Gas turbine engine arc segments with arced walls
AssigneeRaytheon Technologies Corporation
InventorsTracy A. Propheter-Hinckley, Justin M. Aniello, Kyle J. Brevick
Life of this patent
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Abstract
A gas turbine engine includes first and second arc segments that each have leading and trailing sides and first and second circumferential sides. The first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion. The first and second slot portions are in registration and together define a seal slot. At least the first slot portion has a first concave arced back wall. A feather seal is entrapped in the seal slot and includes first and second feather seal circumferential sides. At least the first feather seal circumferential side has a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion.
Claims18
A gas turbine engine comprising:
- first and second arc segments each having leading and trailing sides and first and second circumferential sides, the first circumferential side including a first slot portion and the second circumferential side including a second slot portion, the first and second slot portions being in registration and together defining a seal slot, at least the first slot portion having a first concave arced back wall;
- and
- a feather seal entrapped in the seal slot, the feather seal including first and second feather seal circumferential sides, at least the first feather seal circumferential side having a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion, wherein the first concave arced back wall includes a notch and the first feather seal circumferential side includes a tab that is in the notch.
An assembly method for use in a gas turbine engine, the assembly method comprising:
- providing first and second arc segments and a feather seal, the first and second arc segments each have leading and trailing sides and first and second circumferential sides, the first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion, at least the first slot portion has an concave arced back wall, and the feather seal includes first and second feather seal circumferential sides, at least the first feather seal circumferential side has a convex arced edge;
- and
- bringing the first and second arc segments together to entrap the feather seal in the first and second slot portions with the convex arced edge adjacent the concave arced back wall of the first slot portion, wherein the first concave arced back wall includes a notch and the first feather seal circumferential side includes a tab, and the tab is received into the notch when the first and second arc segments are brought together.
A seal for a gas turbine engine comprising:
- a feather seal adapted for use between first and second arc segments of a gas turbine engine, the feather seal being flat, of uniform-thickness, and defining first and second feather seal circumferential sides, at least the first feather seal circumferential side having a convex arced edge, wherein the feather seal is oval or elliptical.
Dependencies are inferred from the claim text.