Section
4 Structural Integrity
4.1 General
4.1.1 The structural design shall ensure that tanks have an adequate capacity
to sustain all relevant loads with an adequate margin of safety. This should take
into account the possibility of plastic deformation, buckling, fatigue and loss of
liquid and gas tightness.
4.2 Structural analyses
4.2.1
Analysis
The design analyses shall be based on accepted principles of statics,
dynamics and strength of materials.
Simplified methods or simplified analyses may be used to calculate the
load effects, provided that they are conservative. Model tests may be used in
combination with, or instead of, theoretical calculations. In cases where
theoretical methods are inadequate, model or full-scale tests may be required.
When determining responses to dynamic loads, the dynamic effect shall be
taken into account where it may affect structural integrity.
Where direct calculation procedures are adopted, the assumptions made
and other details of the calculations are to be submitted.
4.2.2
Load scenarios
For each location or part of the cargo containment system to be
considered and for each possible mode of failure to be analysed, all relevant
combinations of loads that may act simultaneously shall be considered.
The most onerous load scenarios for all relevant phases of the life-cycle
shall be considered. Loads during construction/handling, installation, on-site
operation, inspection/maintenance including testing and in transit/disconnect
conditions shall be considered, as applicable.
4.2.3 When the static and dynamic stresses are calculated separately and unless
other methods of calculation are justified, the total stresses shall be calculated
according to:
where:
σx.st, σy.st, σz.st, τxy.st,
τxz.st and τyz.st = static stresses
σx.dyn, σy.dyn, σz.dyn,
τxy.dyn, τxz.dyn and τyz.dyn = dynamic stresses
Each shall be determined separately from acceleration components and
hull strain components due to deflection and torsion.
4.3 Design conditions
4.3.1 All relevant failure modes shall be considered in the design for all
relevant load scenarios and design conditions. The design conditions are given in
the earlier part of this Chapter, and the load scenarios are covered by Pt 11, Ch 4, 4.2 Structural analyses 4.2.2.
4.3.2
On-site operation design condition
Structural capacity may be determined by testing, or by analysis, taking
into account both the elastic and plastic material properties, or by simplified
linear elastic analysis.
- Plastic deformation and buckling shall be considered.
- Analysis shall be based on characteristic load values as
follows:
Permanent
Loads
|
Expected
Values
|
Functional
Loads
|
Specified
Values
|
Environmental
Loads
|
Wave loads are to
be calculated at a return period of 100 years.
|
- For the purpose of strength assessment the
following material parameters apply:
-
R
e = specified minimum yield stress at room temperature
(N/mm2). If the stress-strain curve does not show a
defined yield stress, the 0,2 per cent proof stress applies.
R
m = specified minimum tensile strength at room
temperature (N/mm2).
NOTE
For welded connections where under-matched welds,
i.e. where the weld metal has lower tensile strength than the
parent metal, are unavoidable, such as in some aluminium alloys,
the respective R
e and R
m of the welds, after any applied heat treatment,
shall be used. In such cases the transverse weld tensile
strength shall not be less than the actual yield strength of the
parent metal. If this cannot be achieved, welded structures made
from such materials shall not be incorporated in cargo
containment systems.
- The above properties shall correspond to the minimum
specified mechanical properties of the material, including the weld
metal in the as-fabricated condition. Subject to special
consideration by LR, account may be taken of the enhanced yield
stress and tensile strength at low temperature.
- The equivalent stress σc (von Mises, Huber)
shall be determined by:
where
σx =
total normal stress in x-direction
σy =
total normal stress in y-direction
σz =
total normal stress in z-direction
τxy =
total shear stress in x-y plane.
τxz =
total shear stress in x-z plane
τyz =
total shear stress in y-z plane.
- Allowable stresses for materials
other than those covered by Chapter 6 shall be subject to approval by LR in
each case.
Details of the proposals are to be submitted for
consideration.
- Stresses may be further limited by fatigue analysis, crack
propagation analysis and buckling criteria.
4.3.3
Fatigue design condition
- The fatigue design condition is the design condition with
respect to accumulated cyclic loading.
- The maximum allowable cumulative fatigue damage ratio
CW is to be less than or equal to 0,5, but is to be no
greater than 0,33 for any parts of the supporting structure which are not
accessible for inspection during the service life of the unit.
