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    Thrust Reverser Apparatus and Method
    12.
    发明申请
    Thrust Reverser Apparatus and Method 审中-公开
    推力逆变器装置及方法

    公开(公告)号：US20160363097A1

    公开(公告)日：2016-12-15

    申请号：US14734298

    申请日：2015-06-09

    Applicant: The Boeing Company

    Inventor： David W. Foutch

    IPC: F02K1/70 ,  F02K1/76

    CPC classification number: F02K1/70 ,  F02C7/24 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F02K1/827 ,  F05D2260/50 ,  F05D2260/96 ,  Y02T50/671

    Abstract: A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.

    Abstract translation: 推力反向器适于固定在基本上围绕发动机芯罩的涡轮风扇发动机机舱内。 机舱和发动机核心罩一起限定了轴向延伸的环形管道，用于接收在推力反向器展开时向前重新定向的后流动的风扇旁路空气流。 机舱包括轴向平移套筒，周向布置的平移级联组件和可轴向平移的阻塞门，其适于从平移套筒径向向内枢转以至少部分地延伸到风扇旁路空气流中。 阻挡门部分牵引连杆机构可枢转地联接到每个平移套筒和阻挡门。 当收起时，旁路管道的轴向延伸的外壁径向插入在每个阻塞门和风扇旁路空气流之间，以确保阻挡门保持完全从风扇旁路空气流中隐藏。

    Bleed air systems for use with aircrafts and related methods
    13.
    发明授权
    Bleed air systems for use with aircrafts and related methods 有权
    用于飞机和相关方法的排气系统

    公开(公告)号：US08955794B2

    公开(公告)日：2015-02-17

    申请号：US13951181

    申请日：2013-07-25

    Applicant: The Boeing Company

    Inventor： Steve G. Mackin ,  David W. Foutch

    IPC: F02C3/13 ,  F02C6/08 ,  F02C7/32

    CPC classification number: F02C3/13 ,  F02C6/08 ,  F02C6/12 ,  F02C7/047 ,  F02C7/32 ,  F02K3/06 ,  F05D2260/601 ,  Y02T50/671

    Abstract: Bleed air systems for use with aircrafts and related methods are disclosed. An example apparatus includes a turbo-compressor including a compressor has a compressor inlet fluidly coupled to a low-pressure compressor of an aircraft engine and an intermediate port of a high-pressure compressor of the aircraft engine. The compressor inlet to receive fluid from either the low-pressure compressor or the high-pressure compressor based on a first system parameter of the aircraft. A turbine has a turbine inlet fluidly coupled to the intermediate port of the high pressure compressor and a high-pressure port of the high pressure compressor of the aircraft engine. The turbine inlet to receive fluid from either the intermediate port of the high-pressure compressor or the high-pressure port of the high-pressure compressor based on a second system parameter of the aircraft.

    Abstract translation: 公开了用于飞机和相关方法的排气系统。 一种示例性装置包括具有压缩机的涡轮压缩机，该压缩机具有流体耦合到飞机发动机的低压压缩机的压缩机入口和飞机发动机的高压压缩机的中间端口。 压缩机入口，用于基于飞行器的第一系统参数从低压压缩机或高压压缩机接收流体。 涡轮机具有流体耦合到高压压缩机的中间端口的涡轮机入口和飞机发动机的高压压缩机的高压端口。 涡轮入口基于飞行器的第二系统参数从高压压缩机的中间端口或高压压缩机的高压端口接收流体。

    Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers
    14.
    发明授权
    Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers 有权

    公开(公告)号：US12259196B2

    公开(公告)日：2025-03-25

    申请号：US17842552

    申请日：2022-06-16

    Applicant: The Boeing Company

    Inventor： Derek William Flett ,  David W. Foutch ,  Justin Honshune Lan ,  James W. Peck

    IPC: F28D9/00 ,  F02K3/00 ,  F28D21/00 ,  F28F3/02 ,  F28F13/06

    Abstract: Sound-attenuating heat exchangers and methods of exchanging heat and attenuating sound within sound-attenuating heat exchangers. The sound-attenuating heat exchangers include a base region, which defines a first base side and a second base side, and a plurality of elongate fluid conduits, which are at least partially defined by the base region and configured to contain a cooled fluid stream. The sound-attenuating heat exchangers also include a plurality of heat transfer-enhancing structures, which extend from the first base side and are configured to exchange thermal energy with a cooling fluid stream, and a sound-attenuating region, which extends from the second base side. The sound-attenuating region includes a plurality of resonator cells configured to attenuate sound and a plurality of resonator cell openings. Each resonator cell opening opens from a corresponding resonator cell toward the plurality of heat transfer-enhancing structures. The methods include methods of operating the sound-attenuating heat exchanger.

