Patents by Inventor Chen Chuck
Chen Chuck 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: 11491686Abstract: Compression mold assembly for forming a preform of a cascade includes first and second die elements and an axis of alignment. Line of removal of a formed preform is positioned perpendicular to a plane perpendicular to the axis of alignment. First die portion includes first curved surface forming interior surface of first strong back and second die portion includes first curved surface forming interior surface of a second strong back of a cell of a formed preform. Second die portion includes second curved surface forming an interior surface of a first vane on forward side of the cell of the formed preform and first die portion further includes first wall member which extends along line of removal and a second wall member which extends angularly from first wall portion forming an interior surface of a second vane positioned on an aft side of the cell.Type: GrantFiled: July 22, 2019Date of Patent: November 8, 2022Assignee: THE BOEING COMPANYInventors: Zachariah VanDeMark, David J. Barene, Everette D. Gray, Chen Chuck, Tunde A. Olaniyan, Garry A. Booker, Douglas G. Cogswell, Stephen R. Dark
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Publication number: 20220290580Abstract: An inlet for a nacelle housing a gas turbine engine generating thrust and having an engine centerline, the inlet including a highlight comprising a leading edge of the inlet, wherein the highlight has an outboard side and an inboard side; and the outboard side is forward of the inboard side of the highlight so as to increase an airflow into the inlet and allow increased alignment of a thrust vector of the thrust with the engine centerline.Type: ApplicationFiled: March 11, 2022Publication date: September 15, 2022Applicant: The Boeing CompanyInventors: Chen Chuck, Brian Scott Kornegay
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Patent number: 11085845Abstract: Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided.Type: GrantFiled: June 17, 2019Date of Patent: August 10, 2021Assignee: The Boeing CompanyInventors: Sho Sato, Chen Chuck
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Publication number: 20210023745Abstract: Compression mold assembly for forming a preform of a cascade includes first and second die elements and an axis of alignment. Line of removal of a formed preform is positioned perpendicular to a plane perpendicular to the axis of alignment. First die portion includes first curved surface forming interior surface of first strong back and second die portion includes first curved surface forming interior surface of a second strong back of a cell of a formed preform. Second die portion includes second curved surface forming an interior surface of a first vane on forward side of the cell of the formed preform and first die portion further includes first wall member which extends along line of removal and a second wall member which extends angularly from first wall portion forming an interior surface of a second vane positioned on an aft side of the cell.Type: ApplicationFiled: July 22, 2019Publication date: January 28, 2021Inventors: Zachariah VanDeMark, David J. Barene, Everette D. Gray, Chen Chuck, Tunde A. Olaniyan, Garry A. Booker, Douglas G. Cogswell, Stephen R. Dark
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Patent number: 10823112Abstract: A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.Type: GrantFiled: May 25, 2017Date of Patent: November 3, 2020Assignee: THE BOEING COMPANYInventors: Naimishkumar Harpal, Chen Chuck, Zachariah VanDeMark, Tunde A. Olaniyan, Minkoo Han
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Patent number: 10807735Abstract: Method and apparatus to reduce static pressure measuring error are disclosed. An example apparatus to measure static pressure includes a static pressure tap including a channel to define an external opening of a vehicle, where the channel extends through a pressure chamber to a pressure sensor disposed within, and a porous material disposed proximate the opening to reduce error in static pressure measurements.Type: GrantFiled: October 17, 2017Date of Patent: October 20, 2020Assignee: The Boeing CompanyInventors: Chen Chuck, Sho Sato
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Patent number: 10786929Abstract: A mold insert assembly includes a base section having a base side removably attachable to a base plate of a mold and a first interface surface having a notched portion thereon. A first section includes a first interface side with a first interconnecting tab sized to engage the notched portion of the base section when the first interface side abuts the first interface surface, the first section further including an adjoining side having an interconnecting notch. A second section includes a second interface side having a second interconnecting tab, where the second interconnecting tab is sized to engage the interconnecting notch of the first section when the second interface side abuts the adjoining side, and where the base section, the first section, and the second section when assembled form a contoured insert configured to create a contoured cavity in a part formed within the mold.Type: GrantFiled: September 24, 2018Date of Patent: September 29, 2020Assignee: The Boeing CompanyInventors: Chen Chuck, Tunde A. Olaniyan, David J. Barene, Zachariah B. Vandemark
