# US 12,000,306 B2 · Vane arc segment with single-sided platforms > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,000,306 B2 - Document ID: US12000306B2 - Status: Granted - Kind: B2 - Application number: 17/831,933 - Filed: 2022-06-03 - Published: 2023-12-07 - Granted: 2024-06-04 - Earliest claimed: 2022-06-03 - Assignees: Rtx Corporation - Applicants: Raytheon Technologies Corporation - Inventors: Michael G. McCaffrey - Web page: https://patentgrep.com/patent/US12000306B2 ## CPC - F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments} - F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)} - 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 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/005: {Selecting particular materials} - F04D 9/041: {the priming pump having evacuating action (F04D9/043 and F04D9/06 take precedence)} - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/80: Platforms for stationary or moving blades - F05D 2250/75: given by its similarity to a letter, e.g. T-shaped - F05D 2300/2261: of silicon - F05D 2300/2283: of silicon - F05D 2300/6033: Ceramic matrix composites [CMC] - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A vane arc segment includes ceramic matrix composite (CMC) fairing that has an airfoil section, a first single-sided platform at the outer radial end projecting from the suction side wall, and a second single-sided platform at the inner radial end projecting from the pressure side wall. The first single-sided platform is comprised of a fiber layer that extends from the airfoil section and turns into the first single-sided platform, and the second single-sided platform is comprised of the fiber layer that from the airfoil section and turns into the second single-sided platform. ## Claims ### Claim 1 A vane arc segment comprising: a ceramic matrix composite (CMC) fairing including an airfoil section defining suction and pressure side walls, leading and trailing ends, and inner and outer radial ends, a first single-sided platform at the outer radial end projecting in a first circumferential direction from the suction side wall, and a second single-sided platform at the inner radial end projecting in a second, opposite circumferential direction from the pressure side wall, wherein the first single-sided platform being comprised of a fiber layer extending from the airfoil section at the first radial end and turning into the first single-sided platform, and the second single-sided platform being comprised of the fiber layer extending from the airfoil section at the second radial end and turning into the second single-sided platform, the first single-sided platform includes an edge portion that has a contour that is complementary in shape to the pressure side wall of the airfoil section, and aft of the edge portion the first single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, aft of the airfoil section. ### Claim 2 (depends on 1) The vane arc segment as recited in claim 1, wherein the first single-sided platform includes an edge portion that has a contour that is complementary in shape to the pressure side wall of the airfoil section. ### Claim 3 (depends on 2) The vane arc segment as recited in claim 2, wherein, aft of the edge portion, the first single-sided platform includes a straight portion. ### Claim 4 (depends on 1) The vane arc segment as recited in claim 1, the fiber layer in the airfoil section having a first fiber architecture and the fiber layer in at least one of the first single-sided platform or the second single-sided platform has a second fiber architecture that is different than the first fiber architecture with respect to ordered arrangements of fiber tows in the first fiber architecture and the second fiber architecture. ### Claim 5 (depends on 4) The vane arc segment as recited in claim 4, wherein the first fiber architecture has a first volume of fibers and the second fiber architecture has a second volume of fibers that is less than the first volume of fibers. ### Claim 6 (depends on 1) The vane arc segment as recited in claim 1, the second single-sided platform includes an edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section, and forward of the edge portion of the second single-sided platform, the second single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, forward of the airfoil section. ### Claim 7 (depends on 1) The vane arc segment as recited in claim 1, wherein the second single-sided platform includes an edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section. ### Claim 8 (depends on 7) The vane arc segment as recited in claim 7, wherein, forward of the edge portion, the second single-sided platform includes a straight portion. ### Claim 9 (depends on 1) The vane arc segment as recited in claim 1, wherein the CMC fairing is made of a CMC material that has silicon-containing ceramic fiber and a silicon-containing matrix. ### 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 a ceramic matrix composite (CMC) fairing including an airfoil section defining suction and pressure side walls, leading and trailing ends, and inner and outer radial ends, a first single-sided platform at the outer radial end projecting in a first circumferential direction from the suction side wall, and a second single-sided platform at the inner radial end projecting in a second, opposite circumferential direction from the pressure side wall, wherein the first single-sided platform being comprised of a fiber layer extending from the airfoil section at the first radial end and turning into the first single-sided platform, and the second single-sided platform being comprised of the fiber layer extending from the airfoil section at the second radial end and turning into the second single-sided platform, the first single-sided platform includes an edge portion that has a contour that is complementary in shape to the pressure side wall of the airfoil section, and aft of the edge portion the first single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, aft of the airfoil section. ### Claim 11 (depends on 10) The gas turbine engine as recited in claim 10, further comprising inner and outer diameter supports supporting the vane arc segments by, respectively, the first single-sided platform and the second single-sided platform. ### Claim 12 (depends on 10) The gas turbine engine as recited in claim 10, wherein, when under aerodynamic loading, the vane arc segments transfer loads to the inner and outer diameter supports via, respectively, the first single-sided platform and the second single-sided platform, and the airfoil section is in compression. ### Claim 13 (depends on 10) The gas turbine engine as recited in claim 10, the fiber layer in the airfoil section having a first fiber architecture and the fiber layer in at least one of the first single-sided platform or the second single-sided platform has a second fiber architecture that is different than the first fiber architecture with respect to ordered arrangements of fiber tows in the first fiber architecture and the second fiber architecture. ### Claim 14 (depends on 10) The gas turbine engine as recited in claim 10, the second single-sided platform includes an edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section, and forward of the edge portion of the second single-sided platform, the second single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, forward of the airfoil section. ### Claim 15 (depends on 10) The gas turbine engine as recited in claim 10, wherein the first single-sided platform includes a first platform edge portion that has a contour that is complementary in shape to the pressure side wall of the airfoil section. ### Claim 16 (depends on 15) The gas turbine engine as recited in claim 15, wherein the second single-sided platform includes a second platform edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section. ### Claim 17 (depends on 16) The gas turbine engine as recited in claim 16, wherein, aft of the first platform edge portion, the first single-sided platform includes a first platform straight portion. ### Claim 18 (depends on 17) The gas turbine engine as recited in claim 17, wherein, forward of the second platform edge portion, the second single-sided platform includes a second platform straight portion. ### Claim 19 A vane arc segment comprising: a ceramic matrix composite (CMC) fairing including an airfoil section defining suction and pressure side walls, leading and trailing ends, and inner and outer radial ends, a first single-sided platform at the outer radial end projecting in a first circumferential direction from the suction side wall, and a second single-sided platform at the inner radial end projecting in a second, opposite circumferential direction from the pressure side wall, wherein the first single-sided platform being comprised of a fiber layer extending from the airfoil section at the first radial end and turning into the first single-sided platform, the second single-sided platform being comprised of the fiber layer extending from the airfoil section at the second radial end and turning into the second single-sided platform, and the second single-sided platform includes an edge portion that has a contour that is complementary in shape to the suction side wall of the airfoil section, and forward of the edge portion of the second single-sided platform, the second single-sided platform includes a straight portion, the straight portion comprising circumferentially-facing surfaces on both suction and pressure side wall facing sides of the straight portion, forward of the airfoil section.