# US 12,000,288 B2 · Variable thickness machinable coating for platform seals > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,288 B2 - Document ID: US12000288B2 - Status: Granted - Kind: B2 - Application number: 17/246,912 - Filed: 2021-05-03 - Published: 2022-11-03 - Granted: 2024-06-04 - Earliest claimed: 2021-05-03 - Assignees: Rtx Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Robert A. White, III; Bryan P. Dube; Wojciech Lipka - Web page: https://patentgrep.com/patent/US12000288B2 ## CPC - F01D 11/005: {Sealing means between non relatively rotating elements} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 11/003: {by packing rings; Mechanical seals} - F01D 25/005: {Selecting particular materials} - F01D 25/246: {Fastening of diaphragms or stator-rings} - F05D 2230/90: Coating; Surface treatment - F05D 2240/11: Shroud seal segments - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The flow path component assembly of claim 1, wherein the coating has a first thickness and a second thickness, the second thickness is closer to the first circumferential side than the first thickness, the second thickness is smaller than the first thickness. ### Claim 3 (depends on 1) The flow path component assembly of claim 1, wherein the coating has a thickness less than 0.100 inches (2.54 mm). ### Claim 4 (depends on 1) The flow path component assembly of claim 1, 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. ### Claim 5 (depends on 4) The flow path component assembly of claim 4, wherein the coating has a portion between the first and second axial sides that is flat in an axial direction. ### Claim 6 (depends on 1) The flow path component assembly of claim 1, wherein the coating extends a circumferential distance from the first circumferential side of less than 0.250 inches (6.35 mm). ### Claim 7 (depends on 1) The flow path component assembly of claim 1, wherein the platform comprises a ceramic matrix composite material. ### Claim 8 (depends on 1) The flow path component assembly of claim 1, wherein the platform is a vane platform. ### Claim 9 (depends on 8) The flow path component assembly of claim 8, wherein the vane platform is an outer vane platform. ### Claim 10 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. ### Claim 11 (depends on 10) The flow path component assembly of claim 10, wherein the coating has a first thickness in the portion that is smaller than an outer thickness forward or aft of the portion. ### Claim 12 (depends on 10) The flow path component assembly of claim 10, wherein the platform comprises a ceramic matrix composite material. ### Claim 13 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. ### Claim 14 (depends on 13) The turbine section of claim 13, wherein the platform has a first radius of curvature in the circumferential direction, the coating having a second radius of curvature in the circumferential direction, and the second radius of curvature is larger than the first radius of curvature. ### Claim 15 (depends on 13) The turbine section of claim 13, wherein a spring assembly biases the mateface seal into engagement with the coating. ### Claim 16 (depends on 13) The turbine section of claim 13, wherein the mateface seal comprises a metallic material. ### Claim 17 (depends on 16) The turbine section of claim 16, wherein at least one of the adjacent platforms comprises a ceramic material. ### Claim 18 (depends on 13) The turbine section of claim 13, wherein the first radial side includes a localized region free of the coating, and the second radial side bounds a gas path of the turbine section. ### Claim 19 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. ### Claim 20 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.