# US 12,006,891 B2 · Propulsor wing trailing edge exhaust area control > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,891 B2 - Document ID: US12006891B2 - Status: Granted - Kind: B2 - Application number: 17/679,540 - Filed: 2022-02-24 - Published: 2022-11-03 - Granted: 2024-06-11 - Earliest claimed: 2021-03-03 - Assignees: Whisper Aero Inc. - Applicants: Whisper Aero Inc. - Inventors: Mark Douglass Moore; Ian Andreas Villa; Devon Jedamski - Web page: https://patentgrep.com/patent/US12006891B2 ## CPC - F02K 1/08: by axially moving or transversely deforming an internal member, e.g. the exhaust cone - F02K 1/1207: {of one series of flaps hinged at their upstream ends on a fixed structure (F02K1/1215 - F02K1/1292 take precedence)} - B64C 15/02: the jets being propulsion jets - B64D 33/04: of exhaust outlets or jet pipes - F05D 2220/323: for aircraft propulsion, e.g. jet engines - F05D 2240/128: Nozzles - F05D 2250/12: rectangular - F05D 2250/141: circular - F05D 2260/57: using servos, independent actuators, etc. - 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) - 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 - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A propulsor system comprising a propulsor and an exhaust area control mechanism are described. The exhaust area control mechanism is connected to an outlet of the propulsor and is configured to vary the area through which air exits the propulsor system. ## Claims ### Claim 1 An exhaust control system comprising: a tail cone configured to be directly connected to a stator of a propulsor fan, the tail cone including: a first end of the tail cone having a plurality of concentric rings including a first ring and a second ring, the first ring including a first end that is configured to connect to the stator of the propulsor fan and a second end that is opposite the first end of the first ring, and the second ring including a first end that overlaps the second end of the first ring such that the second end of the first ring is inserted into the first end of the second ring and a second end of the second ring; a second end of the tail cone that is opposite the first end; and an intermediate portion having an end and the second end of the second ring is inserted into the end of the intermediate portion, and the intermediate portion is disposed between the second end of the second ring and the second end of the tail cone, the intermediate portion having a diameter that is greater than a diameter of the first end of the tail cone and a diameter of the second end of the tail cone; and an exhaust area control mechanism configured to adjust an amount of overlap between the second end of the first ring and the first end of the second ring of the tail cone and adjust an amount of overlap between the second end of the second ring and the intermediate portion of the tail cone to adjust a length of the tail cone such that a position of the intermediate portion within an outlet of the propulsor fan changes thereby varying an area of the outlet of the propulsor fan. ### Claim 2 (depends on 1) The exhaust control system of claim 1, wherein the exhaust area control mechanism is connected to the second end of the tail cone. ### Claim 3 (depends on 2) The exhaust control system of claim 2, wherein the exhaust area control mechanism is configured to increase the amount of overlap between the plurality of concentric rings to reduce the length of the tail cone such that the intermediate portion is closer to the first end thereby increasing the area of the outlet of the propulsor fan to increase thrust. ### Claim 4 (depends on 3) The exhaust control system of claim 3, wherein the exhaust area control mechanism is configured to decrease the amount of overlap between the plurality of concentric rings to increase the length of the tail cone such that the intermediate portion is farther from the first end thereby decreasing the area of the outlet of the propulsor fan to decrease thrust. ### Claim 5 A propulsor system comprising: a propulsor fan configured to generate thrust, the propulsor fan including: a stator; and a tail cone configured to be connected to the stator, the tail cone including: a first end of the tail cone having a plurality of concentric rings including a first ring and a second ring, the first ring including a first end that is configured to connect to the stator of the propulsor fan and a second end that is opposite the first end of the first ring, and the second ring including a first end that overlaps the second end of the first ring such that the second end of the first ring is inserted into the first end of the second ring and a second end of the second ring; a second end of the tail cone that is opposite the first end; and an intermediate portion having an end and the second end of the second ring is inserted into the end of the intermediate portion, and the intermediate portion is disposed between the second end of the second ring and the second end of the tail cone, the intermediate portion having a diameter that is greater than a diameter of the first end of the tail cone and a diameter of the second end of the tail cone; and an exhaust area control mechanism configured to adjust an amount of overlap between the second end of the first ring and the first end of the second ring of the tail cone and adjust an amount of overlap between the second end of the second ring and the intermediate portion of the tail cone to adjust a length of the tail cone such that a position of the intermediate portion within an outlet of the propulsor fan changes thereby varying an area of the outlet of the propulsor fan. ### Claim 6 (depends on 4) The exhaust control system of claim 4, wherein a minimum area of the outlet of the propulsor fan corresponds to a first position of a part of the intermediate portion having a maximum diameter being aligned with a trailing edge of the outlet of the propulsor fan and a maximum area of the outlet of the propulsor fan corresponds to a second position of the part of the intermediate portion being inset from the trailing edge of the outlet of the propulsor fan while a maximum amount of overlap is between the plurality of concentric rings. ### Claim 7 (depends on 5) The propulsor system of claim 5, wherein the exhaust area control mechanism is connected to the second end of the tail cone. ### Claim 8 (depends on 7) The propulsor system of claim 7, wherein the exhaust area control mechanism is configured to increase the amount of overlap between the plurality of concentric rings to reduce the length of the tail cone such that the intermediate portion is closer to the first end thereby increasing the area of the outlet of the propulsor fan to increase thrust. ### Claim 9 (depends on 8) The propulsor system of claim 8, wherein the exhaust area control mechanism is configured to decrease the amount of overlap between the plurality of concentric rings to increase the length of the tail cone such that the intermediate portion is farther from the first end thereby decreasing the area of the outlet of the propulsor fan to decrease thrust. ### Claim 10 (depends on 9) The propulsor system of claim 9, wherein a minimum area of the outlet of the propulsor fan corresponds to a first position of a part of the intermediate portion having a maximum diameter being aligned with a trailing edge of the outlet of the propulsor fan and a maximum area of the outlet of the propulsor fan corresponds to a second position of the part of the intermediate portion being inset from the trailing edge of the outlet of the propulsor fan while a maximum amount of overlap is between the plurality of concentric rings.