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US 12,000,288 B2Granted
Variable thickness machinable coating for platform seals
AssigneeRtx Corporation
InventorsRobert A. White, III, Bryan P. Dube, Wojciech Lipka
Life of this patent
Estimating the term…
Abstract
A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.
Claims20
A flow path component assembly, comprising:
- a flow path component having a platform extending from a first circumferential side to a second circumferential side, the platform having a first radius of curvature between the first circumferential side and the second circumferential side;
- and
- a coating arranged on a portion of the platform near the first circumferential side, the coating having a second radius of curvature, the second radius of curvature larger than the first radius of curvature, and wherein the coating is configured to support a mateface seal;
- wherein the platform extends between a radially inner surface and a radially outer surface, the radially inner surface is dimensioned to bound a gas path, and the coating is disposed on the radially outer surface.
1 more element
A flow path component assembly, comprising:
- a flow path component having a platform extending from a first circumferential side to a second circumferential side, the platform having a first radius of curvature between the first circumferential side and the second circumferential side;
- a coating arranged on a portion of the platform near the first circumferential side, the coating having a second radius of curvature, the second radius of curvature larger than the first radius of curvature, and wherein the coating is configured to support a mateface seal;
- wherein the platform extends from a first axial side to a second axial side, and the coating extends from the first axial side to the second axial side;
- wherein the coating has a portion between the first and second axial sides that is flat in an axial direction;
- and
- wherein the portion extends between 25% and 70% of a distance between the first axial side and the second axial side.
3 more elements
A turbine section for a gas turbine engine, comprising:
- a plurality of vanes arranged circumferentially about an engine axis, each vane having a platform, and each of the platforms extend in a radial direction between a first radial side and a second radial side and extend in a circumferential direction between a first circumferential side and a second circumferential side;
- wherein adjacent platforms of the plurality of vanes establish an intersegment gap between the first circumferential side and the second circumferential side of the adjacent platforms;
- a coating arranged on the first radial side along the first circumferential side and the second circumferential side, the coating having a first thickness and a second thickness that is different from the first thickness;
- and
- a mateface seal spanning across the intersegment gap such that the mateface seal sits on the coating near the first circumferential side of one of the adjacent platforms and sits on the coating near the second circumferential side of another one of the adjacent platforms.
2 more elements
A turbine section for a gas turbine engine, comprising:
- a plurality of vanes arranged circumferentially about an engine axis, each vane having a platform, and each of the platforms have a first radial side and a second radial side and extend from a first circumferential side to a second circumferential side;
- a coating arranged on the first radial side along the first circumferential side and the second circumferential side, the coating having a first thickness and a second thickness that is different from the first thickness;
- a mateface seal arranged on the coating near the first circumferential side of the platform of one of the vanes and the second circumferential side of the platform of another one of the vanes;
- and
- wherein the platform extends from a first axial side to a second axial side, and the coating extends from the first axial side to the second axial side, the coating has a portion between the first and second axial sides that is flat in an axial direction, the portion extends between 25% and 70% of a distance between the first axial side and the second axial side.
2 more elements
A turbine section for a gas turbine engine, comprising:
- a plurality of vanes arranged circumferentially about an engine axis, each vane having a platform;
- each of the platforms having a first radial side and a second radial side and extending from a first circumferential side to a second circumferential side;
- a coating arranged on the first radial side along the first circumferential side and the second circumferential side, the coating having a first thickness and a second thickness that is different from the first thickness;
- a mateface seal arranged on the coating near the first circumferential side of the platform of one of the vanes and the second circumferential side of the platform of another one of the vanes;
- and
- wherein an axial seal extends along an axial side of the platform, and a step is formed in the coating, wherein at least a portion of the axial seal is arranged between the step and the mateface seal.
3 more elements
Dependencies are inferred from the claim text.