translate moment from shell/nozzle junction to flange

[s1111]

I have axial load(tensile/compressive) and longitudinal and circumferential bending moments at nozzle/shell intersection. Axial load is along centerline of nozzle, circumferential and longitudinal are along tangential axes at shell.

I need to check flange on a nozzle and for that the loads need to be at end of flange instead of nozzle shell junction. How do I translate the moment?


The loads are numbers from a specification (and have not been derived from pipine, etc. loads)


Any help is helpful.

Thanks
s1111

http://files.engineering.com/getfil...29cf-4cf0-ad79-3a8c00292ca6&file=Drawing1.bmp

 

[JStephen]

If there isn't any shear force, the moments at the flange would be the same as those at the nozzle.

 

[s1111]

thanks JStephen... that is helpful...

Shear forces and Torsional moment are ignored as they have negligible effect in nozzle/shell intersection in most cases... and this is the guideline per the internal spec I am using as no loads were available...
while it appears that the moments shall be same...
but when piping loads are provided, they are different at both points of loading...
ofcourse needless to say the presence of piping system futher complicates my question... and we dont have the piping model... so the loads cant be obtained from it...
are there any general go by guidelines...???

thank u in advance

regards.

 

[SnTMan]

s1111, the loads and moments can be transferred using simple mechanics. In evaluating a flange for external loading, the loads and moments can be converted to an equivalent pressure.

This subject has been discussed previously, you might find it with a site search. I believe the discussion contained references to the calculations.

Regards,

Mike

 

[doct9960]

s111,

As SnTMan had said, forces and moments can be transferred using simple mechanics. See the attachment.

If there are no forces, then the moments at the flange and shell/nozzle junction are the same. Just as JStephen had said.

 

[s1111]

thanks doct9960. that is very helpful.
Thank u Sntman.

regards,
s1111