Abstract
The shape and size chosen for the cross section of shrink rings can be such as to minimize the thermal stresses in the rings and the bending stresses in the enclosed shell in the case of a shell heated by a internal gas flow. In this study, the authors prove that it is possible to reduce these stresses by installing a damping ring near the flange at a distance that will ensure a stress level during shell bending under the flange no higher than the stress level attained under the optimum ring. Illustrations show the deflection of the heated shell near the flange and optimum ring, as well as the deflection of the shell with the damping ring. The effectiveness of installing a damping ring on the exhaust pipes of an An-22 airplane was established from the results of operation of the plane before and after installation.
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