# US 10,502,089 B2 · Gas turbine engine variable stator vane > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,502,089 B2 - Document ID: US10502089B2 - Status: Granted - Kind: B2 - Application number: 14/835,849 - Filed: 2015-08-26 - Published: 2016-06-09 - Granted: 2019-12-10 - Earliest claimed: 2014-09-22 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Loi Cheng; Tracy A. Propheter-Hinckley - Web page: https://patentgrep.com/patent/US10502089B2 ## CPC - F01D 17/167: {of vanes moving in translation} - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 17/143: {the shiftable member being a wall, or part thereof of a radial diffuser} - F01D 17/18: varying effective number of nozzles or guide conduits {, e.g. sequentially operable valves for steam turbines} - F04D 27/0246: {by varying geometry within the pumps, e.g. by adjusting vanes} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - F04D 29/563: {specially adapted for elastic fluid pumps} - F05D 2220/32: in gas turbines - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2260/57: using servos, independent actuators, etc. - F05D 2270/101: Compressor surge or stall - F05D 2270/20: to optimize the performance of a machine - 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 gas turbine engine includes a stator stage arranged in a core flow path that includes a vane that is configured to be retractable from the core flow path during engine operation. ## Claims ### Claim 1 A gas turbine engine comprising: a stator stage including a retractable set of vanes arranged in a core flow path that extends in an axial direction relative to the gas turbine engine, each vane of the retractable set of vanes being moveable so as to be retracted from the core flow path into a retracted position or extended into the core flow path into an extended position during operation of the gas turbine engine; and an actuator assembly that includes a fueldraulic system and a master cylinder and a slave cylinder, the slave cylinder being in direct communication with one of the vanes, and the actuator assembly is configured to move the vane in a generally radial direction with respect to the axial direction between the extended position and the retracted position. ### Claim 2 (depends on 1) The gas turbine engine according to claim 1, wherein the stator stage is arranged in a turbine section of the gas turbine engine. ### Claim 3 (depends on 1) The gas turbine engine according to claim 1, wherein the stator stage includes a fixed set of vanes arranged in circumferentially alternating relationship with the retractable set of vanes. ### Claim 4 (depends on 1) The gas turbine engine according to claim 1, wherein the actuator assembly includes an actuator operatively connected to multiple vanes of the retractable set of vanes. ### Claim 5 (depends on 4) The gas turbine engine according to claim 4, wherein the actuator assembly includes a screw operatively connected to the vane, and a ring gear operatively connected to the screw, a motor configured to rotate the ring gear to move the vane between the extended and retracted positions with the screw. ### Claim 6 (depends on 1) The gas turbine engine according to claim 1, wherein the vane includes an end that is spaced from a flow surface in the retracted position, the flow surface defining a portion of the core flow path. ### Claim 7 (depends on 6) The gas turbine engine according to claim 6, wherein the end abuts another flow path surface opposite the flow path surface in the extended position. ### Claim 8 A gas turbine engine comprising: stator stage arranged in a core flow path that includes a vane that is configured to be retractable from the core flow path during operation of the gas turbine engine, wherein the core flow path extends in an axial direction, wherein the stator stage includes a retractable set of vanes that includes the vane; and wherein the stator stage comprises an actuator assembly configured to move the vane in a generally radial direction with respect to the axial direction and between an extended position and a retracted position, and the vane is configured to move between the extended and retracted positions along a non-linear path. ### Claim 9 (depends on 8) The gas turbine engine according to claim 8, wherein the stator stage includes a fixed set of vanes arranged in circumferentially alternating relationship with the retractable set of vanes. ### Claim 10 (depends on 8) The gas turbine engine according to claim 8, wherein the actuator assembly includes an actuator operatively connected to multiple vanes of the retractable set of vanes. ### Claim 11 (depends on 10) The gas turbine engine according to claim 10, wherein the actuator assembly includes a screw operatively connected to the vane, and a ring gear operatively connected to the screw, a motor configured to rotate the ring gear to move the vane between the extended and retracted positions with the screw. ### Claim 12 (depends on 8) The gas turbine engine according to claim 8, wherein the vane includes an end that is spaced from a flow surface in the retracted position, the flow surface defining a portion of the core flow path. ### Claim 13 (depends on 12) The gas turbine engine according to claim 12, wherein the end abuts another flow path surface opposite the flow path surface in the extended position. ### Claim 14 A gas turbine engine comprising: radially inner and outer flow surfaces defining a core flow path; and a stator stage arranged in the core flow path that includes a vane that is configured to be retractable from the core flow path during operation of the gas turbine engine, wherein the core flow path extends in an axial direction, wherein the stator stage includes a retractable set of vanes that includes the vane; and wherein the stator stage comprises an actuator assembly configured to move the vane in a generally radial direction with respect to the axial direction and between an extended position and a retracted position, and the vane includes an end that is spaced radially across the core flow path from the outer flow surface in the retracted position. ### Claim 15 A gas turbine engine comprising: a stator stage arranged in a core flow path and including a vane that is configured to be retractable from the core flow path during operation of the gas turbine engine by an actuator assembly, wherein the core flow path extends in an axial direction, and the stator stage is arranged in a compressor section of the gas turbine engine; and wherein the actuator assembly includes a screw operatively connected to the vane and a ring gear operatively connected to the screw, and the screw further comprises a fluid passage provided through the screw to communicate cooling fluid to the vane.