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Aim: To simulate a Bird Strike on Aero engine in which the blades of the Aero engine fail as a result of high velocity impact Case-Setup: The units system used here is kg-mm-ms. The cylindrical simple elastic component is assumed as the bird for this simulation. The model is divided into individual component key…
Rutvik M
updated on 16 Nov 2020
Aim:
Case-Setup:
The units system used here is kg-mm-ms.
The cylindrical simple elastic component is assumed as the bird for this simulation.
The model is divided into individual component key files and material,part & sections are included in another key file.
Finally, the boundary conditions and control cards are included in a unique key file.
Renumbering
The node ids, element ids,etc., are all renumbered as follows
Material card
Casing is defined by an elastic card with Youngs modulus of 200 GPa and other properties of steel.
Blades is defined with an aluminium elastic-plastic material card given.
Hub is defined as a rigid material with properties of steel as the results in the Hub component are of the least interest in this simulation.
Bird is defined by an elastic material as follows
Youngs modulus = 2 GPa
Density = 1.5E−6kgmm3
Poisson's ratio = 0.47
Boundary conditions
The Casing is constrained at its free edges in all DOFs.
Initial velocity of 0.8 rad/ms (8000 rpm approximately) is given to the Hub and Blades to rotate as a unit.
Bird is given an initial velocity of 150 m/s as the relative velocity between bird and plane would be of that order.
Trials and Debugging
Trial 1 - Blade velocity = 0.5 rad/ms (~5000rpm) & Bird velocity = 6 mm/ms (21.6 km/h)
The bird bounces off of the blades without penerating with such low velocity of the bird.
We can also see the blades penetrating the casing at the end as no contact is defined between them.
Trial 2 - Blade velocity = 0.5 rad/ms (~5000rpm) & Bird velocity = 100 mm/ms (21.6 km/h)
A universal *AUTOMATIC_SINGLE_SURFACE contact is defined to take care of all the unexpected contacts
Large penetrations are seen between the bird and the blades and bird is stuck in the blades. This happened becuse of improper material definition of bird.
The bird's poissons ratio was defined as 0.3 which is usually a case for metals. So it is changed to 0.47
Trial 3 - Blade velocity = 0.5 rad/ms (~5000rpm) ; Bird velocity = 100 mm/ms (21.6 km/h) & Poissons ratio = 0.47 for bird
Now, we can see failure of the blade as a result of contact between both.
Mass scaling
The simulation is run for 3 ms for capturing the collision of bird and failure of blades.
It took 67 seconds to run the simulation without any mass scaling.
Case 1. DT2MS = -5.0E-4
% mass increase = 3.54E-3
Elapsed Time = 36 s
Case 2. DT2MS = -7.0E-4
% mass increase = 6.75E-1
Elapsed Time = 27 s
Case 3. DT2MS = -8.0E-4
% mass increase = 4.64
Elapsed Time = 24 s
The conclusions of mass scaling are as follows
Results:
Plastic Strain Contour
GLSTAT plot
Contact force plot
Conclusions:
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Bird Strike
Aim: To simulate a Bird Strike on Aero engine in which the blades of the Aero engine fail as a result of high velocity impact Case-Setup: The units system used here is kg-mm-ms. The cylindrical simple elastic component is assumed as the bird for this simulation. The model is divided into individual component key…
16 Nov 2020 07:34 AM IST
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