Abstract: A divergent flap seal for a gas turbine engine exhaust nozzle having a longitudinal axis is provided, having a body, a spine member, and a flap position guide. The flap position guide separates adjacent divergent flaps regardless of the angle the flaps are skewed relative to the longitudinal axis of the nozzle, thereby more evenly distributing the flaps about the circumference of the nozzle.

Abstract: A seal for a gas turbine engine exhaust nozzle is provided, comprising a body, a spine member attached to one side of the body, and a plurality of face segments attached to the side of the body opposite that to which the spine member is attached. The body includes a length and a width, a plurality of corrugations formed in the body extending across the width, and a first and a second channel. One of the channels is positioned on one side of the body width and the other channel is positioned on the other side of the body width. Each face segment includes a first end and a second end. The ends of the face segments are freely received within the first and second channels such that the ends may translate within the channels.

Abstract: Misalignment tolerances in a nozzle four bar linkage (14, 18, 24, 26) are minimized by direct pinning (42) the A-frame 14 and the mode strut bracket (32). The A-frame and bracket are independently bolted to support 12. Tolerance stackup preventing installation or increasing wear is avoided.