# US 12,006,845 B2 · Vane arc segment with flange and gusset > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,845 B2 - Document ID: US12006845B2 - Status: Granted - Kind: B2 - Application number: 18/088,166 - Filed: 2022-12-23 - Published: 2023-04-27 - Granted: 2024-06-11 - Earliest claimed: 2021-03-30 - Assignees: Rtx Corporation - Applicants: Rtx Corporation - Inventors: Jon E. Sobanski; Bryan P. Dube - Web page: https://patentgrep.com/patent/US12006845B2 ## CPC - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 5/147: {Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18)} - F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments} - F01D 5/284: {Selection of ceramic materials} - F01D 9/04: forming ring or sector - F01D 11/005: {Sealing means between non relatively rotating elements} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/80: Platforms for stationary or moving blades - F05D 2300/6033: Ceramic matrix composites [CMC] - 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 vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange. ## Claims ### Claim 1 A vane arc segment comprising: an airfoil fairing formed of a ceramic matrix composite and having first and second fairing platforms and an airfoil section extending therebetween, the airfoil section having a pressure side, a suction side, and an internal cavity, the first fairing platform defining suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side, the flange extending along the suction side circumferential mate face, and a rib having a rib section in the internal cavity spanning the pressure side and the suction side and a rib extension section extending from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform, the rib extension intersecting the flange to form a gusset for reinforcing the flange, the rib extension terminating at a fillet between the pressure side of the airfoil section and the first fairing platform, and the first fairing platform including a seal flange projecting from the non-gaspath side and overhanging the pressure side circumferential mate face. ### Claim 2 (depends on 1) The vane arc segment as recited in claim 1, wherein the rib extension is substantially perpendicular to the flange. ### Claim 3 (depends on 2) The vane arc segment as recited in claim 2, wherein, relative to the non-gaspath side, the rib extension defines a rib extension height, the flange defines a flange height, and the flange height is approximately equal to the rib extension height. ### Claim 4 (depends on 1) The vane arc segment as recited in claim 1, wherein the rib extension defines a rib extension through-thickness, the flange defines a flange through-thickness, and the rib extension through-thickness is less than the flange through-thickness. ### Claim 5 (depends on 4) The vane arc segment as recited in claim 4, wherein the seal flange includes a radial bearing face. ### Claim 6 (depends on 1) The vane arc segment as recited in claim 1, wherein the airfoil fairing is arranged about a gas turbine engine central axis, and the suction and pressure side circumferential mate faces form angles of 15° to 60° relative to the gas turbine engine central axis. ### Claim 7 (depends on 6) The vane arc segment as recited in claim 6, wherein the flange is flush with the suction side circumferential mate face. ### Claim 8 (depends on 6) The vane arc segment as recited in claim 6, wherein the flange is offset from the suction side circumferential mate face. ### Claim 9 (depends on 1) The vane arc segment as recited in claim 1, wherein the airfoil fairing is arranged about a gas turbine engine central axis, the flange includes a radial face that has a curved profile, and the curved profile is a cylindrical surface segment of a reference cylinder having a main axis that is co-linear with the gas turbine engine central axis. ### Claim 10 A gas turbine engine comprising: a compressor section; a combustor in fluid communication with the compressor section; and a turbine section in fluid communication with the combustor, the turbine section having vane arc segments disposed about a central axis of the gas turbine engine, each of the vane arc segments includes: an airfoil fairing formed of a ceramic matrix composite and having first and second fairing platforms and an airfoil section extending therebetween, the airfoil section having a pressure side, a suction side, and an internal cavity, the first fairing platform defining suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange projecting from the non-gaspath side, the flange extending along the suction side circumferential mate face, and a rib having a rib section in the internal cavity spanning the pressure side and the suction side and a rib extension section extending from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform, the rib extension intersecting the flange to form a gusset for reinforcing the flange, the rib extension terminating at a fillet between the pressure side of the airfoil section and the first fairing platform, and the first fairing platform including a seal flange projecting from the non-gaspath side and overhanging the pressure side circumferential mate face.