# US 2019/0376397 A1 · Gas turbine engine stator vane base shape > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0376397 A1 - Document ID: US20190376397A1 - Status: Published application - Kind: A1 - Application number: 16/001,187 - Filed: 2018-06-06 - Published: 2019-12-12 - Earliest claimed: 2018-06-06 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Nicholas Hunnewell; Michael J. Martel - Web page: https://patentgrep.com/patent/US20190376397A1 ## CPC - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F05D 2230/60: Assembly methods - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2250/232: conical - 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 ## Abstract A stator assembly for use in a gas turbine engine is provided. The stator assembly including: a conical stator shroud including a radially inward surface and a radially outward surface opposite the radially inward surface; and a plurality of stator vanes integrally attached to the conical stator shroud, each of the plurality of stator vanes being integrally attached to the conical stator shroud at a base of the stator vane, wherein radially outward surface of the base of the stator vane mates flush with the radially inward surface of the conical stator shroud. ## Claims ### Claim 1 A stator assembly for use in a gas turbine engine, the stator assembly comprising: a conical stator shroud including a radially inward surface and a radially outward surface opposite the radially inward surface; and a plurality of stator vanes integrally attached to the conical stator shroud, each of the plurality of stator vanes being integrally attached to the conical stator shroud at a base of the stator vane, wherein radially outward surface of the base of the stator vane mates flush with the radially inward surface of the conical stator shroud. ### Claim 2 (depends on 1) The stator assembly of claim 1, wherein the radially outward surface of the base of the guide vane is shaped to create line-to-line surface contact between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 3 (depends on 1) The stator assembly of claim 1, wherein the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud are opposite congruent shapes, such that when the radially outward surface of the base of the guide vane is the radially inward surface of the conical stator shroud there are no overlaps or gaps between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 4 (depends on 1) The stator assembly of claim 1, further comprising: a plurality of fastening mechanism configured to securely fasten the base of each of the plurality of stator vanes to the conical stator shroud. ### Claim 5 (depends on 4) The stator assembly of claim 4, wherein each of the plurality of fastening mechanisms is a rivet. ### Claim 6 (depends on 1) The stator assembly of claim 1, wherein the conical stator shroud has a conical frustum shape. ### Claim 7 A method of manufacturing a stator assembly for use in a gas turbine engine, the method comprising: inserting a stator vane into a vane slot in a radially inward surface of a conical stator shroud; moving the stator vane through the vane slot such that the stator vane projects out of the vane slot from a radially outward surface the conical stator shroud; and securely attaching the stator vane to the conical stator shroud at a base of the stator vane, such that a radially outward surface of the base of the stator vane mates flush with the radially inward surface of the conical stator shroud. ### Claim 8 (depends on 7) The method of claim 7, wherein the radially outward surface of the base of the guide vane is shaped to create line-to-line surface contact between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 9 (depends on 7) The method of claim 7, wherein the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud are opposite congruent shapes, such that when the radially outward surface of the base of the guide vane is the radially inward surface of the conical stator shroud there are no overlaps or gaps between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 10 (depends on 7) The method of claim 7, wherein a plurality of fastening mechanism are configured to securely fasten the base the stator vane to the conical stator shroud. ### Claim 11 (depends on 10) The method of claim 10, wherein each of the plurality of fastening mechanisms is a rivet. ### Claim 12 (depends on 7) The method of claim 7, wherein the conical stator shroud has a conical frustum shape. ### Claim 13 A gas turbine engine, comprising: a compressor section; a turbine section; a stator vane assembly located in at least one of the compressor section and the turbine section, the stator vane assembly comprising: a conical stator shroud including a radially inward surface and a radially outward surface opposite the radially inward surface; and a plurality of stator vanes integrally attached to the conical stator shroud, each of the plurality of stator vanes being integrally attached to the conical stator shroud at a base of the stator vane, wherein radially outward surface of the base of the stator vane mates flush with the radially inward surface of the conical stator shroud. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the radially outward surface of the base of the guide vane is shaped to create line-to-line surface contact between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 15 (depends on 13) The gas turbine engine of claim 13, wherein the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud are opposite congruent shapes, such that when the radially outward surface of the base of the guide vane is the radially inward surface of the conical stator shroud there are no overlaps or gaps between the radially outward surface of the base of the guide vane and the radially inward surface of the conical stator shroud. ### Claim 16 (depends on 13) The gas turbine engine of claim 13, further comprising: a plurality of fastening mechanism configured to securely fasten the base of each of the plurality of stator vanes to the conical stator shroud. ### Claim 17 (depends on 16) The gas turbine engine of claim 16, wherein each of the plurality of fastening mechanisms is a rivet. ### Claim 18 (depends on 13) The gas turbine engine of claim 13, wherein the conical stator shroud has a conical frustum shape.