# US 2014/0150403 A1 · Thrust reverser system with translating-rotating cascade and method of operation > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0150403 A1 - Document ID: US20140150403A1 - Status: Published application - Kind: A1 - Application number: 13/690,065 - Filed: 2012-11-30 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Alan Roy Stuart; James Michael Cosgrove - Web page: https://patentgrep.com/patent/US20140150403A1 ## CPC - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - F02K 1/64: Reversing fan flow - F02K 1/70: using thrust reverser flaps or doors mounted on the fan housing - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumferential opening. The cascade system is deployed from a stowed position as the translating cowl and the cascade system are translated in the aft direction. During deployment of the cascade system, a fore end thereof translates in the aft direction and an aft end thereof initially translates in the aft direction and then subsequently rotates about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to a deployed position and divert bypass air within a bypass duct of the engine through the circumferential opening. ## Claims ### Claim 1 A thrust reverser system for a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising: a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween, the translating cowl having a radially inner wall that defines a radially outer flow surface of the bypass duct; a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction; a cascade system mounted to the nacelle and adapted to move between a stowed position and a deployed position, the cascade system having a fore end and an oppositely-disposed aft end, the cascade system translating in the aft direction of the gas turbine engine and away from the fan cowl as the cascade system moves from the stowed position to the deployed position thereof, the aft end of the cascade system projecting into the bypass duct and the cascade system being operable to divert bypass air within the bypass duct through the circumferential opening when the cascade system is in the deployed positions thereof, the fore end of the cascade system being adapted for translating the cascade system in the aft direction, the aft end of the cascade system being adapted for initially causing the aft end to translate in the aft direction as the fore end translates in the aft direction and then subsequently rotate about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to the deployed position thereof. ### Claim 2 (depends on 1) The thrust reverser system according to claim 1, wherein the thrust reverser system does not include a discreet blocker door that blocks air flow within the bypass duct downstream of the cascade segments. ### Claim 3 (depends on 1) The thrust reverser system according to claim 1, further comprising actuators adapted to translate the fore end of the cascade system in the aft direction. ### Claim 4 (depends on 1) The thrust reverser system according to claim 1, further comprising guide connections slidably connected to the fore end of the cascade system and adapted to axially guide the fore end as the cascade system translates in the aft direction with the translating cowl and thereafter as the aft end pivots about the fore end. ### Claim 5 (depends on 4) The thrust reverser system according to claim 4, wherein the guide connections comprise tracks that are entirely linear along lengths thereof and impart solely linear translational motions to the fore end of the cascade system. ### Claim 6 (depends on 1) The thrust reverser system according to claim 1, further comprising: a first link pivotably coupled adjacent the aft end of cascade system and pivotably coupled to the core cowl; and a second link pivotably coupled adjacent the aft end of cascade system and pivotally coupled to the translating cowl. ### Claim 7 (depends on 1) The thrust reverser system according to claim 1, further comprising a link pivotably coupled adjacent the aft end of cascade system and pivotally coupled to the translating cowl, and the thrust reverser system lacks any link coupled to the core cowl. ### Claim 8 (depends on 1) The thrust reverser system according to claim 1, wherein cascade system is adapted to turn air flow within the bypass duct by an angle of greater than 90 degrees. ### Claim 9 (depends on 1) The thrust reverser system according to claim 1, wherein cascade system in the deployed position thereof contacts the core cowl and defines a gap with a fore end of the radially inner wall of the translating cowl. ### Claim 10 A thrust reverser system for a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl, and a bypass duct defined by and between the nacelle and the core cowl, the thrust reverser system comprising: a translating cowl mounted to the nacelle and adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween, the translating cowl having a radially inner wall that defines a radially outer flow surface of the bypass duct; a fixed structure within the nacelle that does not translate when the translating cowl is translated in the aft direction; a cascade system comprising cascade segments mounted to the nacelle and adapted to move between a stowed position and a deployed position, each of the cascade segments having a fore end and an oppositely-disposed aft end, each of the cascade segments translating with the translating cowl in the aft direction of the gas turbine