# US 10,309,340 B2 · Thrust reverser of a turbojet engine nacelle, comprising control cylinders of movable cowls and a variable secondary nozzle > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,340 B2 - Document ID: US10309340B2 - Status: Granted - Kind: B2 - Application number: 15/281,569 - Filed: 2016-09-30 - Published: 2017-01-19 - Granted: 2019-06-04 - Earliest claimed: 2014-03-31 - Assignees: Aircelle - Applicants: Aircelle - Inventors: Patrick Boileau; Olivier Kerbler - Web page: https://patentgrep.com/patent/US10309340B2 ## CPC - F02K 1/625: {the aft end of the engine cowling being movable to uncover openings for the reversed flow} - F01D 25/24: Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) - F02K 1/72: the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow - F02K 1/763: {with actuating systems or actuating devices; Arrangement of actuators for thrust reversers} - F05D 2220/32: in gas turbines - F05D 2250/34: translated - F05D 2250/90: Variable geometry - 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) - 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 thrust reverser of a bypass turbojet engine nacelle is disclosed, which includes movable cowls that move backwards with respect to a fixed front structure to uncover thrust reverser cascades and a variable secondary nozzle connected to the movable cowls by guide means allowing an axial sliding of the system which controls the movement of this variable secondary nozzle, wherein it includes cylinders bearing on the front structure for controlling reversal means of the displacement direction connected to the movable cowls, which move the variable secondary nozzle backwards when these cylinders output a forward stroke, as well as blocking devices which connect the secondary nozzle to the movable cowls when this nozzle is deployed. ## Claims ### Claim 1 A thrust reverser of a bypass turbojet engine nacelle, comprising: movable cowls, the movable cowls configured to move backwards with respect to a fixed front structure to uncover thrust reverser cascades; a variable secondary nozzle connected to the movable cowls by a guide device, the guide device allowing an axial sliding of a control system of the variable secondary nozzle; cylinders bearing on the fixed front structure for controlling a reversal device connected to the movable cowls, the reversal device moving the variable secondary nozzle backwards when the cylinders output a forward stroke; and blocking devices that connect the variable secondary nozzle to the movable cowls when the variable secondary nozzle is deployed. ### Claim 2 (depends on 1) The thrust reverser according to claim 1, wherein the reversal device includes connecting rods fastened by pivots to the movable cowls. ### Claim 3 (depends on 2) The thrust reverser according to claim 2, wherein each connecting rod is fastened in a central portion by the pivots to the movable cowls, one end of each connecting rod being connected by a hinge to a cylinder, the other end of each connecting rod being connected by a hinge to the variable secondary nozzle. ### Claim 4 (depends on 2) The thrust reverser according to claim 2 further comprising latches that block ends of the connecting rods. ### Claim 5 (depends on 2) The thrust reverser according to claim 2 further comprising double connecting rods disposed symmetrically with respect to an axis of each cylinder, each double connecting rod having a pivot connected the movable cowls. ### Claim 6 (depends on 2) The thrust reverser according to claim 2 further comprising quadruple connecting rods disposed symmetrically with respect to an axis of each cylinder, each quadruple connecting rod having a pivot connected the movable cowls. ### Claim 7 (depends on 2) The thrust reverser according to claim 2 further comprising a plurality of connecting rods in multiples of two disposed symmetrically with respect to an axis of each cylinder, each multiple of two connecting rods having a pivot connected the movable cowls. ### Claim 8 (depends on 1) The thrust reverser according to claim 1 wherein the blocking devices have two positions which can alternately block at least one of the movable cowls on the front fixed structure and the variable secondary nozzle on the movable cowls. ### Claim 9 (depends on 8) The thrust reverser according to claim 8 wherein the blocking devices include a latch connected to the movable cowls, the latch configured to sway to alternately engage a hooking device located on one side on the fixed front structure. ### Claim 10 (depends on 8) The thrust reverser according to claim 8 wherein the blocking devices include a hooking device located on a side of the reversal device. ### Claim 11 (depends on 1) The thrust reverser according to claim 1 wherein the blocking devices include an elastic device providing two blocking and unblocking stable positions. ### Claim 12 (depends on 11) The thrust reverser according to claim 11 wherein the blocking devices include levers connected by pivots to the movable cowls, the levers including blocking members connected to the cylinders, a spring being compressed between the levers to provide the two blocking and unblocking stable positions. ### Claim 13 (depends on 1) A turbojet engine nacelle including a thrust reverser according to claim 1.