The fatigue damage shall be based on the design life of the
containment system but not less than 25 years unless agreed otherwise by
LR.
- The fatigue assessment of the cargo containment system is to be
verified in accordance with the ShipRight Procedure for Ship Units.
The loading/unloading history is to be consistent with the
intended operation of the ship unit. Plastic strain is to be accounted
for in the low cycle region. Loading and unloading cycles are to include
a complete pressure and thermal cycle.
- Design S-N curves used in the analysis shall be applicable to
the materials and weldments, construction details, fabrication procedures
and applicable state of the stress envisioned.
The S-N curves
shall be based on a 97,6 per cent probability of survival corresponding
to the mean minus two standard deviation curves of relevant experimental
data up to final failure. Use of S-N curves derived in a different way
requires adjustments to the acceptable C
w values specified in (g), (h) and (i).
- Analysis shall be based on characteristic load values as
follows:
Permanent
Loads
|
Expected
Values
|
Functional
Loads
|
Specified values
or specified history
|
Environmental
Loads
|
Expected load
history, but not less than 108 cycles
|
If simplified dynamic loading spectra are used for
the estimation of the fatigue life, those shall be specially considered
by LR.
- Where the size of the secondary barrier is
reduced, as is provided for in Pt 11, Ch 4, 2.2 Cargo containment safety principles 2.2.3, fracture mechanics analyses of fatigue crack growth
shall be carried out for the primary barrier to determine:
- Crack propagation paths in the structure.
- Crack growth rate.
- The time required for a crack to propagate to cause a
leakage from the tank.
- The size and shape of through thickness cracks.
- The time required for detectable cracks to reach a
critical state.
The fracture mechanics are in general based on crack
growth data taken as a mean value plus two standard deviations of the
test data.
- In analysing crack propagation the largest initial
crack or equivalent defect not detectable by the inspection
method applied shall be assumed, taking into account the
allowable non-destructive testing and visual inspection
criterion as applicable.
- For the crack propagation analysis under the
condition specified in Pt 11, Ch 4, 4.3 Design conditions 4.3.3.(g), the simplified load distribution and
sequence over the RD, as specified in Pt 11, Ch 4, 1.1 Definitions 1.1.9, may be used, unless different
project-specific requirements apply. Project-specific
requirements are to be submitted for consideration. Such
distributions may be obtained as indicated in Figure 4.4.1 Simplified load distribution. Load distribution and sequence
for longer periods, such as in (h) and (i) below shall be
approved by LR.
- The arrangements shall comply with (g), (h) and (I)
below as applicable:
Figure 4.4.1 Simplified load distribution
- For failures that can be reliably detected by
means of leakage detection;
-
C
w shall be less than or equal to 0,5.
- The predicted remaining failure development time, from
the point of detection of leakage until reaching a critical state,
shall not be less than the RD, as specified in Pt 11, Ch 4, 1.1 Definitions 1.1.1, unless different project-specific requirements
apply. Project-specific requirements are to be submitted for
consideration.
- For failures that cannot be detected by
leakage but that can be reliably detected at the time of in-service
inspections;
-
C
w shall be less than or equal to 0,5.
- Predicted remaining failure development time, from the
largest crack not detectable by in-service inspection methods until
reaching a critical state, shall not be less than three times the
inspection interval.
- In particular locations of the tank where
effective defect or crack development detection cannot be assured, the
following, more stringent, fatigue acceptance criteria should be applied as
a minimum;
-
C
w shall be less than or equal to 0,1.
- The predicted failure development time, from the assumed
initial defect until reaching a critical state, shall not be less
than three times the lifetime of the tank.
4.3.4
Accident design condition
The accident design condition is a design condition for accidental loads
with extremely low probability of occurrence. Analysis shall be based on the
characteristic values as follows:
Permanent Loads
|
Expected Values
|
Functional Loads
|
Specified values
|
Environmental Loads
|
Specified values
|
Accidental
loads
|
Specified values
or expected values
|
Loads mentioned in Pt 11, Ch 4, 3.3 Functional loads 3.3.9 and Pt 11, Ch 4, 3.5 Accidental loads need not be combined with each other or with wave induced
loads.
|