Patent ID: 8459936
Filing Date: 2013-06-11
Classification: F01D,F02C,F02K,F05D,F16J,F16L,Y10T

Abstract:
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 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; and a 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: