# US 11,111,881 B2 · Aircraft engine assembly with isolation valve outside uncontained rotor impact area > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,111,881 B2 - Document ID: US11111881B2 - Status: Granted - Kind: B2 - Application number: 16/305,925 - Filed: 2017-05-24 - Published: 2020-10-22 - Granted: 2021-09-07 - Earliest claimed: 2016-05-30 - Assignees: Airbus Canada Limited Partnership - Applicants: C Series Aircraft Limited Partnership - Inventors: Olivier Goudard; Angelo Coluni - Web page: https://patentgrep.com/patent/US11111881B2 ## 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 1/76: Control or regulation of thrust reversers - F02K 1/763: {with actuating systems or actuating devices; Arrangement of actuators for thrust reversers} - B64D 27/12: within, or attached to, wings - B64D 29/06: Attaching of nacelles, fairings or cowlings - F02K 1/766: {with blocking systems or locking devices; Arrangement of locking devices for thrust reversers} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/129: Cascades, i.e. assemblies of similar profiles acting in parallel - F05D 2270/64: Hydraulic actuators - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract An aircraft has a fuselage, left and right wings, and left and right engine assemblies connected to the wings. Each engine assembly has a nacelle, an engine housed in the nacelle, the engine having a plurality of rotors defining an uncontained rotor impact area, a pylon connecting the nacelle to its wing, at least one hydraulic actuator connected to at least one of the engine and the nacelle, at least one directional control valve hydraulically connected to the at least one hydraulic actuator, and at least one isolation valve hydraulically connected to the at least one directional control valve for selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed rearward of the uncontained rotor impact area and forward of a trailing edge of its corresponding wing. ## Claims ### Claim 1 An aircraft comprising: a fuselage; a left wing connected to the fuselage and extending on a left side of the fuselage; a right wing connected to the fuselage and extending on a right side of the fuselage; a left engine assembly connected to the left wing; and a right engine assembly connected to the right wing, each of the left and right engine assemblies comprising: a nacelle; an engine housed in the nacelle, the engine having a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area; a pylon connecting the nacelle to a corresponding one of the left wing and the right wing; at least one hydraulic actuator connected to at least one of the engine and the nacelle; at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator; an aft fairing connected to a rear of the pylon and to a bottom of the corresponding one of the left wing and the right wing; and at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the corresponding one of the left wing and the right wing, rearward of the pylon, inside the aft fairing, rearward of the uncontained rotor impact area and forward of a trailing edge of the corresponding one of the left wing and the right wing. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein for each of the left and right engine assemblies the at least one directional control valve is disposed inside the pylon. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein for each of the left and right engine assemblies the at least one isolation valve is laterally aligned with the pylon. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein for each of the left and right engine assemblies the at least one isolation valve is disposed rearward of the at least one directional control valve. ### Claim 5 (depends on 1) The aircraft of claim 1, wherein for each of the left and right engine assemblies the at least one isolation valve is disposed rearward of a leading edge of the corresponding one of the left wing and the right wing. ### Claim 6 (depends on 1) The aircraft of claim 1, wherein for each of the left and right engine assemblies the at least one directional control valve is disposed in the uncontained rotor impact area. ### Claim 7 (depends on 1) The aircraft of claim 1, wherein: for each of the left and right engine assemblies: the uncontained rotor impact area includes: a large fragment uncontained rotor impact area; and a small fragment uncontained rotor impact area, the large fragment uncontained rotor impact area being smaller than the small fragment uncontained rotor impact area; the at least one isolation valve of the left engine assembly is disposed: rearward of the small fragment uncontained rotor impact area of the plurality of rotors of left engine assembly; and outside of the large fragment uncontained rotor impact area of the plurality of rotors of the right engine assembly; and the at least one isolation valve of the right engine assembly is disposed: rearward of the small fragment uncontained rotor impact area of the plurality of rotors of right engine assembly; and outside of the large fragment uncontained rotor impact area of the plurality of rotors of the left engine assembly. ### Claim 8 (depends on 1) The aircraft of claim 1, wherein each of the left and right engine assemblies further comprises a thrust reverser system operatively connected to the engine; and wherein for each of the left and right engine assemblies the at least one hydraulic actuator includes at least one hydraulic thrust reverser actuator for actuating the thrust reverser system. ### Claim 9 (depends on 1) The aircraft of claim 1, further comprising: at least one hydraulic fluid reservoir hydraulically connected with the at least one isolation valve of the left engine assembly and the at least one isolation valve of the right engine assembly; and at least one hydraulic pump hydraulically connected to the at least one hydraulic fluid reservoir for pressurizing hydraulic fluid in the at least one hydraulic fluid reservoir for selectively applying hydraulic pressure to the at least one hydraulic actuator of the left engine assembly and the at least one hydraulic actuator of the right engine assembly. ### Claim 10 An aircraft comprising: a fuselage; a left wing connected to the fuselage and extending on a left side of the fuselage; a right wing connected to the fuselage and extending on a right side of the fuselage; a left engine assembly connected to the left wing; and a right engine assembly connected to the right wing, each of the left and right engine assemblies comprising: a nacelle; an engine housed in the nacelle, the engine having a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area; a pylon connecting the nacelle to a corresponding one of the left wing and the right wing; an aft fairing connected to a rear of the pylon and to a bottom of the corresponding one of the left wing and the right wing; at least one hydraulic actuator connected to at least one of the engine and the nacelle; at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator; and at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the corresponding one of the left wing and the right wing, rearward of the pylon, and inside the aft fairing. ### Claim 11 (depends on 10) The aircraft of claim 10, wherein for each of the left and right engine assemblies the at least one directional control valve is disposed inside the pylon. ### Claim 12 (depends on 10) The aircraft of claim 10, wherein for each of the left and right engine assemblies the at least one isolation valve is disposed rearward of the at least one directional control valve. ### Claim 13 (depends on 10) The aircraft of claim 10, wherein each of the left and right engine assemblies further comprises a thrust reverser system operatively connected to the engine; and wherein for each of the left and right engine assemblies the at least one hydraulic actuator includes at least one hydraulic thrust reverser actuator for actuating the thrust reverser system. ### Claim 14 (depends on 10) The aircraft of claim 10, further comprising: at least one hydraulic fluid reservoir hydraulically connected with the at least one isolation valve of the left engine assembly and the at least one isolation valve of the right engine assembly; and at least one hydraulic pump hydraulically connected to the at least one hydraulic fluid reservoir for pressurizing hydraulic fluid in the at least one hydraulic fluid reservoir for selectively applying hydraulic pressure to the at least one hydraulic actuator of the left engine assembly and the at least one hydraulic actuator of the right engine assembly. ### Claim 15 An aircraft comprising: a fuselage; a left wing connected to the fuselage and extending on a left side of the fuselage; a right wing connected to the fuselage and extending on a right side of the fuselage; a left engine assembly connected to the left wing; and a right engine assembly connected to the right wing, each of the left and right engine assemblies comprising: a nacelle; an engine housed in the nacelle, the engine having a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area; a pylon connecting the nacelle to a corresponding one of the left wing and the right wing; at least one hydraulic actuator connected to at least one of the engine and the nacelle; at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator; an aft fairing connected to a rear of the pylon and to a bottom of the corresponding one of the left wing and the right wing; and at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the corresponding one of the left wing and the right wing, rearward of the pylon, inside the aft fairing, rearward of a leading edge of the corresponding one of the left wing and the right wing and forward of a trailing edge of the corresponding one of the left wing and the right wing. ### Claim 16 (depends on 15) The aircraft of claim 15, wherein for each of the left and right engine assemblies the at least one directional control valve is disposed inside the pylon. ### Claim 17 (depends on 15) The aircraft of claim 15, wherein for each of the left and right engine assemblies the at least one isolation valve is laterally aligned with the pylon. ### Claim 18 (depends on 15) The aircraft of claim 15, wherein each of the left and right engine assemblies further comprises a thrust reverser system operatively connected to the engine; and wherein for each of the left and right engine assemblies the at least one hydraulic actuator includes at least one hydraulic thrust reverser actuator for actuating the thrust reverser system. ### Claim 19 (depends on 15) The aircraft of claim 15, further comprising: at least one hydraulic fluid reservoir hydraulically connected with the at least one isolation valve of the left engine assembly and the at least one isolation valve of the right engine assembly; and at least one hydraulic pump hydraulically connected to the at least one hydraulic fluid reservoir for pressurizing hydraulic fluid in the at least one hydraulic fluid reservoir for selectively applying hydraulic pressure to the at least one hydraulic actuator of the left engine assembly and the at least one hydraulic actuator of the right engine assembly. ### Claim 20 A hydraulic system for actuating a thrust reverser of an aircraft engine assembly, the aircraft engine assembly being connected to an aircraft wing and comprising a plurality of rotors, the plurality of rotors defining an uncontained rotor impact area, the hydraulic system comprising: at least one hydraulic actuator for actuating the thrust reverser; at least one directional control valve hydraulically connected to the at least one hydraulic actuator for controlling a direction of motion of the at least one hydraulic actuator, the at least one directional control valve being within the uncontained rotor impact area; and at least one isolation valve hydraulically connected to the at least one directional control valve, the at least one isolation valve selectively cutting off a supply of hydraulic fluid to the at least one directional control valve, the at least one isolation valve being disposed under the aircraft wing, rearward of a pylon, inside an aft fairing connected to a rear of the pylon and to a bottom of the aircraft wing, rearward of the uncontained rotor impact area and forward of a trailing edge of the aircraft wing. ### Claim 21 (depends on 20) The hydraulic system of claim 20, wherein the at least one isolation valve is disposed rearward of the at least one directional control valve. ### Claim 22 (depends on 20) The hydraulic system of claim 20, wherein the at least one isolation valve is disposed rearward of a leading edge of the aircraft wing. ### Claim 23 (depends on 20) The hydraulic system of claim 20, further comprising: at least one hydraulic fluid reservoir hydraulically connected with the at least one isolation valve; and at least one hydraulic pump hydraulically connected to the at least one hydraulic fluid reservoir for pressurizing hydraulic fluid in the at least one hydraulic fluid reservoir for selectively applying hydraulic pressure to the at least one hydraulic actuator.