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Supplemental seal for the chordal hinge seals in a gas turbine

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TLDR
In this article, a U-shaped supplemental seal having reversely folded Ushaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment.
Abstract
In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path. To install the supplemental seal, the seal is first compressed and maintained in a compressed state by applying one or more wraps about the supplemental seal or an epoxy 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 nozzle segment and support ring.

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References
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Gas turbine engine shroud seals

TL;DR: In this paper, a ring seal is provided for sealing a joint between a turbine blade tip shroud and a mounting structure where an annular gap is formed having an "L" shaped cross section, the ring seal having a "C" shaped configuration and one of the legs of the "C", extending within an axial component of the gap.
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TL;DR: In this article, a three-piece seal assembly for sealing cooling air leakage between circumferentially spaced-apart flowpath segments in gas turbine engines is described. But the work is restricted to a single engine.
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Turbine nozzle assembly

TL;DR: In this paper, a turbine nozzle assembly includes a plurality of nozzle segments and a nozzle support for supporting the nozzle segments, each of which includes an outer band, an inner band and at least two vanes disposed between the outer and inner bands.
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