# US 10,501,196 B2 · Nacelle for an aircraft aft fan > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,501,196 B2 - Document ID: US10501196B2 - Status: Granted - Kind: B2 - Application number: 15/281,990 - Filed: 2016-09-30 - Published: 2018-04-05 - Granted: 2019-12-10 - Earliest claimed: 2016-09-30 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Kishore Ramakrishnan; Patrick Michael Marrinan - Web page: https://patentgrep.com/patent/US10501196B2 ## CPC - B64D 29/04: associated with fuselages - B64D 27/08: within, or attached to, fuselages - B64D 27/14: within, or attached to, fuselages - B64D 27/18: within, or attached to, wings - B64D 27/20: within, or attached to, fuselages - B64D 27/32: within, or attached to, fuselages - B64D 27/33: Hybrid electric aircraft - B64D 35/023: of series-parallel type - B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)} - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An aircraft includes a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage, the aft engine defining a centerline. The aft engine further includes a nacelle having a bottom section, the bottom section having a forward lip. The forward lip of the bottom section defines a camber line. The camber line, in turn, defines an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees. ## Claims ### Claim 1 An aircraft defining a longitudinal direction and comprising: a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft; and an aft engine mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line of the forward lip defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; wherein the nacelle of the aft engine further includes a body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein the camber line of the forward lip is a best fit linear camber line for a forward ten percent of the bottom section of the nacelle. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the camber line of the forward lip defines an angle relative to the centerline of the aft engine greater than or equal to at least about ten degrees. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein the fuselage defines a bottom side having a slanted surface extending towards the aft engine, wherein the slanted surface of the bottom side of the fuselage extends in a first direction, and wherein the camber line of the forward lip is within about ten degrees of being parallel to the first direction. ### Claim 5 (depends on 1) The aircraft of claim 1, wherein the fuselage defines a bottom side having a slanted surface extending towards the aft engine, wherein the slanted surface of the bottom side of the fuselage extends in a first direction, and wherein the camber line of the forward lip defines an angle with the first direction between about five degrees and about fifteen degrees. ### Claim 6 (depends on 1) The aircraft of claim 1, wherein the nacelle further comprises a top section, wherein the bottom section of the nacelle defines a forward edge at the forward lip, wherein the top section of the nacelle defines a forward edge, wherein the forward edge of top section is positioned farther forward than a forward edge of the bottom section along the longitudinal direction and defines a reference line extending therebetween, and wherein the reference line defines an angle with the centerline of the aft engine less than about eighty-five degrees. ### Claim 7 (depends on 1) The aircraft of claim 1, further comprising: a gas turbine engine; and an electric generator driven by the gas turbine engine, wherein the aft engine is an electric fan powered by the electric generator. ### Claim 8 (depends on 1) The aircraft of claim 1, wherein the aft engine is a boundary layer ingestion fan. ### Claim 9 (depends on 1) The aircraft of claim 1, wherein the nacelle defines an inlet having a top half positioned above the centerline and a bottom half positioned below the centerline, wherein the top half of the inlet defines a top half inlet area, wherein the bottom half of the inlet defines a bottom half inlet area, and wherein the bottom half inlet area is greater than the top half inlet area. ### Claim 10 (depends on 1) The aircraft of claim 1, wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line of the forward lip is at least about five percent of the length of the camber line of the body portion of the bottom section. ### Claim 11 (depends on 1) The aircraft of claim 1, wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line for the forward lip is at least about ten percent of the length of the camber line of the body portion of the bottom section. ### Claim 12 (depends on 1) The aircraft of claim 1, wherein the aircraft defines a vertical direction, and wherein the forward lip of the bottom section is oriented downwardly along the vertical direction. ### Claim 13 A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising: an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; wherein the nacelle of the aft engine further includes a body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion. ### Claim 14 (depends on 13) The propulsion system of claim 13, wherein the camber line of the forward lip defines an angle relative to the centerline of the aft engine greater than or equal to at least about ten degrees. ### Claim 15 (depends on 13) The propulsion system of claim 13, wherein the nacelle of the aft engine further includes the body portion, wherein the nacelle of the aft engine defines an outer surface, wherein the outer surface of the nacelle includes a concave shape between the forward lip of bottom section and the body portion. ### Claim 16 (depends on 13) The propulsion system of claim 13, wherein the nacelle further comprises a top section, wherein the bottom section of the nacelle defines a forward edge at the forward lip, wherein the top section of the nacelle defines a forward edge, wherein the forward edge of top section is positioned farther forward than a forward edge of the bottom section along the longitudinal direction and defines a reference line extending therebetween, and wherein the reference line defines an angle with the centerline of the aft engine less than about eighty-five degrees. ### Claim 17 (depends on 13) The propulsion system of claim 13, further comprising: a gas turbine engine; and an electric generator driven by the gas turbine engine, wherein the aft engine is an electric fan powered by the electric generator. ### Claim 18 (depends on 13) The propulsion system of claim 13, wherein the aft engine is a boundary layer ingestion fan. ### Claim 19 (depends on 13) The propulsion system of claim 13, wherein the bottom section of the nacelle further comprises the body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line of the forward lip is at least about five percent of the length of the camber line of the body portion of the bottom section. ### Claim 20 A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising: an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; and one or more structural members extending between the nacelle and the fuselage, the one or more structural members comprising one or more inlet guide vanes, the one or more inlet guide vanes further comprising: a body portion that is fixed relative to the nacelle; and at least one tail flap, the at least one tail flap configured to rotate about a substantially radial axis. ### Claim 21 A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising: an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; wherein the nacelle further comprises a top section, wherein the bottom section of the nacelle defines a forward edge at the forward lip, wherein the top section of the nacelle defines a forward edge, wherein the forward edge of top section is positioned farther forward than a forward edge of the bottom section along the longitudinal direction and defines a reference line extending therebetween, and wherein the reference line defines an angle with the centerline of the aft engine less than about eighty-five degrees. ### Claim 22 A propulsion system for an aircraft, the aircraft comprising a fuselage defining an aft end, the propulsion system comprising: an aft engine configured to be mounted to the aft end of the fuselage and defining a centerline, the aft engine further comprising a nacelle including a bottom section having a forward lip, the forward lip defining a camber line and the camber line defining an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees; wherein the bottom section of the nacelle further comprises a body portion extending from the forward lip to an aft edge, wherein the body section defines a camber line, and wherein a length of the camber line of the forward lip is at least about five percent of the length of the camber line of the body portion of the bottom section.