Patents by Inventor John Taylor Pearson
John Taylor Pearson 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: 11560968Abstract: A bleed valve for a gas turbine engine includes a housing that defines an inlet upstream from an outlet. The bleed valve includes a poppet movable relative to the housing between a first position, in which the poppet closes the inlet, and a second position, in which the inlet is open and configured to receive a fluid flow. The housing defines a tortuous path for the fluid flow from the inlet to the outlet configured to reduce a pressure of the fluid flow from the inlet to the outlet within the housing. The tortuous path is defined by a plurality of rings positioned about the poppet, with each ring of the plurality of rings spaced apart from an adjacent ring of the plurality of rings between the inlet and the outlet to define the tortuous path.Type: GrantFiled: February 27, 2020Date of Patent: January 24, 2023Assignee: HONEYWELL INTERNATIONAL INC.Inventors: John Taylor Pearson, William B. Schuster, Morris G. Anderson
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Publication number: 20210270388Abstract: A bleed valve for a gas turbine engine includes a housing that defines an inlet upstream from an outlet. The bleed valve includes a poppet movable relative to the housing between a first position, in which the poppet closes the inlet, and a second position, in which the inlet is open and configured to receive a fluid flow. The housing defines a tortuous path for the fluid flow from the inlet to the outlet configured to reduce a pressure of the fluid flow from the inlet to the outlet within the housing. The tortuous path is defined by a plurality of rings positioned about the poppet, with each ring of the plurality of rings spaced apart from an adjacent ring of the plurality of rings between the inlet and the outlet to define the tortuous path.Type: ApplicationFiled: February 27, 2020Publication date: September 2, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: John Taylor Pearson, William B. Schuster, Morris G. Anderson
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Patent number: 11001396Abstract: Airfield guidance signs are described herein. One airfield guidance sign includes a first surface, a second surface angled with respect to the first surface, and a top edge adjacent the first surface and the second surface, wherein the top edge is rounded to reduce a pressure differential between the first surface and the second surface when a force is applied to the first surface or the second surface.Type: GrantFiled: November 17, 2017Date of Patent: May 11, 2021Assignee: Honeywell International Inc.Inventors: John Taylor Pearson, Yogendra Yogi Sheoran, Ramalingam Nallur, Don Reginald Holcomb, Jr.
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Patent number: 10648426Abstract: A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.Type: GrantFiled: January 14, 2016Date of Patent: May 12, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Mark Knowles, Shawn Alstad, Robert Romano, John Taylor Pearson, Morris Anderson, David Robinson
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Publication number: 20200079526Abstract: Airfield guidance signs are described herein. One airfield guidance sign includes a first surface, a second surface angled with respect to the first surface, and a top edge adjacent the first surface and the second surface, wherein the top edge is rounded to reduce a pressure differential between the first surface and the second surface when a force is applied to the first surface or the second surface.Type: ApplicationFiled: November 17, 2017Publication date: March 12, 2020Inventors: John Taylor PEARSON, Yogendra Yogi SHEORAN, Ramalingam NALLUR, Don Reginald HOLCOMB, Jr.
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Patent number: 10337454Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.Type: GrantFiled: January 25, 2016Date of Patent: July 2, 2019Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Shawn Alstad, John Taylor Pearson, Morris Anderson
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Patent number: 10138904Abstract: An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, and a splitter. The hub section has a hub outer surface that diverges, relative to the axis of symmetry, to a hub apex. The shroud section has a shroud inner surface that surrounds, and is spaced apart from, at least a portion of the hub section to define a main flow passageway between the hub outer surface and the shroud inner surface. The splitter is disposed downstream of the air inlet and extends into the main flow passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub section and the shroud section are configured such that the cross sectional flow area of the main flow passageway decreases downstream of the air inlet to define a throat section that is disposed upstream of the hub apex.Type: GrantFiled: January 6, 2016Date of Patent: November 27, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: John Taylor Pearson, Yogendra Yogi Sheoran, Bruce Dan Bouldin, Zedic Daniel Judd, Eduardo Guerra, David Chou
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Patent number: 10100734Abstract: A multi-channel particle separator includes a plurality of vanes. Each vane is spaced apart from at least one other adjacent vane to define a flow channel, and includes a leading edge, a trailing edge, a first side wall, a second sidewall, and a splitter. The first side wall extends between the leading edge and the trailing edge. The second side wall is spaced apart from the first side wall and extends from the leading edge toward the trailing edge. The splitter may be rotationally coupled to the trailing edge and extend toward the leading edge. The splitter is spaced apart from the first side wall to define a scavenge volume and is rotatable between an extended position and a retracted position. The vanes may also or instead be coupled to a ring-shaped structure.Type: GrantFiled: February 24, 2015Date of Patent: October 16, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Yogendra Yogi Sheoran, Jennifer Ann Reich, Bruce Dan Bouldin, Zedic Daniel Judd, John Taylor Pearson, Cristopher Frost, Yates Wong, David Chou, Eduardo Guerra
