The disclosed subject matter relates to a gas turbine engine, and more specifically to a system for mounting a combustor transition piece to a frame of the gas turbine engine.
A gas turbine engine includes at least one combustor, which includes a transition piece leading from a combustion zone toward a nozzle of a turbine. The transition piece is typically coupled to a frame, e.g., an aft frame, of the gas turbine engine with an integral mount (e.g., welded in place). For example, the integral mount may extend between the transition piece and the frame in a fixed orientation. Unfortunately, the integral mount may block certain areas requiring access for assembly, service, maintenance, and other operations. For example, the integral mount may block access for a welding operation. Given that the integral mount is fixed in position, the integral mount cannot be removed to provide access for these operations.