# US 10,370,111 B2 · Hidden thrust reverser blocker door link arm fitting > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,370,111 B2 - Document ID: US10370111B2 - Status: Granted - Kind: B2 - Application number: 15/258,927 - Filed: 2016-09-07 - Published: 2018-03-08 - Granted: 2019-08-06 - Earliest claimed: 2016-09-07 - Assignees: United Technologies Corporation - Applicants: United Technologies Corporation - Inventors: Nigel David Sawyers-Abbott; Matthew Exner - Web page: https://patentgrep.com/patent/US10370111B2 ## CPC - B64D 29/06: Attaching of nacelles, fairings or cowlings - B64D 27/16: of jet type - 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 1/56: Reversing jet main flow - 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} - F16C 11/045: {with at least a pair of arms pivoting relatively to at least one other arm, all arms being mounted on one pin (crank-pins F16C11/02)} - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2230/60: Assembly methods - F05D 2260/50: Kinematic linkage, i.e. transmission of position - F16C 2360/23: Gas turbine engines - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - 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) - F16C: SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS - 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 linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm. ## Claims ### Claim 1 A linkage system for a nacelle comprising: a pivot configured to extend through a second aperture disposed in a link arm; a base member; and a retaining member at least partially defining a first aperture and a cavity, wherein the pivot is configured to extend at least partially into the first aperture, wherein the cavity is configured to accommodate a portion of the link arm, and wherein the retaining member defines a first portion of the first aperture and the base member defines a second portion of the first aperture. ### Claim 2 (depends on 1) The linkage system of claim 1, wherein the base member is configured to be attached to an inner fixed structure (IFS) of the nacelle. ### Claim 3 (depends on 2) The linkage system of claim 2, wherein the link arm comprises a thrust reverser link arm. ### Claim 4 (depends on 3) The linkage system of claim 3, wherein the first aperture extends in a direction substantially orthogonal to the cavity. ### Claim 5 (depends on 4) The linkage system of claim 4, wherein the retaining member is configured to retain the link arm to the base member. ### Claim 6 (depends on 1) The linkage system of claim 1, wherein the pivot is retained within the first aperture in response to the retaining member being fastened to the base member. ### Claim 7 (depends on 1) The linkage system of claim 1, wherein the retaining member comprises an attachment aperture extending substantially orthogonal to the first aperture, the attachment aperture configured to accommodate a fastener for fastening the base member to the retaining member. ### Claim 8 (depends on 1) The linkage system of claim 1, wherein the first portion comprises a first half and the second portion comprises a second half. ### Claim 9 (depends on 1) The linkage system of claim 1, wherein the cavity comprises a high aspect ratio aperture. ### Claim 10 A nacelle for a gas turbine engine comprising: an inner fixed structure (IFS) comprising a proximal layer and a distal layer; a link arm having a first end and a second end, wherein a second aperture is disposed in the link arm at the first end, the link arm configured to rotate about the second aperture; and a fitting arrangement for the link arm comprising: a pivot extending through the second aperture; a base member attached to the proximal layer; and a retaining member at least partially defining a first aperture and a cavity, wherein the pivot is located at least partially within the first aperture, at least a portion of the pivot extends through the second aperture of the link arm, wherein the first end of the link arm is located at least partially within the cavity, wherein the retaining member is substantially flush with the distal layer, and wherein the retaining member defines a first portion of the first aperture and the base member defines a second portion of the first aperture. ### Claim 11 (depends on 10) The nacelle of claim 10, wherein the link arm comprises a thrust reverser link arm. ### Claim 12 (depends on 11) The nacelle of claim 11, wherein the first aperture extends in a direction substantially orthogonal to the cavity. ### Claim 13 (depends on 12) The nacelle of claim 12, wherein the retaining member retains the link arm to the base member. ### Claim 14 (depends on 10) The nacelle of claim 10, wherein a distal surface of the distal layer at least partially defines a bypass flow path. ### Claim 15 (depends on 14) The nacelle of claim 14, wherein the base member is attached to the proximal layer of the IFS via an adhesive. ### Claim 16 (depends on 10) The nacelle of claim 10, wherein the pivot is retained within the first aperture in response to the retaining member being fastened to the base member. ### Claim 17 (depends on 10) The nacelle of claim 10, wherein the retaining member comprises an attachment aperture extending substantially orthogonal to the first aperture, the attachment aperture configured to accommodate a fastener for fastening the base member to the retaining member. ### Claim 18 (depends on 10) The nacelle of claim 10, wherein the base member comprises a slot, at least a portion of the first end extending into the slot. ### Claim 19 A method of installing a linkage system to a nacelle comprising: attaching a base member to an inner fixed structure (IFS); placing a pivot at least partially into a second aperture disposed in a link arm; placing the pivot at least partially into a first aperture disposed in a fitting arrangement; positioning the second aperture and the first aperture in concentric alignment; and attaching a retaining member to the base member, the retaining member defining a first portion of the first aperture and defining at least a portion of a cavity, the base member defining a second portion of the first aperture, and at least a portion of the link arm being located within the cavity. ### Claim 20 (depends on 19) The method of claim 19, wherein the method is performed from a bypass flow path of the nacelle.