# US 10,246,196 B2 · Aircraft engine assembly comprising at least two rear engine attachments axially shifted from each other > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,246,196 B2 - Document ID: US10246196B2 - Status: Granted - Kind: B2 - Application number: 15/285,211 - Filed: 2016-10-04 - Published: 2017-04-06 - Granted: 2019-04-02 - Earliest claimed: 2015-10-05 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations (S.A.S.) - Inventors: Olivier Pautis; Wolfgang Brochard - Web page: https://patentgrep.com/patent/US10246196B2 ## CPC - B64D 27/404: {Suspension arrangements specially adapted for supporting vertical loads} - B64D 27/18: within, or attached to, wings - B64D 27/406: {Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links} - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02K 1/08: by axially moving or transversely deforming an internal member, e.g. the exhaust cone - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - 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) ## Abstract In order to reduce the width of the attachment between the rear portion of an aircraft engine and its attachment pylon, an engine assembly attachment include an assembly of rear engine attachments comprising a first connecting rod laid out in a longitudinal and median vertical plane, a second connecting rod substantially laid out tangentially to the inter-turbine case, and a rear engine attachment for transversely spreading the loads, axially shifted rearwards relatively to the first and second connecting rods, and comprising a shear pin oriented along a vertical direction of the engine assembly. ## Claims ### Claim 1 An aircraft engine assembly comprising: a dual-body engine comprising an inter-turbine casing; a pylon for mounting the engine on a structure of the aircraft, the pylon including a primary structure; a mount for mounting the engine on the primary structure of the mounting pylon; the mount comprising a rear engine attachment assembly comprising: a first connecting rod articulated at one end with a bracket rigidly connected to the inter-turbine casing and articulated at another end with a bracket rigidly connected to the primary structure of the pylon, the first connecting rod being arranged in a median vertical and longitudinal plane; a second connecting rod articulated at one end with a bracket rigidly connected to the inter-turbine casing and articulated at another end with a bracket rigidly connected to the primary structure of the pylon, the second connecting rod being arranged substantially tangential to the inter-turbine casing; and a rear engine attachment for transverse force spreading, shifted axially backwards in relation to the first and second connecting rods, and including a shear pin oriented in a vertical direction of the engine assembly and rigidly connected to either the engine or the primary structure, as well as a seating bracket for the shear pin that is rigidly connected to another of the engine or the primary structure and that has a seating orifice for the shear pin, the shear pin being seated in the seating orifice with a clearance in the longitudinal direction of the engine assembly. ### Claim 2 (depends on 1) The engine assembly according to claim 1, wherein the first and second connecting rods are arranged in a same transverse plane of the engine assembly. ### Claim 3 (depends on 1) The engine assembly according to claim 1, wherein the first and second connecting rods are arranged respectively in two different transverse planes of the engine assembly. ### Claim 4 (depends on 3) The engine assembly according to claim 3, wherein, when viewed axially, the first and second connecting rods cross one another. ### Claim 5 (depends on 1) The engine assembly according to claim 1, wherein each of the first and second connecting rods is associated with an emergency connecting rod that is only stressed in an event of a connecting rod suffering an accident. ### Claim 6 (depends on 1) The engine assembly according to claim 1, wherein the shear pin is seated movably in vertical translation in the seating orifice, and wherein a free end of the shear pin is provided with a vertical stopping member arranged vertically distant from a complementary stopping member rigidly connected to the primary structure. ### Claim 7 (depends on 6) The engine assembly according to claim 6, wherein the primary structure of the mounting pylon is in a form of a box fitted with a lower longeron, wherein the vertical stopping member is positioned inside the box, and wherein the complementary stopping member is formed by the lower longeron. ### Claim 8 (depends on 1) The engine assembly according to claim 1, wherein the rear engine attachment for transverse force spreading is positioned on an exhaust casing of the engine. ### Claim 9 (depends on 1) The engine assembly according to claim 1, wherein the shear pin is rigidly connected to the engine. ### Claim 10 (depends on 1) The engine assembly according to claim 1, wherein the shear pin comprises: a base; a vertical shaft rigidly connected to the base; a male ball-joint element formed on the vertical shaft; an outer bearing member inside the seating orifice, the outer member having an inner surface defining a female ball-joint element cooperating with the male element. ### Claim 11 (depends on 1) The engine assembly according to claim 1, wherein the mount also comprises a front engine attachment, as well as a thrust spreading device oriented in a longitudinal direction of the engine assembly. ### Claim 12 (depends on 11) The engine assembly according to claim 11, wherein the rear engine attachment, the front engine attachment and the thrust spreading device make up the mount of the engine, forming an isostatic force-spreading system. ### Claim 13 (depends on 11) The engine assembly according to claim 11, wherein the thrust spreading device comprises: a supporting element attached to the primary structure; two thrust-spreading lateral link rods; and a swing bar articulated with the supporting element, both lateral link rods being articulated with two opposite ends of the swing bar, respectively. ### Claim 14 (depends on 13) The engine assembly according to claim 13, wherein the supporting element is positioned in front of the first and second connecting rods. ### Claim 15 (depends on 1) An aircraft including at least one engine assembly according to claim 1.