George77577
Aerospace
- Apr 30, 2010
- 13
We have an ongoing issue with cracking around nozzle attachments in over the road filament wound tankers. Only see this in sodium hypochlorite service. Appears to be predominate in the high stress areas such as nozzles and to some extent head attachment.
1. Road tankers have very high dynamic loads but since we don't see this in HCL have to assume its related to Hypo in some way.
2. We tried a higher elongation resin...onset of problems appears sooner. So assume resin is less resistant and effect is corrosion related but resin matrix shows no obvious sign of degradation.
3. Surface veils may play a role and increase rigidity = more susceptiple to cracking in high stress areas?
4. Hypo is unstable and possible corrosion effect is related to the E-glass fibers being attacked once veil layers are breached.
5. Degree of cracking and types vary from small micro to larger but only in Hypo service. Anyone have any ideas on the root cause? We have onboard samples and they provide some direction but not conclusive. Its been a battle for some years still trying to uncover.
Pictures show typical effect. Possible stress induced during cure due to shrinkage? Laminate is .180" could be reduced to .125" ? Not a stuctural laminate just corrosion barrier.
Any comments?
1. Road tankers have very high dynamic loads but since we don't see this in HCL have to assume its related to Hypo in some way.
2. We tried a higher elongation resin...onset of problems appears sooner. So assume resin is less resistant and effect is corrosion related but resin matrix shows no obvious sign of degradation.
3. Surface veils may play a role and increase rigidity = more susceptiple to cracking in high stress areas?
4. Hypo is unstable and possible corrosion effect is related to the E-glass fibers being attacked once veil layers are breached.
5. Degree of cracking and types vary from small micro to larger but only in Hypo service. Anyone have any ideas on the root cause? We have onboard samples and they provide some direction but not conclusive. Its been a battle for some years still trying to uncover.
Pictures show typical effect. Possible stress induced during cure due to shrinkage? Laminate is .180" could be reduced to .125" ? Not a stuctural laminate just corrosion barrier.
Any comments?