on an FEA model which was essentially a flat, very thin plate of plastic with a pressure applied. Initially, I always use small displacement and linear contact (bonded) for debugging a model just to make sure that loads and boundary conditions are correct. This saves time because large deformation effects can introduce much longer solve times. The linear model solved fine.

When I turned on the large displacement option (nlgeom), the model failed to converge even after several cutbacks (bisections). I certainly did not expect to solve the model in one substep, but I thought the default bisection algorithm would find a converged solution. I was using automatic timestep control. I reduced the initial substep until I eventually obtained a solution, but by this point the subsequent substeps were so small that it would take many, many substeps to complete the load step.

I noticed that after the first substep converged, convergence for later substeps required only a few iterations. Therefore, I broke the load step into 2 separate steps. In the first step, the load was reduced to the value that converged earlier, about 1/1000th. In the second step, I specified the full load with a reasonably sized initial substep. The model had no trouble converging, even though the load had dramatically increased between steps. The reason is that the initial stiffness of the plate is bending only, because it was flat. Since it was a very thin plastic component, the bending stiffness is very low. The first step established some membrane stiffness as the plate tries to assume a more spherical shape. Once the load generates some membrane stress and there is membrane stiffness, subsequent predictions of displacement are more accurate.

I have also used this 2 step load strategy for preloading of bolts. Sometimes, not always, the contact resisting the preload has trouble converging with the full preload. Before contact is established, there is no stiffness resisting the preload. Then, the contact overcloses so much that the solver cannot resolve the overclosure efficiently.

Sunday, February 21, 2010

Engineering Simulation at Olympics

I have been watching Vancouver Winter Olympics 2010 with great deal of attention. My loyalties lie with US but cheer any genuinely great sporting achievement. What fascinates me is the true grit and determination of these athletes to overcome great odds to attain perfection! And knowing our passion "engineering simulation" has helped them along towards these levels of perfection really brings a huge smile on my face.

Images Courtesy: www.fluent.com

I wanted to bring light to some of the engineering simulation such as FEA, CFD etc., that goes on in preparation towards these levels of perfections.

Above images show pressure contours on a simulated skeleton slider, with pathlines colored by velocity magnitude (Postprocessed by Ensight). The story behind the simulation is as interesting as the technology itself. You can read the complete story here. The story in short goes something like this: In preparation for 2006 Winter Olympics at Turin, Italy, Kristan Bromley, the top-ranked skeleton bobsled competitor in the UK, approached the Elite Sports CFD Unit - a part of the Sports Engineering Research Group (SERG) in Sheffield, UK - and asked them to provide CFD flow simulation support to increase his chances of success. Bromley's goal:
Minimize the overall aerodynamic drag by assessing small changes in surface texture of his skin-suit. Bromley ended up with a respectable 5th ranking in Turin Winter Olympics and went on to bring home the first gold medal for Britain since 1965 at the 2008 FIBT World Championships. Bromley maintains philosophy of using advanced technology to enhance on-ice performance. Although, the CFD analysis may have been just a drop in the ocean in terms of the dedication, grit and determination for such olympic athletes, it is still atleast a drop!

More information: http://www.bromley-aet.com/

Below are a few more articles that show the role of engineering simulation that goes into such perfection!
ANSYS Article: Giving Ski Racers an Edge
FLUENT Article: CFD for Bob Sled Team
ANSYS Article: Finite Element Analysis on Mountain Climbing Ice Axe to study crack initiation on serrated blade.

Hats off to all the fantastics athletes and the engineering simulation that is enhancing their performance on ice! :)

Friday, February 5, 2010

Turbine Blade Modal Analysis



I have recently had the opportunity to work on a few steam turbine blade failure investigations and have found a whole new world of engineering simulation that I had not been exposed to. Analysis of turbine blades is its own animal and even though steam turbines have been in use in power generation for a very long time, the physics of power generation is so complex there are many areas that are still not well understood. Being new to turbine analysis I thought my experiences as I lean steam turbine analysis may be useful to others. The first topic I would like to describe has been fundamental to all of the turbine projects that I have been involved with: Modal analysis of a bladed disk row. In each investigation, modal analysis was used to calculate the natural frequencies and mode shapes for a particular stage of blades. This is a valuable tool in determining if the blades are operating near a resonant condition that could be responsible for a failure.
As you can find in any vibrations textbook, modal analysis is an eigenvalue procedure in which the eigenvalues of the equation of motion are the square of the natural frequencies and the eigenvectors are the mode shapes. For blade analysis, SimuTech Group uses an in-house developed code to run a modal Finite Element Analysis on turbine blades. This program is called BLADE.
A portion of the bladed disk is modeled in BLADE which usually consists of a 360°/N sector, where N is the number of blades in the row. The mass and stiffness matrices for the bladed disk sector are then reduced to a superelement containing selected fewer degrees of freedom. These selected degrees of freedom are called master degrees of freedom. They are selected in such a way as to be able to represent and predict the dynamic behavior of the bladed disk.
At operating speed, the rotating system stiffens because of the centrifugal effects. This stress stiffening causes the natural frequencies to be higher than their corresponding values calculated at zero RPM. The effect of the stress stiffening is evaluated and incorporated in the analysis.
If a rotating bladed disk is excited by a forcing which is fixed spatially, there are 3 conditions that need to be satisfied in order to produce a resonant condition:
1. The natural frequency of the blade row is equal to some per-rev forcing frequency
2. The number of nodal diameter of the natural mode equals the forcing harmonic number.
3. The excitation must be able to couple with the blade disk mode shape. For example, the forcing on the blade row must be in a direction that matches the mode shape deflection. If the forcing is along the axial direction of the turbine and the mode shape shows deflection only in the tangential direction, the mode can not be excited. Of course many modes contain components in both axial and tangential directions.
If all of the above conditions are met, resonance will occur. This natural frequency-forcing relationship is usually illustrated as an Interference diagram. In the Interference diagram, the natural frequency is plotted against the number of nodal diameters (harmonic content of a mode). An example of an interference diagram is shown above. The line through the origin is called the Impulse Line which corresponds to the operating speed. Whenever the Impulse Line intersects the natural frequency curves, a resonant condition may exist.
The Interference diagram is used to locate frequencies of interest for a more detailed stress analysis. Resonant stresses are calculated for these conditions and detuned as necessary to estimate the true dynamic stress in each blade. The dynamic stress will also depend on the damping present in the system as well as the stimulus ratio (the ratio of dynamic forcing to the steam bending force in the blade). Dynamic stress analysis is a discussion on its own and will likely be a topic of future entries.
Thanks for reading.