Patents by Inventor Justin H. Lan
Justin H. Lan has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11964752Abstract: There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.Type: GrantFiled: April 21, 2022Date of Patent: April 23, 2024Assignee: The Boeing CompanyInventors: Navid Daneshvaran, Justin H. Lan, Takao Suzuki, Deric A. Babcock, Jordan R. Kreitzman, Eric H. Nesbitt
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Publication number: 20220380026Abstract: There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.Type: ApplicationFiled: April 21, 2022Publication date: December 1, 2022Inventors: Navid Daneshvaran, Justin H. Lan, Takao Suzuki, Deric A. Babcock, Jordan R. Kreitzman, Eric H. Nesbitt
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Patent number: 10442523Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.Type: GrantFiled: August 25, 2015Date of Patent: October 15, 2019Assignee: The Boeing CompanyInventors: Vyacheslav Khozikov, Jesse I. Follet, Justin H. Lan, Eric H. Nesbitt
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Patent number: 10364035Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.Type: GrantFiled: August 25, 2015Date of Patent: July 30, 2019Assignee: The Boeing CompanyInventors: Vyacheslav Khozikov, Jesse I. Follet, Justin H. Lan, Eric H. Nesbitt
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Patent number: 9963238Abstract: An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.Type: GrantFiled: January 6, 2017Date of Patent: May 8, 2018Assignee: The Boeing CompanyInventors: Eric H. Nesbitt, Justin H. Lan, Thonse R. S. Bhat, Charles W. Rust
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Patent number: 9771868Abstract: An aircraft engine sound attenuation apparatus includes a perforated face member, a backing member, a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member, and a bulk absorber disposed in each of the plurality of channels, wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine.Type: GrantFiled: July 21, 2015Date of Patent: September 26, 2017Assignee: The Boeing CompanyInventors: Eric H. Nesbitt, Justin H. Lan, Thonse R. S. Bhat, Charles W. Rust
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Publication number: 20170113806Abstract: An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.Type: ApplicationFiled: January 6, 2017Publication date: April 27, 2017Inventors: Eric H. NESBITT, Justin H. LAN, Thonse R.S. BHAT, Charles W. RUST
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Patent number: 9587563Abstract: An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.Type: GrantFiled: July 21, 2015Date of Patent: March 7, 2017Assignee: The Boeing CompanyInventors: Eric H. Nesbitt, Justin H. Lan, Thonse R. S. Bhat, Charles W. Rust
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Publication number: 20170057644Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.Type: ApplicationFiled: August 25, 2015Publication date: March 2, 2017Inventors: Vyacheslav Khozikov, Jesse I. Follet, Justin H. Lan, Eric H. Nesbitt
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Publication number: 20170057618Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.Type: ApplicationFiled: August 25, 2015Publication date: March 2, 2017Inventors: Vyacheslav Khozikov, Jesse I. Follet, Justin H. Lan, Eric H. Nesbitt
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Publication number: 20170022904Abstract: An aircraft auxiliary power unit sound attenuation apparatus includes a perforated body having a center aperture through which exhaust fluid passes, a backing member outwardly offset from the perforated body, a plurality of connecting members coupling the perforated body to the backing member to form a locally reacting sound attenuation member having a plurality of channels spanning outwardly from the perforated body to the backing member, and a bulk absorber disposed in each of the plurality of channels where the bulk absorber is in fluid communication with the exhaust fluid, where the locally reacting sound attenuation member is in fluid communication with an auxiliary power unit of an aircraft so that the plurality of channels are oriented in a direction crossing a pressure drop direction of an exhaust fluid flow passing through the center aperture and each channel circumscribes the center aperture.Type: ApplicationFiled: July 21, 2015Publication date: January 26, 2017Inventors: Eric H. NESBITT, Justin H. LAN, Thonse R.S. BHAT, Charles W. RUST
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Publication number: 20170022903Abstract: An aircraft engine sound attenuation apparatus includes a perforated face member, a backing member, a plurality of connecting members coupling the perforated face member to the backing member to form a plurality of channels spanning from the perforated face member to the backing member, and a bulk absorber disposed in each of the plurality of channels, wherein the plurality of channels are connected to an interior portion of an aircraft engine nacelle component so that the plurality of channels are oriented in a direction substantially normal to a direction of fluid flow pressure drop passing through the aircraft engine.Type: ApplicationFiled: July 21, 2015Publication date: January 26, 2017Inventors: Eric H. NESBITT, Justin H. LAN, Thonse R.S. BHAT, Charles W. RUST
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Patent number: 9168716Abstract: An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic attenuating section.Type: GrantFiled: September 14, 2012Date of Patent: October 27, 2015Assignee: The Boeing CompanyInventors: Brenda Benedetti, Robert S. Farrell, Luis R. Leon, Justin H. Lan, Garry A. Booker
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Publication number: 20140077031Abstract: An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing through the nacelle. The radiused portion may include an acoustic attenuating section.Type: ApplicationFiled: September 14, 2012Publication date: March 20, 2014Applicant: THE BOEING COMPANYInventors: Brenda Benedetti, Robert S. Farrell, Luis R. Leon, Justin H. Lan, Garry A. Booker