# US 2019/0168883 A1 · Integrated support structure for an aircraft engine and its auxillary components > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0168883 A1 - Document ID: US20190168883A1 - Status: Published application - Kind: A1 - Application number: 16/210,919 - Filed: 2018-12-05 - Published: 2019-06-06 - Earliest claimed: 2017-12-06 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Applicants: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Carsten BUCHHOLZ - Web page: https://patentgrep.com/patent/US20190168883A1 ## CPC - F01D 25/28: Supporting or mounting arrangements, e.g. for turbine casing - B64C 1/16: specially adapted for mounting power plant - B64D 27/14: within, or attached to, fuselages - B64D 27/20: within, or attached to, fuselages - B64D 27/402: {comprising box like supporting frames, e.g. pylons or arrangements for embracing the power plant} - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F05D 2240/90: Mounting on supporting structures or systems - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B64C: AEROPLANES; HELICOPTERS - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A supporting structure arrangement for fastening an aircraft gas turbine engine to an aircraft, including: a supporting structural element of the aircraft engine and a supporting structure with at least one support and at least one bearing, by means of which the support can be connected or is connected to the aircraft, wherein the support can be connected or is connected rigidly to the supporting structural element of the aircraft engine by means of a connecting device. ## Claims ### Claim 1 A supporting structure arrangement for fastening an aircraft gas turbine engine to an aircraft, comprising: a supporting structural element of the aircraft engine and a supporting structure with at least one support and at least one bearing, by means of which the support can be connected or is connected to the aircraft, wherein the support can be connected or is connected rigidly to the supporting structural element of the aircraft engine by means of a connecting device. ### Claim 2 (depends on 1) The supporting structure arrangement according to claim 1, wherein the supporting structural element is at least part of a casing or at least part of a core engine case. ### Claim 3 (depends on 1) The supporting structure arrangement according to claim 1, wherein at least two bearings are provided, each bearing having at least one degree of freedom. ### Claim 4 (depends on 1) The supporting structure arrangement according to claim 1, wherein the at least one support has at least two bearings for connecting the support to the aircraft, the distance of which from one another is greater than the minimum diameter of the supporting structure between the aircraft engine and the aircraft in a direction parallel to the direct connecting line between the at least two bearings. ### Claim 5 (depends on 1) The supporting structure arrangement according to claim 1, characterized by at least two spaced-apart supports of the supporting structure. ### Claim 6 (depends on 5) The supporting structure arrangement according to claim 5, wherein, with the supports connected to the aircraft engine, the at least one bearing of one of the at least two supports is/are at a distance from the at least one bearing of another of the at least two supports that is greater than a length of a core engine and/or a casing of the aircraft engine. ### Claim 7 (depends on 5) The supporting structure arrangement according to claim 5, wherein at least one accessory component of the aircraft engine is arranged between the at least two axially spaced-apart supports of the supporting structure. ### Claim 8 (depends on 7) The supporting structure arrangement according to claim 7, wherein at least one accessory component comprises a gearbox, an arrangement of lines, a supply device and/or a control computer. ### Claim 9 (depends on 7) The supporting structure arrangement according to claim 7, characterized by an installation frame, which is arranged between the at least the two axially spaced-apart supports of the supporting structure and to which the at least one accessory component is fastened. ### Claim 10 (depends on 9) The supporting structure arrangement according to claim 9, characterized by at least one shock absorber, by means of which the installation frame is mounted or can be mounted on the aircraft engine, on the fastening device and/or on the aircraft. ### Claim 11 (depends on 1) The supporting structure arrangement according to claim 1, wherein the bearing comprises a shock absorber and/or an elastic element, which, in the state in which it is connected to the aircraft, is arranged in the load path. ### Claim 12 (depends on 1) An aircraft with a fuselage and at least one aircraft gas turbine engine, characterized by a supporting structure arrangement according to claim 1, the aircraft engine being fastened by means of the supporting structure of the supporting structure arrangement to the fuselage of the aircraft. ### Claim 13 (depends on 12) The aircraft according to claim 12, wherein the bearing comprises at least one fastening point, which is fixedly connected to the fuselage of the aircraft and which is arranged in a pocket set back from an outer shell of the fuselage of the aircraft. ### Claim 14 (depends on 1) A method for producing a supporting structure arrangement according to claim 1 with at least two spaced-apart supports of the supporting structure, wherein, by means of optimization of the topology, at least one out of a distance between the supports, a height of each of the supports and a relative material distribution of the supports is determined.