# US 10,309,309 B2 · Air guiding device and aircraft engine with air guiding device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,309,309 B2 - Document ID: US10309309B2 - Status: Granted - Kind: B2 - Application number: 14/845,704 - Filed: 2015-09-04 - Published: 2016-03-10 - Granted: 2019-06-04 - Earliest claimed: 2014-09-05 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Applicants: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Robert Thies - Web page: https://patentgrep.com/patent/US10309309B2 ## CPC - F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} - B64D 13/02: the air being pressurised - F01D 9/065: {Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids (see also F01D25/16, F01D25/24 and F01D25/26)} - F01D 25/14: Casings modified therefor (double casings F01D25/26) - F02C 6/08: the gas being bled from the gas-turbine compressor - F02C 7/20: Mounting or supporting of plant; Accommodating heat expansion or creep - F02K 3/06: with front fan - Y02T 50/60: Efficient propulsion technologies, e.g. for 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) - 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) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An air guiding device in an aircraft engine, comprising at least one connection device of a core engine shroud with an external wall of a bypass duct of the aircraft engine is provided. At least one first air inlet opening for inflowing air is connected to a connection device or is arranged inside the connection device. ## Claims ### Claim 1 An aircraft engine with air guiding device, comprising: a bypass duct including an external wall; a core engine including a compressor, a combustion chamber and a turbine; a core engine shroud surrounding the core engine and forming an internal wall of the bypass duct; a connection device connecting the core engine shroud with the external wall of the bypass duct, a first air inlet opening positioned in the bypass duct and connected to the core engine for inflowing air from the bypass duct into the core engine, wherein the first air inlet opening is at least one chosen from connected to the connection device and arranged in the connection device; a sealing barrier positioned between the core engine shroud and a casing wall of at least one chosen from the compressor, the combustion chamber and the turbine and sealing the inflowing air entering through the first air inlet opening from other areas internally of the core engine shroud such that the inflowing air is directed to an interior of the core engine. ### Claim 2 (depends on 1) The aircraft engine with air guiding device according to claim 1, wherein the connection device is a strut. ### Claim 3 (depends on 2) The aircraft engine with air guiding device according to claim 2, wherein the strut is arranged at least one chosen from radially and tangentially with respect to the core engine shroud. ### Claim 4 (depends on 3) The aircraft engine with air guiding device according to claim 3, and further comprising a housing at the core engine shroud, wherein the first air inlet opening is arranged in the housing. ### Claim 5 (depends on 4) The aircraft engine with air guiding device according to claim 4, wherein the housing is at least one chosen from a protrusion of the core engine shroud and the strut. ### Claim 6 (depends on 5) The aircraft engine with air guiding device according to claim 5, wherein the first air inlet opening inflows air for cooling at least one chosen from an area of a wall of the turbine, a part of the connection device, an electric device and a bearing housing. ### Claim 7 (depends on 6) The aircraft engine with air guiding device according to claim 6, wherein the inflowing air forms a counter-pressure in a spacial area of bearings of at least one chosen from the turbine and the compressor. ### Claim 8 (depends on 7) The air guiding device according to claim 7, wherein the sealing barrier includes at least one chosen from an elastic ribbon, a circumferential ring, an elastic membrane and a gaiter. ### Claim 9 (depends on 8) The aircraft engine with air guiding device according to claim 8, and further comprising a second air inlet opening arranged inside the bypass duct upstream of the first air inlet opening. ### Claim 10 (depends on 9) The aircraft engine with air guiding device according to claim 9, wherein the inflowing air through at least one chosen from the first air inlet opening and the second air inlet opening suppresses an air flow from an internal area of the aircraft engine into the bypass duct. ### Claim 11 (depends on 1) The aircraft engine with air guiding device according to claim 1, and further comprising a further air inlet device positioned outside of the connection device. ### Claim 12 (depends on 1) The aircraft engine with air guiding device according to claim 1, and further comprising a housing at the core engine shroud, wherein the first air inlet opening is arranged in the housing. ### Claim 13 (depends on 12) The aircraft engine with air guiding device according to claim 12, wherein the housing is at least one chosen from a protrusion of the core engine shroud and a strut of the connection device. ### Claim 14 (depends on 1) The aircraft engine with air guiding device according to claim 1, wherein the first air inlet opening inflows air for cooling at least one chosen from an area of a wall of the turbine, a part of the connection device, an electric device and a bearing housing. ### Claim 15 (depends on 1) The air guiding device according to claim 1, wherein the sealing barrier includes at least one chosen from an elastic ribbon, a circumferential ring, an elastic membrane and a gaiter. ### Claim 16 (depends on 1) The aircraft engine with air guiding device according to claim 1, and further comprising a second air inlet opening arranged inside the bypass duct upstream of the first air inlet opening. ### Claim 17 (depends on 16) The aircraft engine with air guiding device according to claim 16, wherein the inflowing air through at least one chosen from the first air inlet opening and the second air inlet opening suppresses an air flow from an internal area of the aircraft engine into the bypass duct.