Abstract: A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.

Abstract: A seal usable to seal a transition in a can-annular combustion system of a turbine engine to a turbine vane assembly to direct exhaust gases through the turbine vane assembly. The seal may be formed from an elongated body extending along an outer edge of the transition and having first and second edges. The first edge of the seal may be attached to the transition, and the elongated body may extend away from the transition edge and contact a portion of the turbine vane assembly. The elongated body may flex during use without yielding or otherwise deforming.

Abstract: A replaceable section (25) of force-cooling tubing assembly (21, 22) for attachment to a transition piece (5) of a gas turbine is comprised of two ends (54, 70) fashioned for attachment by removable unions (52) to adjoining parts of a force-cooling tubing assembly. When assembled thereto to complete the assembly, the replaceable section 25 provides for fluid communication between a manifold (3) and the transition piece (5) for either the supply or return of cooling fluid. A transition piece (5) in combination with two such assemblies, one a supply assembly (21), the other a return assembly (22), comprises a field-installable transition piece assembly (10) that provides for rapid and easy installation.