Patent ID: 8622396

Claim:
A rotary aircraft exhaust system, comprising: an engine, the engine having a first seal face; an exhaust member in gaseous communication with the engine, the exhaust member having a second seal face; a longitudinally compressible bellow seal in sealing contact with both the engine and the exhaust member, the bellow seal being configured to slidingly engage the first seal face and the second seal face; and a first stop protruding from the first seal face; a second stop protruding from the second seal face; wherein the first seal face and the second seal face move in the transverse, longitudinal, and pivoting directions relative to each other; wherein the first stop and the second stop limit radial sliding movement of the bellow seal; and wherein the bellow seal is configured to provide a gaseous seal between the engine and the exhaust member while also allowing the exhaust member to move in the transverse, longitudinal, and pivoting directions relative to the engine.