OS-C501
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Offshore Standard DNV-<strong>OS</strong>-<strong>C501</strong>, November 2013<br />
Sec.14 Calculation example: two pressure vessels – Page 198<br />
5.6 Matrix cracking (ref. Sec.6 [4])<br />
5.6.1 Matrix cracking does not have to be considered for the gas vessel with liner.<br />
5.7 Unacceptably large displacement (ref. Sec.6 [9])<br />
5.7.1 It is assumed for the purpose of this example that the long-term yield strain of the liner is 5%, and this<br />
value should not be exceeded to ensure that the liner will not yield.<br />
5.7.2 The liner in this example is thin and does not contribute to the load bearing capabilities of the vessel. The<br />
liner will follow the deformations of the laminate body of the vessel.<br />
5.7.3 For simplicity we assume that the liner has the same strain as the laminate. In reality the liner will have<br />
slightly larger strain since it is located on the inside of the cylindrical vessel, see [5.2.4]-[5.2.5]. This is taken<br />
into account by introducing a load-model factor, γ Sd = 1.05.<br />
5.7.4 The criterion for unacceptably large displacements from Sec.6 [9.1.1] shall be used.<br />
5.7.5 The following values are selected for the gas vessel with liner:<br />
Table 14-23 Displacement values used for gas vessel with liner<br />
Factors Value Explanation<br />
Specified requirement on maximum d spec 5% See [5.3.2]<br />
displacement<br />
Characteristic value of the local response of d n<br />
Calculated below<br />
the structure (here strain)<br />
Partial load effect factor γ F 1.15 From Sec.8 [2.4]:<br />
Maximum load is known with 0 COV<br />
Strain to failure COV 5%<br />
Target reliability level C<br />
Load-model factor γ Sd 1.05 Same as before, due to simplifications in analytical<br />
model, see [5.2.4]-[5.2.5]<br />
5.7.6 The maximum principle strain in the laminate should be less than 5/(1.15 × 1.1) = 4.14%.<br />
5.7.7 The highest elastic strain in fibre direction is only 0.65%. However, in this case we have to look at the<br />
elastic strain and the plastic strain due to creep. A method to calculate elastic and plastic strain is given in Sec.4<br />
[3.2.11].<br />
ε = ε + elastic ε plastic<br />
or<br />
σ σ<br />
ε = +<br />
E elastic E plastic<br />
5.7.8 Creep in the ±15 o plies: The elastic strain is 0.65%. The plastic strain can be calculated according to the<br />
representative data of App.F for creep:<br />
σ 0.2<br />
ε with time in hours and strain in %.<br />
1520 t<br />
plastic<br />
=<br />
The total strain for the maximum stress of 154 MPa (see [5.2.8]) and 219000 hours is: 0.65%+1.18%=1.83%.<br />
5.7.9 Creep in the ±85 o plies can be calculated the same way. Since the ply stresses are slightly lower, the creep<br />
strain is also slightly less.<br />
5.7.10 The principle strains of the laminate should be calculated from the ply strains and applied to the design<br />
criterion. Since the ply strains are so much below the acceptable levels this calculation is not done here.<br />
5.8 Impact resistance (ref. Sec.6 [12])<br />
γ<br />
d<br />
F<br />
.γ<br />
Sd<br />
. <<br />
n<br />
5.8.1 Impact may be caused by dropped tools etc. The possible impact scenarios, if any, should be defined.<br />
5.8.2 There is no good theoretical criterion to evaluate the resistance to impact. According to Sec.6 [12], the<br />
resistance of a structure to impact shall be tested experimentally.<br />
5.8.3 The critical failure mechanisms in this example is fibre failure. It would have to be shown that the defined<br />
impact scenarios do not cause any fibre failure. This could be shown on full scale specimens or on<br />
representative laminates.<br />
d<br />
spec<br />
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