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Patent number: 10723054Abstract: Methods of fabricating a component, such as a cascade grid panel for a jet engine thrust reverser, having a plurality of cavities extending through the component, with each cavity having at least one surface with a complex contour, and related devices. A plurality of two or more mold inserts are stacked to form a mold insert stack, with the mold insert stack having a plurality of mold bosses formed by mold boss sets. The mold boss sets are each formed by a mold boss segment from each of the mold inserts. Further, the mold boss segments are affixed to respective baseplates so that the mold boss segments can be handled as a group and remain properly positioned relative to their neighboring mold boss segments.Type: GrantFiled: December 11, 2017Date of Patent: July 28, 2020Assignee: The Boeing CompanyInventors: Chen Chuck, Everette D. Gray, David J. Barene, Tunde A. Olaniyan, Zachariah B. Vandemark
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Patent number: 10724475Abstract: Systems and methods are provided for a thrust reverser system with a straight vane thrust reverser cascade. The thrust reverser system may also include a blocker door and a turning door. The blocker door may divert air flowing within a bypass flow path of the aircraft propulsor to flow through the thrust reverser cascade. The turning door may then deflect air flowing from the thrust reverser cascade to provide reverse thrust. The straight vane thrust reverser cascade may allow for increased reverse thrust and/or a smaller, more efficient, aircraft propulsor.Type: GrantFiled: September 27, 2016Date of Patent: July 28, 2020Assignee: THE BOEING COMPANyInventors: Chen Chuck, Zachariah B. VanDeMark
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Patent number: 10641207Abstract: There is provided an air flow deflector apparatus for a thrust reverser system of an engine of an air vehicle. The air flow deflector apparatus is movable between a stowed non-reversing position and a deployed thrust reversing position, to deflect an air flow out of the engine, and to provide an effective reverse thrust for the thrust reverser system. There is further provided an air flow deflector assembly for a structure. The air flow deflector assembly has the air flow deflector apparatus, an extender member, and a recessed housing disposed in the structure. The air flow deflector assembly has an air flow deflector actuator that moves the air flow deflector apparatus between a stowed position and a deployed position adjacent to a reverse efflux air flow exit portion of the structure. The air flow deflector assembly deflects a reverse efflux air flow away from being re-ingested into the structure.Type: GrantFiled: July 21, 2017Date of Patent: May 5, 2020Assignee: The Boeing CompanyInventors: Chen Chuck, Suk C. Kim
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Publication number: 20200094444Abstract: A mold insert assembly includes a base section having a base side removably attachable to a base plate of a mold and a first interface surface having a notched portion thereon. A first section includes a first interface side with a first interconnecting tab sized to engage the notched portion of the base section when the first interface side abuts the first interface surface, the first section further including an adjoining side having an interconnecting notch. A second section includes a second interface side having a second interconnecting tab, where the second interconnecting tab is sized to engage the interconnecting notch of the first section when the second interface side abuts the adjoining side, and where the base section, the first section, and the second section when assembled form a contoured insert configured to create a contoured cavity in a part formed within the mold.Type: ApplicationFiled: September 24, 2018Publication date: March 26, 2020Inventors: Chen Chuck, Tunde A. Olaniyan, David J. Barene, Zachariah B. Vandemark
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Patent number: 10590885Abstract: Thrust reversers and methods to provide reverse thrust are disclosed. An example thrust reverser includes a cascade to direct air from an interior volume of an engine nacelle to generate reverse thrust with respect to a direction of travel, and an air extractor to extract a portion of air approaching the cascade from within the interior volume.Type: GrantFiled: November 14, 2016Date of Patent: March 17, 2020Assignee: THE BOEING COMPANYInventors: Kurt Erik Acheson, Chen Chuck
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Patent number: 10533521Abstract: There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body.Type: GrantFiled: July 31, 2017Date of Patent: January 14, 2020Assignee: The Boeing CompanyInventors: Naimishkumar B. Harpal, Chen Chuck, Zachariah B. Vandemark
