# US 11,077,955 B2 · Jet engine with a linking device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,077,955 B2 - Document ID: US11077955B2 - Status: Granted - Kind: B2 - Application number: 16/159,076 - Filed: 2018-10-12 - Published: 2019-04-18 - Granted: 2021-08-03 - Earliest claimed: 2017-10-16 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Applicants: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Gideon Daniel Venter; Michael Schacht - Web page: https://patentgrep.com/patent/US11077955B2 ## CPC - 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} - B64D 41/00: Power installations for auxiliary purposes - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02C 7/32: Arrangement, mounting, or driving, of auxiliaries - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/90: Mounting on supporting structures or systems - 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 jet engine with a linking device for linking the jet engine at an element of an aircraft optionally in a first mounting position and at least one second mounting position, and with at least one operating equipment appliance that has a first fluid area and a second fluid area. In the first mounting position, the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality. In the second mounting position, the fluid areas are assigned to the respectively other functionality. What is further described is an aircraft with at least one such jet engine. ## Claims ### Claim 1 A jet engine comprising: an attachment member for linking the jet engine at an element of an aircraft in a first mounting position and a second mounting position, an operating equipment appliance which has a first fluid area and a second fluid area for connect to the aircraft, wherein, in the first mounting position the first fluid area is assigned to a first functionality and the second fluid area is assigned to a second functionality, wherein, in the second mounting position, the first fluid area is assigned to the second functionality and the second fluid area is assigned to the first functionality. ### Claim 2 (depends on 1) The jet engine according to claim 1, wherein the fluid areas are assigned to re-circulation and venting as functionalities. ### Claim 3 (depends on 1) The jet engine according to claim 1, wherein the fluid areas have conduit areas that are arranged at a distance to each other in a circumferential direction of the jet engine, wherein the conduit areas are arranged so as to be symmetrical to the attachment member in the circumferential direction of the jet engine. ### Claim 4 (depends on 1) The jet engine according to claim 1, wherein the attachment member includes two engine attachment points, wherein the attachment member is connected to a carrier structure of the jet engine in an area of the engine attachment points. ### Claim 5 (depends on 4) The jet engine according to claim 4, wherein the attachment member comprises an interface device to the aircraft positioned centrally to the two engine attachment points in the circumferential direction. ### Claim 6 (depends on 1) The jet engine according to claim 1, and further comprising two lifting points configured for mounting the jet engine distributed in a circumferential direction of the jet engine, wherein the lifting points are arranged to be symmetrical to the interface device in the circumferential direction. ### Claim 7 (depends on 1) The jet engine according to claim 1, and further comprising a support strut extending in a radial direction through a bypass channel of the jet engine, wherein the fluid areas extend inside the support strut. ### Claim 8 (depends on 1) The aircraft with a jet engine according to claim 1, and further comprising a radially outer engine cladding and an auxiliary device gear appliance that comprises multiple auxiliary devices and that is configured to be driven by an auxiliary shaft that is in operative connection with an engine shaft that rotates about a central axis, wherein the auxiliary device gear appliance is arranged in a radial direction of the jet engine substantially outside the outer engine cladding of the jet engine. ### Claim 9 (depends on 8) The aircraft according to claim 8, wherein the auxiliary device gear appliance is linked to a frame appliance that is directly connected to at least one chosen from an aircraft fuselage and an aircraft wing. ### Claim 10 (depends on 9) The aircraft according to claim 9, wherein the frame appliance is arranged at least partially inside an engine pylon that is assigned to the jet engine. ### Claim 11 (depends on 9) The aircraft according to claim 9, wherein the frame appliance has linking elements for at least one chosen from the auxiliary devices, a conduit, a tube and a wiring harness. ### Claim 12 (depends on 8) The aircraft according to claim 8, wherein the auxiliary device gear appliance is arranged at least partially inside at least one chosen from an aircraft fuselage, an engine pylon and an aircraft wing. ### Claim 13 (depends on 12) The aircraft according to claim 12, wherein the auxiliary shaft that drives the auxiliary device gear appliance extends through a support strut of the jet engine, with the jet engine being linked to the at least one chosen from the aircraft fuselage, the engine pylon, and the aircraft wing in an area of the support strut.