# US 10,370,113 B2 · Flow drag mitigation device > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,370,113 B2 - Document ID: US10370113B2 - Status: Granted - Kind: B2 - Application number: 15/328,022 - Filed: 2015-07-23 - Published: 2017-07-06 - Granted: 2019-08-06 - Earliest claimed: 2014-07-23 - Assignees: Shield Aerodynamics LLC - Applicants: Shield Aerodynamics LLC - Inventors: Dennis Snyder; Wayne Duncan - Web page: https://patentgrep.com/patent/US10370113B2 ## CPC - B64D 33/02: of combustion air intakes - B64C 7/02: Nacelles - B64C 21/10: using other surface properties, e.g. roughness - B64D 15/00: De-icing or preventing icing on exterior surfaces of aircraft - B64D 29/00: Power-plant nacelles, fairings or cowlings - B64D 29/06: Attaching of nacelles, fairings or cowlings - F04D 29/522: {especially adapted for elastic fluid pumps} - B64D 2033/0206: {comprising noise reduction means, e.g. acoustic liners} - B64D 2033/0226: {comprising boundary layer control means} - B64D 2033/0233: {comprising de-icing means} - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64C: AEROPLANES; HELICOPTERS - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) ## Abstract A mitigating system for reducing flow drag in aircraft engines uses a mitigating device attached to either the nacelle of an engine to mitigate the flow drag of the airflow moving across the nacelle. The mitigating device has an inner sleeve and an outer sleeve, each of which can be adjusted separately to extend any desired length across the inner surface or outer surface of the nacelle. As the sleeves are extended, they cover a greater number of flow drag elements thereby improving the aerodynamic properties of the aircraft engine. ## Claims ### Claim 1 A system for mitigating flow drag caused by airflow over a jet engine surface comprising: a. a housing having a first end and a second end, wherein said airflow moves from said first end of said housing toward said second end of said housing, further wherein said housing comprises flow drag elements, wherein said flow drag elements comprise a nose cowl having a first end and a second end and an inner surface and an outer surface, a fan cowl having a first end and a second end and an inner surface and an outer surface, and a lipskin having a lipskin leading edge and a second end and an inner surface and an outer surface; b. a first plurality of fasteners, wherein said first plurality of fasteners connects said second end of said lipskin to said first end of said nose cowl thereby creating a first joint, wherein said first plurality of fasteners is located at said second end of said lipskin; c. a second plurality of fasteners, wherein said second plurality of fasteners connects said second end of said lipskin to said first end of said nose cowl, wherein said second plurality of fasteners is located at said first end of said nose cowl; d. a third plurality of fasteners, wherein said third plurality of fasteners connects said second end of said nose cowl to said first end of said fan cowl thereby causing a cowl interface having a nose cowl side and a fan cowl side thereby creating a second joint, wherein said third plurality of fasteners is located on said nose cowl side of said cowl interface; e. a fourth plurality of fasteners, wherein said fourth plurality of fasteners connects said second end of said nose cowl to said first end of said fan, wherein said fourth plurality of fasteners is located on said fan cowl side of said cowl interface; and f. a mitigating device having an outer sleeve, wherein said outer sleeve has a first end and a second end, wherein said mitigating device is connected to said housing, further wherein said mitigating device directs said airflow over said flow drag elements thereby reducing flow drag caused by said flow drag elements. ### Claim 2 (depends on 1) The system of claim 1, wherein said mitigating device further comprises an inner sleeve having a first end and a second end. ### Claim 3 (depends on 2) The system of claim 2, wherein said second end of said inner sleeve of said mitigating device extends to a point on said inner surface of said lipskin before said second end of said lipskin. ### Claim 4 (depends on 2) The system of claim 2, wherein said second end of said inner sleeve of said mitigating device extends over said second end of said lipskin thereby covering at least a portion of said inner surface of said lipskin. ### Claim 5 (depends on 4) The system of claim 4, further wherein said second end of said inner sleeve of said mitigating device extends over said first joint thereby covering said first joint. ### Claim 6 (depends on 2) The system of claim 2, wherein said inner sleeve of said mitigating device comprises acoustic absorbing surfaces. ### Claim 7 (depends on 1) The system of claim 1, wherein said mitigating device is connected to said lipskin leading edge, wherein said second end of said outer sleeve of said mitigating device extends to a point on said outer surface of said lipskin before said second end of said lipskin. ### Claim 8 (depends on 1) The system of claim 1, wherein said second end of said outer sleeve of said mitigating device extends over said second end of said lipskin thereby covering at least a portion of said outer surface of said lipskin and covering at least a portion of said first plurality of fasteners. ### Claim 9 (depends on 8) The system of claim 8, further wherein said second end of said outer sleeve of said mitigating device extends over said first joint thereby covering said first joint. ### Claim 10 (depends on 9) The system of claim 9, further wherein said second end of said outer sleeve of said mitigating device extends over said first end of said nose cowl to a point on said outer surface of said nose cowl before said second end of said nose cowl thereby covering a portion of said outer surface of said nose cowl and thereby covering said second plurality of fasteners. ### Claim 11 (depends on 10) The system of claim 10, further wherein said second end of said outer sleeve of said mitigating device extends over said second end of said nose cowl thereby covering said outer surface of said nose cowl and thereby covering said third plurality of fasteners. ### Claim 12 (depends on 1) The system of claim 1, wherein said outer sleeve of said mitigating device comprises acoustic absorbing surfaces. ### Claim 13 (depends on 1) The system of claim 1, further comprising an outside device attached to said first end of said mitigating device. ### Claim 14 (depends on 1) The system of claim 1 wherein said housing is a nacelle. ### Claim 15 (depends on 1) The system of claim 1, wherein said mitigating device comprises an anti-icing device. ### Claim 16 A mitigation device for reducing drag on an aircraft surface, the mitigation device comprising: a. an outer sleeve, wherein said outer sleeve has a first end and a second end; b. an inner sleeve having a first and second end, wherein said mitigating device is attached to said aircraft surface and wherein said mitigating device comprises a smooth mitigation device surface such that it directs airflow over said aircraft surface thereby reducing flow drag caused by flow drag elements of said aircraft surface, wherein said aircraft surface is a lipskin comprising an inner surface and an outer surface and a first and second end, and wherein said second end of said outer sleeve of said mitigating device extends to a point on said outer surface of said lipskin before said second end of said lipskin, further wherein said second end of said inner sleeve of said mitigating device extends to a point on said inner surface of said lipskin before said second end of said lipskin, further wherein said second end of said outer sleeve of said mitigating device extends over said second end of said lipskin thereby covering at least a portion of said outer surface of said lipskin, further wherein said second end of said inner sleeve of said mitigating device extends over said second end of said lipskin thereby covering at least a portion of said inner surface of said lipskin, and further wherein said aircraft surface further comprises a nose cowl comprising a first end and a second end and connected to the lipskin and defining a first joint therebetween, further wherein said second end of said outer sleeve of said mitigating device extends over said first joint thereby covering said first joint. ### Claim 17 (depends on 16) The mitigation device of claim 16, further wherein said second end of said inner sleeve of said mitigating device extends over said first joint thereby covering said first joint. ### Claim 18 (depends on 17) The mitigation device of claim 17, further wherein said second end of said outer sleeve of said mitigating device extends over said first end of said nose cowl to a point on said outer surface of said nose cowl before said second end of said nose cowl thereby covering a portion of said outer surface of said nose cowl. ### Claim 19 (depends on 18) The mitigation device of claim 18, further wherein said second end of said outer sleeve of said mitigating device extends over said second end of said nose cowl thereby covering said outer surface of said nose cowl.