Abstract: A sealing arrangement for a gas turbine including exhaust and manifold diffusers separated by a circumferential diffuser gap. The sealing arrangement includes a forward clamp arrangement attached to the exhaust diffuser wherein the forward clamp arrangement includes a forward groove. The sealing arrangement also includes an aft clamp arrangement attached to manifold diffuser wherein the aft clamp arrangement includes an aft groove. Further, the sealing arrangement includes a flexible circumferential seal including forward and aft loop portions. The forward loop portion is located in the forward groove and the aft loop portion is located in the aft groove wherein the circumferential seal extends across the circumferential diffuser gap to seal the circumferential diffuser gap. The forward and aft loop portions are moveable in the forward and aft grooves to enable movement of the circumferential seal in a circumferential direction to accommodate thermal expansion of the exhaust and manifold diffusers.

Abstract: A cooling structure for a stationary blade is provided. The cooling structure may include a first chamber in an endwall of the stationary blade directing a first cooling fluid from the stationary blade to a first cooling circuit, and a second chamber in the endwall of the stationary blade directing a second cooling fluid from the stationary blade to a second cooling circuit different than the first cooling circuit. The first cooling fluid has a lower temperature than the second cooling fluid.