Abstract: A nozzle of a gas turbine engine includes an array of radially extending guide vanes fixedly supported at their tip portions to an outer shroud, while the root portion of each vane is connected to a segment of a radially inner, segmented shroud. Each segment is, in turn, connected via a slip fit inter-connection to a radially inner ring support structure of generally L-shaped configuration. A spring extends between the segment and the base of the L-shaped ring support for forming a flexible coupling between the inner ring and the segment, while the remaining portion of the ring support structure defines a pressure dam to reduce leakage through the flexible coupling connection. The segmented nozzle construction effectively reduces stress levels resulting from differential thermal excursions of the components of the nozzle under transient and steady state operation of the engine, while also minimizing leakage through the flexible coupling.