A method of installing a seal into a turbomachine and turbomachine with such a seal

摘要

In a gas turbine including a nozzle retaining ring (42) having a first annular axially facing sealing surface (48) and a shroud segment (41) having an axial registering second surface (46). To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal ((70) having reversely folded U-shaped marginal portions is received in a cavity (80) formed in the second surface. At operating conditions, the marginal portions seal against the base (82) of the cavity and the first surface (48) of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body (71) is first compressed and maintained in a compressed state by applying one or more wraps about the seal body and an epoxy is used to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions (74) Öagainst opposite sealing surfaces of the shroud segments and retaining ring. <IMAGE> <IMAGE>