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公开(公告)号：US10724475B2
公开(公告)日：2020-07-28
申请号：US15277900
申请日：2016-09-27
Applicant: The Boeing Company
Inventor： Chen Chuck , Zachariah B. VanDeMark
Abstract: 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.
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公开(公告)号：US20190176382A1
公开(公告)日：2019-06-13
申请号：US15837604
申请日：2017-12-11
Applicant: The Boeing Company
Inventor： Chen Chuck , Everette D. Gray , David J. Barene , Tunde A. Olaniyan , Zachariah B. Vandemark
Abstract: 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.
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公开(公告)号：US09670875B2
公开(公告)日：2017-06-06
申请号：US13665596
申请日：2012-10-31
Applicant: The Boeing Company
Inventor： Kurt Erik Acheson , Chen Chuck
CPC classification number: F02K1/72 , F02K1/766 , F05D2220/323 , Y02T50/671
Abstract: 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.
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公开(公告)号：US12215591B2
公开(公告)日：2025-02-04
申请号：US17692816
申请日：2022-03-11
Applicant: The Boeing Company
Inventor： Chen Chuck , Brian Scott Kornegay
Abstract: 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.
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公开(公告)号：US10807735B2
公开(公告)日：2020-10-20
申请号：US15786341
申请日：2017-10-17
Applicant: The Boeing Company
Inventor： Chen Chuck , Sho Sato
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US10590885B2
公开(公告)日：2020-03-17
申请号：US15350217
申请日：2016-11-14
Applicant: The Boeing Company
Inventor： Kurt Erik Acheson , Chen Chuck
Abstract: 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.
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公开(公告)号：US20190112069A1
公开(公告)日：2019-04-18
申请号：US15786341
申请日：2017-10-17
Applicant: The Boeing Company
Inventor： Chen Chuck , Sho Sato
CPC classification number: B64D43/02 , G01K13/02 , G01K2013/024 , G01L19/0038 , G01L19/0046 , G01L19/0609 , G01P13/045
Abstract: 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
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公开(公告)号：US12276238B2
公开(公告)日：2025-04-15
申请号：US18161670
申请日：2023-01-30
Applicant: The Boeing Company
Inventor： Chen Chuck , Brian S. Kornegay
Abstract: A thrust reverser in an engine includes a first reverser portion configured to direct a gas in a first direction to create reverse thrust. The thrust reverser also includes a second reverser portion configured to direct the gas in a second direction that is different than the first direction. The second reverser portion is upstream or downstream from the first reverser portion.
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公开(公告)号：US10533521B2
公开(公告)日：2020-01-14
申请号：US15665362
申请日：2017-07-31
Applicant: The Boeing Company
Inventor： Naimishkumar B. Harpal , Chen Chuck , Zachariah B. Vandemark
Abstract: 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.
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公开(公告)号：US10323997B2
公开(公告)日：2019-06-18
申请号：US15641148
申请日：2017-07-03
Applicant: The Boeing Company
Inventor： Chen Chuck , Sho Sato
Abstract: 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.
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