Abstract: An improved honeycomb seal is provided for turbine engines. The subject honeycomb structure comprises a plurality of identical rings. Each ring has a plurality of radially extending convolutions defining alternating ridges and valleys. The rings are fixedly arranged in abutting relationship to define a tubular honeycomb structure having an array of radially extending honeycomb cells. The resultant honeycomb structure is adaptable to both large and small diameter turbine engines. Furthermore, the individual cells of the honeycomb structure can be constructed to any width or depth.

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.

Abstract: A cylinder of a gas turbine engine is formed of a multilayered construction including a radially inner ceramic ring, the inner surface of which is juxtaposed to the tips of a turbine rotor, an intermediate arrangement of two annular ceramic rings that are substantially L-shaped in cross-section and are disposed in mirror image so as to entrap the radially inner ceramic ring, and a radially outer metallic support means which envelopes the intermediate ceramic rings for maintaining the composite ceramic structure during different operating modes of the turbine engine. The composite ceramic portion of the cylinder enables the engine to operate at higher temperatures, and offers the potential for improved turbine tip clearance control, since the ceramic material is less sensitive to thermal distortion.