Abstract: A combustor assembly is provided. The combustor assembly includes a combustion chamber and at least one transition portion extending downstream from the combustion chamber to facilitate channeling combustion gases from the combustor assembly. The assembly also includes at least one air control system coupled to the at least one transition portion. The air control system including at least one biasing mechanism coupled to a controller to facilitate reducing emissions from the combustor assembly operation.

Abstract: A crossfire tube for attachment between casing bosses of combustors includes a bellows assembly having a bellows with opposite cylindrical ends welded to annular flanges. The annular flanges include a bolt circle for securing the flanges to the combustor bosses. The flanges bear against a gasket for sealing against inserts welded to the casing bosses for retrofit in the sealing assembly to combustors or to seats where the inserts and bosses are formed integrally during original equipment manufacture. A telescoping cylindrical sleeve surrounds the bellows to protect from falling foreign object damage.

Abstract: A thermal isolation device for a gas turbine combustor assembly includes a plurality of substantially flat plates secured in spaced relationship by a plurality of columns, at least one column incorporating a bolt hole for use in securing the device between a pair of combustor components.

Abstract: The endcover assembly for a combustor includes an endcover having an aperture, an insert disposed in the stepped bore opening through an internal face of the endcover, a fuel cartridge extending through the insert and aperture and a seal cover on the external face of the endcover. Seal cover/endcover annular seals are disposed in registering axial cavities to seal against fluid leakage externally of the endcover assembly. Generally C-shaped and W-shaped seals are disposed in the cavities between the stepped shoulders of the insert and aperture to seal against leakage through the internal face of the endcover. The seals maintain sealing engagement during assembly and thermal distortion during turbine usage.

Abstract: A replaceable clip formed from an elongated bowed member having one end adapted to fit a lug through an aperture and the opposite end fit another lug through a slot. The lugs extend from a panel secured by the clip to an annular shaped shell and the bowed surface bears again the upper surface of the shell to retain the panel while allowing it to grow thermally in both the axial and circumferential directions. The clip is particularly adapted to be used in a transition duct or combustor liner of a gas turbine engine.