Shroud seal
AssigneeGeneral Electric Company
InventorMelvin Bobo
Life of this patent
Estimating the term…
Abstract
To prevent overheating of the gaps between shroud segments circumferentially arranged about a high pressure turbine rotor, an improved seal is provided to block radial leakage flow of hot working gas through the gaps, as well as to restrict axial flow of working gas in the gaps. The seal includes a corrugated, axial fluid flow restricting element sandwiched between a pair of radially spaced, gap spanning shim sealing elements. Pressurized cooling air is admitted to the gap at locations between the shim sealing elements via passages through adjacent shroud segments to cool the gap and to further restrict working gas axial flow in the gap.
Claims13
In a segmented annular shroud for confining the axial flow of hot working gas in a gas turbine engine, a seal for blocking radial leakage flow of working gas through a gap between adjacent shroud segments, and seal comprising, in combination:
- A. a first axially elongated strip sealing element spanning the gap and having lateral edges received in opposed first slots formed in confronting, gap-defining, radial surfaces of adjacent shroud segments;
- B. a second, axially elongated strip sealing element spanning the gap and having lateral edges received in opposed second slots formed in said confronting, gap-defining, radial surfaces of the adjacent shroud segments, said second sealing element being in radially spaced relation with said first sealing element;
- and
- C. a flow restricting element disposed between said first and second sealing elements to restrict the axial flow of hot working gas in the gap between said first and second sealing elements.
Dependencies are inferred from the claim text.