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A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection dev

A system includes a gas turbine engine, a nozzle structure located adjacent to the gas turbine engine, a flexible annular seal linking the gas turbine engine and the nozzle structure, the flexible annular seal having a plurality of corrugate sections arranged about a centerline, and a connection device secured to the gas turbine engine and to the nozzle structure. The connection device is adjustable to select a length of the flexible annular seal measured along the centerline.

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1. A system comprising: a gas turbine engine;a nozzle structure located adjacent to the gas turbine engine;a flexible annular seal linking the gas turbine engine and the nozzle structure, wherein the flexible annular seal comprises exactly two corrugate sections arranged about a centerline;a connect

1. A system comprising: a gas turbine engine;a nozzle structure located adjacent to the gas turbine engine;a flexible annular seal linking the gas turbine engine and the nozzle structure, wherein the flexible annular seal comprises exactly two corrugate sections arranged about a centerline;a connection device secured to the gas turbine engine and to the nozzle structure, wherein the connection device is adjustable to select a length of the flexible annular seal measured along the centerline, wherein the connection device comprises: a strap; andan adjustment mechanism configured to maintain the strap at a selected engaged length;a first bracket attached to the gas turbine engine, wherein the connection device is engaged with the first bracket to secure the connection device to the gas turbine engine; anda second bracket attached to the nozzle structure, wherein the connection device is engaged with the second bracket to secure the connection device to the nozzle structure, wherein the second bracket comprises: a first portion attached to the nozzle structure; anda second portion extending from the first portion at an angle greater than zero and less than 90° in a direction away from the flexible annular seal. 2. The system of claim 1, wherein the connection device is configured to compress the flexible annular seal along the centerline. 3. The system of claim 1, wherein the first bracket comprises: a first portion attached to the gas turbine engine; anda second portion extending from the first portion at an angle greater than zero and less than 90° in a direction away from the flexible annular seal. 4. The system of claim 3, wherein the first bracket further comprises an opening in the second portion usable to engage the connection device. 5. The system of claim 1 and further comprising: a reinforcement member positioned between the two corrugate sections. 6. The system of claim 5, wherein the reinforcement member comprises an annular tube positioned adjacent to an outer surface of the flexible annular seal. 7. The system of claim 1, wherein the plurality of corrugate sections are integral and comprise a single monolithic piece. 8. The system of claim 1, wherein the connection device is positioned adjacent to a radially outward surface of the flexible annular seal. 9. A system comprising: a gas turbine engine assembly;a nozzle;a flexible annular wall having a first end that is attachable to the gas turbine engine assembly and a second end that is attachable to the nozzle to define a seal therebetween, wherein the flexible annular wall defines a plurality of corrugate portions;a first clamp bracket at the first end of the flexible annular wall attached to the gas turbine engine assembly, wherein the first bracket comprises: a first portion attached to the gas turbine engine; anda second portion extending from the first portion at an angle greater than zero and less than 90° in a direction away from the flexible annular wall;a second clamp bracket at the second end of the flexible annular wall attached to the nozzle structure; anda connection device secured to the first clamp bracket and to the second clamp bracket, wherein the connection device is adjustable to select a compressive clamping length measured relative to a centerline defined along a center of the flexible annular wall, and wherein the connection device comprises: a strap; andan adjustment mechanism configured to maintain the strap at a selected engaged length. 10. The system of claim 9 and further comprising: a reinforcement member positioned about an outer surface of the flexible annular wall and configured to reduce outward flexibility of at least a portion of the flexible annular wall. 11. The system of claim 10, wherein the reinforcement member comprises an annular tube positioned adjacent to an outer surface of the flexible annular wall. 12. The system of claim 9, wherein the plurality of corrugate sections are integral and comprise a single monolithic piece. 13. The system of claim 9, wherein the connection device is configured to compress the flexible annular wall along the centerline. 14. A method for providing a seal in a gas turbine engine system, the method comprising: establishing a connection between a first end of a flexible annular seal and a gas turbine engine;establishing a connection between a second end of the flexible annular seal and an exhaust nozzle;defining exactly two corrugations in the flexible annular seal;positioning a reinforcement member about an outer surface of the flexible annular seal at a location between the two corrugations;providing a first bracket located at or near the first end of the of the flexible annular seal and a second bracket located at or near the second end of the flexible annular seal, wherein at least one of the first and second brackets includes a first portion and a second portion extending from the first portion at an angle greater than zero and less than 90° in a direction away from the flexible annular seal;operatively connecting a compressive tool between the first and second brackets located at or near the first and second ends of the flexible annular seal to control an effective length of the flexible annular seal along a centerline defined by the flexible annular seal; andadjusting a mechanism to maintain the compressive tool at a selected engaged length. 15. The system of claim 9, wherein the plurality of corrugate sections define exactly two corrugate sections.