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Publication number: 20190375136Abstract: A cascade assembly for a jet engine thrust reverser comprising an inflow cascade, an outflow cascade, and fasteners. The inflow cascade has a plurality of inflow vanes, a plurality of inflow strongbacks, and a front inflow flange. The outflow cascade has a plurality of outflow vanes, a plurality of outflow strongbacks, and a front outflow flange, wherein each of the plurality of outflow strongbacks are parallel to each other. The fasteners extend through the front inflow flange and the front outflow flange.Type: ApplicationFiled: June 8, 2018Publication date: December 12, 2019Inventors: Chen Chuck, Tunde Abiodun Olaniyan, Zachariah B. Vandemark, Naimishkumar B. Harpal, David J. Barene
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Publication number: 20190331545Abstract: Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided.Type: ApplicationFiled: June 17, 2019Publication date: October 31, 2019Inventors: Sho SATO, Chen CHUCK
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Patent number: 10323997Abstract: Various techniques are provided for correcting error in static pressure data. In one example, a system includes an aircraft component. The aircraft component can include a port disposed within the aircraft component. A static pressure sensor is disposed within the port. The static pressure sensor is configured to provide primary pressure data in response to environmental air pressure. The data provided can include error due to acoustic disturbance. The system can also include an acoustic sensor configured to provide acoustic data in response to the acoustic disturbance. Data from the static pressure sensor and the acoustic sensor can be provided to a processor communicatively coupled to the static pressure sensor and the acoustic sensor. The processor can be configured to determine corrected static pressure data using the provided primary pressure data and the provided acoustic data. Additional systems and similar methods are also provided.Type: GrantFiled: July 3, 2017Date of Patent: June 18, 2019Assignee: The Boeing CompanyInventors: Chen Chuck, Sho Sato
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Publication number: 20190176382Abstract: Methods of fabricating a component, such as a cascade grid panel for a jet engine thrust reverser, having a plurality of cavities extending through the component, with each cavity having at least one surface with a complex contour, and related devices. A plurality of two or more mold inserts are stacked to form a mold insert stack, with the mold insert stack having a plurality of mold bosses formed by mold boss sets. The mold boss sets are each formed by a mold boss segment from each of the mold inserts. Further, the mold boss segments are affixed to respective baseplates so that the mold boss segments can be handled as a group and remain properly positioned relative to their neighboring mold boss segments.Type: ApplicationFiled: December 11, 2017Publication date: June 13, 2019Inventors: Chen Chuck, Everette D. Gray, David J. Barene, Tunde A. Olaniyan, Zachariah B. Vandemark
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Patent number: 10309341Abstract: Systems and methods are provided for a formed thrust reverser cascade. The formed thrust reverser cascade may be coupled to an aircraft propulsor and may include a first portion disposed at a first angle to a portion of the aircraft propulsor and a second portion disposed at a second angle to the first portion. The formed thrust reverser cascade may be circumferentially disposed around a core engine of the aircraft propulsor. The formed thrust reverser cascades may be retrofitted to aircraft propulsors using linear thrust reverser cascade and may increase airflow through the formed thrust reverser cascade due to a greater throat area as compared to the linear thrust reverser cascade. Alternatively, the formed thrust reverser cascades may allow for shorter cascades while retaining the same performance, thus resulting in shorter nacelles.Type: GrantFiled: January 15, 2016Date of Patent: June 4, 2019Assignee: The Boeing CompanyInventors: Naimishkumar B. Harpal, Chen Chuck
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Publication number: 20190112069Abstract: Method and apparatus to reduce static pressure measuring error are disclosed.Type: ApplicationFiled: October 17, 2017Publication date: April 18, 2019Inventors: Chen Chuck, Sho Sato
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Publication number: 20190032601Abstract: There is provided an inflatable cascade assembly for a cascade thrust reverser system of an engine of an air vehicle. The inflatable cascade assembly has inflatable cascade members for inflation with a pressurized fluid. The inflatable cascade members are movable between a stowed deflated state and a deployed inflated state. Each inflatable cascade member has a forward end, an aft end, and a body. The body has circumferential vanes each having a first non-inflatable rigid side attached adjacent to a second inflatable flexible side. The body further has inflatable support members that are spaced apart and longitudinally extending, and coupled in a perpendicular arrangement to the circumferential vanes. The body further has a plurality of flow openings defined between the circumferential vanes and the inflatable support members. Each inflatable cascade member further has first and second extendable side supports coupled to respective first and second side ends of the body.Type: ApplicationFiled: July 31, 2017Publication date: January 31, 2019Inventors: Naimishkumar B. Harpal, Chen Chuck, Zachariah B. Vandemark