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Publication number: 20170370287Abstract: An inlet particle separator system includes a shroud section and a hub section that is at least partly surrounded by the shroud section. The hub section is spaced apart from the shroud section. The inlet particle separator system also includes a flow passageway with an air inlet defined between the hub section and the shroud section. The flow passageway branches downstream of the air inlet into a main passage and a pre-cleaner passage. The main passage is defined between the hub section and the shroud section. The pre-cleaner passage includes a pre-cleaner inlet and extends at least partially through the hub section. Furthermore, the system includes a splitter that divides the main passage into scavenge and engine flow paths. The pre-cleaner inlet is partly defined by a first surface of the hub section. The first surface faces substantially in an upstream direction toward the air inlet.Type: ApplicationFiled: June 22, 2016Publication date: December 28, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: John Taylor Pearson, Zedic Daniel Judd, Yogendra Yogi Sheoran, Bruce Dan Bouldin, David Chou, Eduardo Guerra
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Publication number: 20170211511Abstract: A thrust reverser system having an asymmetric vane assembly is provided. The provided thrust reverser system generates a desired vertical thrust component that at least partially offsets a potential nose-up pitch moment. The provided thrust reverser system employs a single row asymmetric vane geometry that reduces weight and material cost.Type: ApplicationFiled: January 25, 2016Publication date: July 27, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Shawn Alstad, John Taylor Pearson, Morris Anderson
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Publication number: 20170204808Abstract: A thrust reverser system for a turbine engine includes a support structure, a transcowl, and a door. The transcowl is mounted on the support structure and is axially translatable, relative to the support structure, between first and second positions. The door is pivotally coupled to the support structure and is rotatable, about a pivot axis, between stowed and deployed positions when the transcowl translates between the first and second positions, respectively. The door has an internal surface and a balance plane, and pressure forces acting along the balance plane effectively creates no moment about the pivot axis. The internal surface of the door has a first surface area forward of the balance plane and a second surface area aft of the balance plane, and the second surface area substantially exceeds the first surface area.Type: ApplicationFiled: January 18, 2016Publication date: July 20, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Robert Romano, John Taylor Pearson, Morris Anderson, Remo Neri
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Publication number: 20170204809Abstract: A thrust reverser system comprising a single row vane assembly is provided. The provided thrust reverser system is capable of meeting performance requirements for turbine engines with reduced weight and cost.Type: ApplicationFiled: January 14, 2016Publication date: July 20, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Danis Burton Smith, Mark Knowles, Shawn Alstad, Robert Romano, John Taylor Pearson, Morris Anderson, David Robinson
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Publication number: 20170191503Abstract: An inlet particle separator system for a vehicle engine includes a hub section, a shroud section, and a splitter. The hub section has a hub outer surface that diverges, relative to the axis of symmetry, to a hub apex. The shroud section has a shroud inner surface that surrounds, and is spaced apart from, at least a portion of the hub section to define a main flow passageway between the hub outer surface and the shroud inner surface. The splitter is disposed downstream of the air inlet and extends into the main flow passageway to divide the main flow passageway into a scavenge flow path and an engine flow path. The hub section and the shroud section are configured such that the cross sectional flow area of the main flow passageway decreases downstream of the air inlet to define a throat section that is disposed upstream of the hub apex.Type: ApplicationFiled: January 6, 2016Publication date: July 6, 2017Applicant: HONEYWELL INTERNATIONAL INC.Inventors: John Taylor Pearson, Yogendra Yogi Sheoran, Bruce Dan Bouldin, Zedic Daniel Judd, Eduardo Guerra, David Chou
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Publication number: 20160245176Abstract: A multi-channel particle separator includes a plurality of vanes. Each vane is spaced apart from at least one other adjacent vane to define a flow channel, and includes a leading edge, a trailing edge, a first side wall, a second sidewall, and a splitter. The first side wall extends between the leading edge and the trailing edge. The second side wall is spaced apart from the first side wall and extends from the leading edge toward the trailing edge. The splitter may be rotationally coupled to the trailing edge and extend toward the leading edge. The splitter is spaced apart from the first side wall to define a scavenge volume and is rotatable between an extended position and a retracted position. The vanes may also or instead be coupled to a ring-shaped structure.Type: ApplicationFiled: February 24, 2015Publication date: August 25, 2016Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Yogendra Yogi Sheoran, Jennifer Ann Reich, Bruce Dan Bouldin, Zedic Daniel Judd, John Taylor Pearson, Cristopher Frost, Yates Wong, David Chou, Eduardo Guerra
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Patent number: D825367Type: GrantFiled: November 21, 2016Date of Patent: August 14, 2018Assignee: Honeywell International Inc.Inventors: John Taylor Pearson, Yogendra Yogi Sheoran, Ramalingam Nallur, Don Reginald Holcomb, Jr.