engine and away from the fan cowl as the cascade segment moves from the stowed position to the deployed position thereof, the inner wall of the translating cowl being between each of the cascade segments and the bypass duct when the cascade segments are in their stowed positions, the aft ends of the cascade segments projecting into the bypass duct and the cascade segments being operable to divert bypass air within the bypass duct through the circumferential opening when the cascade segments are in the deployed positions thereof; first means pivotably coupled adjacent the fore end of each of the cascade segments for translating the cascade segment in the aft direction; and second means pivotably coupled adjacent the aft end of each of the cascade segments for initially causing the aft end to translate in the aft direction as the fore end translates in the aft direction and then subsequently causing the aft end to rotate about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to the deployed position thereof; wherein the thrust reverser system does not include a discreet blocker door that blocks air flow within the bypass duct downstream of the cascade segments. ### Claim 11 (depends on 10) The thrust reverser system according to claim 10, wherein the first means comprises actuators adapted to translate the fore ends of the cascade segments in the aft direction. ### Claim 12 (depends on 10) The thrust reverser system according to claim 10, wherein the first means comprises guide connections slidably connected to the fore ends of the cascade segments and adapted to axially guide the fore ends as the cascade segments translate in the aft direction with the translating cowl and thereafter as the aft ends pivot about the fore ends. ### Claim 13 (depends on 12) The thrust reverser system according to claim 12, wherein the guide connections comprise tracks that are entirely linear along lengths thereof and impart solely linear translational motions to the fore ends of the cascade segments. ### Claim 14 (depends on 10) The thrust reverser system according to claim 10, wherein the second means comprises: a first link pivotably coupled adjacent the aft end of each of the cascade segments and pivotably coupled to the core cowl; and a second link pivotably coupled adjacent the aft end of each of the cascade segments and pivotally coupled to the translating cowl. ### Claim 15 (depends on 10) The thrust reverser system according to claim 10, wherein the second means comprises a link pivotably coupled adjacent the aft end of each of the cascade segments and pivotally coupled to the translating cowl, and the thrust reverser system lacks any link coupled to the core cowl. ### Claim 16 (depends on 10) The thrust reverser system according to claim 10, wherein each of the cascade segments is adapted to turn air flow within the bypass duct by an angle of greater than 90 degrees. ### Claim 17 (depends on 10) The thrust reverser system according to claim 10, wherein each of the cascade segments in the deployed position thereof contacts the core cowl and defines a gap with a fore end of the radially inner wall of the translating cowl. ### Claim 18 (depends on 10) A high-bypass gas turbofan engine comprising the thrust reverser system of claim 10. ### Claim 19 A method of reversing thrust of a gas turbine engine having a core engine, a core cowl surrounding the core engine, a nacelle surrounding the core cowl and comprising a fan cowl and a translating cowl adapted to translate in an aft direction of the gas turbine engine away from the fan cowl to define a circumferential opening therebetween, and a bypass duct defined by and between the fan cowl and the core cowl, the method comprising: stowing a cascade system in a stowed position so that an inner wall of the translating cowl is between the bypass duct and the cascade system; translating the translating cowl and the cascade system in an aft direction of the gas turbine engine to expose the circumferential opening; and deploying the cascade system from the stowed positions thereof to a deployed position thereof as the translating cowl and the cascade system are translated in the aft direction, the cascade system having a fore end and an oppositely-disposed second end, the cascade system being deployed as a result of the fore end translating in the aft direction and the aft end initially translating in the aft direction as the fore end translates in the aft direction and then subsequently rotating about the fore end so that further translation of the cascade segment in the aft direction causes the cascade segment to move to the deployed position thereof. ### Claim 20 (depends on 19) The method according to claim 19, wherein the thrust reverser system does not include a discreet blocker door that blocks air flow within the bypass duct downstream of the cascade segments. ### Claim 21 (depends on 19) The method according to claim 19, wherein the cascade system in the deployed position thereof contacts the core cowl. ### Claim 22 (depends on 19) The method according to claim 19, wherein the cascade system in the deployed position thereof defines a gap with a fore end of the radially inner wall of the translating cowl. ### Claim 23 (depends on 19) The method according to claim 19, wherein multiple links pivotally coupling the translating cowl to the cascade segments cause the translating cowl to translate with the cascade system during the translating step.