Patent ID: 9097130
Filing Date: 2015-08-04
Classification: F01D,F05D,F23R,Y02E

Abstract:
1. A seal assembly comprising: a liner at least partially defining a combustion chamber of a gas turbine, the liner having at least one tubular liner collar through which an injector is inserted, wherein the at least one tubular liner collar has a partially convex outer diameter; a floating collar positioned at least partially around the at least one tubular liner collar; and a retention member having a first end fixed to the floating collar and a second end configured to abut the partially convex outer diameter of the at least one tubular liner collar, wherein the retention member maintains the floating collar at a radial distance from the injector less than a radial distance between an inner diameter of the at least one tubular liner collar and the injector, and wherein the retention member is S-shaped, with at least one curved portion abutting the at least one tubular liner collar.