# US 11,994,039 B2 · Shroud for a gas turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,994,039 B2 - Document ID: US11994039B2 - Status: Granted - Kind: B2 - Application number: 17/711,405 - Filed: 2022-04-01 - Published: 2022-11-10 - Granted: 2024-05-28 - Earliest claimed: 2016-07-18 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Kirk Douglas Gallier; Charles William Craig, III - Web page: https://patentgrep.com/patent/US11994039B2 ## CPC - F01D 25/246: {Fastening of diaphragms or stator-rings} - F01D 9/042: {fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246)} - F01D 11/005: {Sealing means between non relatively rotating elements} - 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 gas turbine engine having a rotor blade stage with a plurality of circumferentially spaced rotors, a nozzle stage adjacent the rotor blade stage and including an outer nozzle end, at least one stop, and a shroud. The shroud having a forward end positioned radially outward from the circumferentially spaced rotor blades, and an aft end axially aft of the forward end. The at least one stop confronting at least a portion of the outer nozzle end. ## Claims ### Claim 1 A gas turbine engine defining a longitudinal axis and comprising: a rotor blade stage comprising multiple rotor blades spaced circumferentially with respect to the longitudinal axis; a nozzle stage adjacent the rotor blade stage and comprising a nozzle with an outer nozzle end; a shroud extending between a forward end and an aft end with respect to the longitudinal axis, with the forward end spaced radially outward from the multiple rotor blades, and with the outer nozzle end extending radially outward beyond an outer surface of the shroud; a shroud seal positioned between the nozzle stage and the shroud; and at least one stop spaced from the shroud, the at least one stop defining at least one of an axial position or a circumferential position for the nozzle relative to the shroud. ### Claim 2 (depends on 1) The gas turbine engine of claim 1, wherein the outer nozzle end includes a flange extending across at least a portion of the outer nozzle end. ### Claim 3 (depends on 2) The gas turbine engine of claim 2, wherein the at least one stop directly contacts at least a portion of the flange. ### Claim 4 (depends on 1) The gas turbine engine of claim 1, further comprising an outer casing encasing at least a portion of the shroud. ### Claim 5 (depends on 4) The gas turbine engine of claim 4, wherein the at least one stop extends radially inwardly, with respect to the longitudinal axis, from the outer casing. ### Claim 6 (depends on 1) The gas turbine engine of claim 1, wherein the shroud seal is positioned between the outer nozzle end and the shroud. ### Claim 7 (depends on 1) The gas turbine engine of claim 1, further comprising a pocket within a portion of one of the nozzle or the shroud, wherein the seal is at least partially positioned within the pocket. ### Claim 8 (depends on 1) The gas turbine engine of claim 1, wherein the at least one stop comprises a first stop confronting a first portion of the outer nozzle end, and a second stop confronting a second portion of the outer nozzle end. ### Claim 9 (depends on 8) The gas turbine engine of claim 8, wherein the first stop extends from the second stop. ### Claim 10 (depends on 8) The gas turbine engine of claim 8, wherein the first stop defines the axial position and the second stop defines the circumferential position. ### Claim 11 (depends on 1) The gas turbine engine of claim 1, wherein the outer nozzle end comprises a U-shaped geometric profile when viewed circumferentially with respect to the longitudinal axis. ### Claim 12 A gas turbine engine defining a longitudinal axis and comprising: a rotor blade stage comprising multiple rotor blades spaced circumferentially with respect to the longitudinal axis; a nozzle stage adjacent the rotor blade stage and comprising a nozzle with an outer nozzle end; a casing circumferentially surrounding the rotor blade stage and the nozzle stage; a shroud extending between a forward end and an aft end with respect to the longitudinal axis, with the forward end spaced radially outward from the multiple rotor blades, and with the outer nozzle end extending radially outward beyond an outer surface of the shroud; a shroud seal positioned between the nozzle stage and the shroud; and at least one stop coupled to the casing, the at least one stop defining at least one of an axial position or a circumferential position for the nozzle relative to the shroud. ### Claim 13 (depends on 12) The gas turbine engine of claim 12, wherein the outer nozzle end comprises a flange. ### Claim 14 (depends on 13) The gas turbine engine of claim 13, wherein the at least one stop directly contacts at least a portion of the flange. ### Claim 15 (depends on 12) The gas turbine engine of claim 12, wherein the at least one stop comprises a first stop confronting a first portion of the outer nozzle end and a second stop confronting a second portion of the outer end. ### Claim 16 (depends on 15) The gas turbine engine of claim 15, wherein the first stop defines the axial position and the second stop defines the circumferential position. ### Claim 17 (depends on 12) The gas turbine engine of claim 12, wherein the first stop extends from the second stop.