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In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-s

In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-shaped marginal portions is received in a cavity formed in the second surface. At operating conditions, the marginal portions seal against the base of the cavity and the first surface of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body 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 against opposite sealing surfaces of the shroud segments and retaining ring.

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In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-s

In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-shaped marginal portions is received in a cavity formed in the second surface. At operating conditions, the marginal portions seal against the base of the cavity and the first surface of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body 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 against opposite sealing surfaces of the shroud segments and retaining ring. ty in a compressed state such that said seal body lies wholly within said cavity, said retaining means releasing said seal body from said compressed state in response to turbine operating conditions. 10. A gas turbine according to claim 9 wherein said cavity and said seal body are arcuate in a circumferential direction about an axis of the turbine. 11. A gas turbine according to claim 9 wherein said seal body comprises sheet metal. 12. A gas turbine according to claim 9 wherein said seal body comprises a pair of sheet metal plates secured one to the other. 13. A gas turbine according to claim 9 wherein said seal body is biased to maintain said marginal portions in sealing engagement with said interior cavity surface and said another of said first and second surfaces, respectively. 14. A gas turbine according to claim 9 wherein said seal body comprises a pair of sheet metal plates secured one to the other, said seal body being biased to maintain said marginal portions in sealing engagement with said interior cavity surface and said another of said first and second surfaces. 15. A gas turbine according to claim 9 wherein said retaining means includes a wrap about said seal body. 16. A gas turbine according to claim 9 wherein said retaining means includes an epoxy temporarily maintaining said seal body in said cavity in said compressed state.