# US 11,827,339 B1 · Apparatus for ingesting boundary layer flow for an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,827,339 B1 - Document ID: US11827339B1 - Status: Granted - Kind: B1 - Application number: 18/102,342 - Filed: 2023-01-27 - Granted: 2023-11-28 - Earliest claimed: 2023-01-27 - Assignees: JetZero, Inc. - Applicants: Jetzero, Inc. - Inventors: Mark Allan Page - Web page: https://patentgrep.com/patent/US11827339B1 ## CPC - B64C 21/01: Boundary layer ingestion [BLI] propulsion - B64C 21/06: for sucking (BLI propulsion B64C21/01) - B64C 39/10: All-wing aircraft - B64D 29/00: Power-plant nacelles, fairings or cowlings - B64D 29/04: associated with fuselages - B64C 2039/105: {of blended wing body type} - B64D 2033/0226: {comprising boundary layer control means} - Y02T 50/10: Drag reduction - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct. ## Claims ### Claim 1 An apparatus for ingesting boundary layer flow on an aircraft, wherein the apparatus comprises: a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft; a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle further comprises: a propulsor configured to propel the aircraft; and a primary duct, wherein the primary duct is configured to intake an airflow from a forward portion of the nacelle to a rear portion of the nacelle; and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further comprises: a secondary duct, wherein the secondary duct is configured to ingest the boundary layer flow in the airflow from an inlet proximal to the forward portion of the nacelle to an outlet proximal to the rear portion of the nacelle; and a tertiary duct connecting the primary duct to the secondary duct, wherein the tertiary duct comprises a converging-divergent duct. ### Claim 2 (depends on 1) The apparatus of claim 1, wherein the blended wing body further comprises: an outer mold line, wherein the outer mold line comprises a depression. ### Claim 3 (depends on 1) The apparatus of claim 1, wherein the propulsor comprises a turbofan engine. ### Claim 4 (depends on 1) The apparatus of claim 1, wherein the primary duct is further configured to intake a uniform inlet flow. ### Claim 5 (depends on 2) The apparatus of claim 2, wherein the secondary duct is located below the primary duct within the depression in the outer mold line. ### Claim 6 (depends on 1) The apparatus of claim 1, wherein the secondary duct is further configured to: route the boundary layer flow around the nacelle; and exhaust the boundary layer flow from the rear portion of the nacelle. ### Claim 7 (depends on 1) The apparatus of claim 1, wherein the secondary duct is further configured to prevent the boundary layer flow from entering an input of the propulsor. ### Claim 8 (depends on 1) The apparatus of claim 1, wherein the secondary duct is further configured to prevent a turbulent spillage from entering the primary duct. ### Claim 9 (depends on 1) The apparatus of claim 1, wherein the tertiary duct is further configured to intake airflow from the primary duct to the secondary duct. ### Claim 10 (depends on 9) The apparatus of claim 9, wherein the tertiary duct is further configured to intake airflow from the secondary duct to the primary duct. ### Claim 11 (depends on 1) The apparatus of claim 1, wherein the tertiary duct comprises a venturi pump. ### Claim 12 (depends on 1) The apparatus of claim 1, wherein the venturi pump comprises a venturi tube. ### Claim 13 (depends on 1) The apparatus of claim 1, wherein the tertiary duct comprises an extended section located within the secondary duct. ### Claim 14 (depends on 13) The apparatus of claim 13, wherein the extended section comprises a tertiary duct nozzle. ### Claim 15 (depends on 14) The apparatus of claim 14, wherein the at least one tertiary duct nozzle comprises a nozzle angle. ### Claim 16 (depends on 1) The apparatus of claim 1, wherein the flow augmentation arrangement is further configured to: mix a high-pressure airflow from the primary duct with the boundary layer flow within the secondary duct; and generate a suction in the secondary duct. ### Claim 17 (depends on 1) The apparatus of claim 1, wherein the flow augmentation arrangement is further configured to: mix ingested boundary layer flow from the secondary duct with a high-pressure airflow within the primary duct; and generate an additional thrust in the primary duct. ### Claim 18 (depends on 17) The apparatus of claim 17, wherein the secondary duct is further configured to ingest the boundary layer flow as a function of a suction. ### Claim 19 (depends on 18) The apparatus of claim 18, wherein propulsor is further configured to propel the aircraft as a function of the airflow and ingested boundary layer flow.