Patent ID: 8920893
Filing Date: 2014-12-30
Classification: B21D,B23P,F01D,F04D,F05D,Y10S,Y10T

Abstract:
1. An article for minimizing a transfer of vibrations in an aerofoil blade of a gas turbine engine, the article comprising: a cavity; and first and second panels spaced apart from each other with the cavity disposed between the first and second panels, the first panel having at least one bowed protrusion having a proximal end and a distal end, the protrusion extending therefrom within the cavity towards the second panel, and the second panel has at least one pocket, wherein: the proximal end of the protrusion is secured to the first panel and the distal end of the protrusion is slidably secured in the pocket of the second panel; the first panel includes an exterior wall and at least one interior membrane leaf, the proximal end of the protrusion being integral with at least one of the interior membrane leaves; the second panel includes an exterior wall and at least one interior membrane leaf, the pocket being disposed between the exterior wall and at least one of the interior membrane leaves; and at least one of the interior membrane leaves is metallic.