Patent ID: 7631504

Claim:
A method of assembling a gas turbine engine including at least one combustor, said method comprising: coupling at least one transition portion to the at least one combustor and to at least one gas turbine nozzle such that the at least one transition portion facilitates channeling combustion gases discharged from the at least one combustor to the at least one gas turbine nozzle; defining a downstream combustion gas flow channel within the at least one transition portion; defining a substantially annular upstream airflow channel that is spaced substantially circumferentially about the downstream flow channel and located within a plenum; providing at least one air control system including at least one biasing mechanism and at least one piston coupled to a control mechanism; forming at least one seat within an opening defined in the at least one transition portion, wherein the opening extends between the downstream flow channel and the upstream flow channel, the seat configured to limit movement of the at least one piston; and coupling the air control system to the at least one transition portion to facilitate combustion during engine operation.