Patent ID: 8020831

Claim:
A suspension for suspending a turbine engine from the structure of an aircraft comprising: a beam with an attachment device which attaches to said structure; and at least one link rod articulated via a first end to a journal secured to the beam and via a second end to a fitting secured to the turbine engine, wherein said journal is mounted on the beam via a flexible coupling provided by first and second laminated, elastomer and metal, cylinders which support first and second ends of the journal, respectively, the first and second laminated cylinders are disposed in first and second cylindrical housings, respectively, and the link rod is provided between the first and second laminated cylinders in an axial direction, wherein each of the first and second laminated cylinders includes an annular first inner armature secured to the journal, a second outer armature with an outer surface abutting an inner surface of the cylindrical housing, and an elastomer layer provided between the first inner armature and the second outer armature, the first and second armatures are coaxial with the journal, and wherein an outer surface of the first inner armature is frustoconical and tapers from a first end to a second end closer to the link rod such that an outer diameter at the first end of the first inner armature is greater than an outer diameter at the second end of the first inner armature, and an inner surface of the second outer armature is frustoconical and tapers from a first end to a second end closer to the link rod such that an inner diameter at the first end of the second outer armature is greater than an inner diameter at the second end of the second outer armature such that the elastomer layer between the first and second armatures is preloaded by the first and second armatures.