    SHAPE MEMORY ALLOY ACTUATORS AND THERMAL MANAGEMENT SYSTEMS INCLUDING THE SAME
    16.
    发明申请
    SHAPE MEMORY ALLOY ACTUATORS AND THERMAL MANAGEMENT SYSTEMS INCLUDING THE SAME 有权

    公开(公告)号：US20210404451A1

    公开(公告)日：2021-12-30

    申请号：US17469790

    申请日：2021-09-08

    Applicant: The Boeing Company

    Inventor： David W. Foutch ,  Kevin D. Finke

    IPC: F03G7/06

    Abstract: Shape memory alloy (SMA) actuators and thermal management systems including the same. An SMA actuator includes an SMA lifting tube and a process fluid conduit configured to convey a process fluid through the SMA lifting tube. The SMA actuator assumes a conformation that is based on the temperature of the process fluid. The SMA lifting tube includes a first end and a second end configured to translate relative to the first end at least partially along a lateral direction. A thermal management system is configured to regulate a temperature of a process fluid. The thermal management system includes a heat exchanger that at least partially defines a heat transfer region, a process fluid conduit configured to convey the process fluid through the heat transfer region, and an actuator assembly including the SMA actuator. The actuator assembly is configured to selectively position the heat exchanger within a thermal management fluid flow.

    Aircraft bleed air and engine starter systems and related methods
    17.
    发明授权
    Aircraft bleed air and engine starter systems and related methods 有权

    公开(公告)号：US10100744B2

    公开(公告)日：2018-10-16

    申请号：US14744398

    申请日：2015-06-19

    Applicant: The Boeing Company

    Inventor： Steve G. Mackin ,  David W. Foutch ,  Eric G. Landre

    IPC: F02C7/27 ,  F02C6/08

    Abstract: Example bleed air and engine starter systems are described herein that employ a shaft-driven compressor to start an aircraft engine and/or to supply pressurized air to one or more systems of an aircraft. An example compressor includes a housing and an impeller disposed within a cavity of the housing. The impeller is operatively coupled to a drive shaft. The compressor includes a first port in the housing to direct onto the impeller to rotate the impeller when the compressor is operating in a first mode. In the first mode, the impeller is to drive the drive shaft. The compressor also includes a second port in the housing oriented to provide air to the impeller when the impeller is operating in a second mode. In the second mode, the drive shaft is to rotate the impeller to draw the air from the first port and increase a pressure of the air.

    Thrust reverser apparatus and method
    19.
    发明授权
    Thrust reverser apparatus and method 有权

    公开(公告)号：US10041443B2

    公开(公告)日：2018-08-07

    申请号：US14734298

    申请日：2015-06-09

    Applicant: The Boeing Company

    Inventor： David W. Foutch

    IPC: F02K1/70 ,  F02K1/72 ,  F02K1/82 ,  F02C7/24 ,  F02K1/76

    Abstract: A thrust reverser is adapted to be fixed within a turbofan engine nacelle that extends substantially about an engine core cowl. The nacelle and engine core cowl together define an axially extending annular duct for receiving an aft flowing fan bypass air stream that is forwardly redirected upon deployment of the thrust reverser. The nacelle includes an axially translating sleeve, circumferentially arranged translating cascade sets, and axially translatable blocker doors adapted to pivot radially inwardly from the translating sleeve to extend at least partially into the fan bypass air stream. A blocker door deployment drag linkage is pivotally coupled to each of the translating sleeve and the blocker doors. When stowed, an axially extending outer wall of the bypass duct is radially interposed between each blocker door and the fan bypass air stream to assure that the blocker doors remain entirely concealed from the fan bypass air stream.

    BLEED AIR SYSTEMS FOR USE WITH AIRCRAFT AND RELATED METHODS
    20.
    发明申请
    BLEED AIR SYSTEMS FOR USE WITH AIRCRAFT AND RELATED METHODS 审中-公开

    公开(公告)号：US20180058333A1

    公开(公告)日：2018-03-01

    申请号：US15787511

    申请日：2017-10-18

    Applicant: The Boeing Company

    Inventor： David W. Foutch ,  Steve G. Mackin

    IPC: F02C9/18 ,  F02C7/047 ,  F02C3/10 ,  F02C7/27 ,  F02C7/32 ,  B64D13/06

    Abstract: Bleed air systems for use with aircraft and related methods are disclosed. An example apparatus includes a compressor having a compressor inlet, a compressor outlet, and a first drive shaft. The compressor outlet is to be fluidly coupled to a system of an aircraft that receives pressurized air, and the compressor inlet is to receive bleed air from a low-pressure compressor of an engine of the aircraft. The example apparatus includes a gearbox operatively coupled to the first drive shaft to drive the compressor. The gearbox is to be operatively coupled to and powered by a second drive shaft extending from the engine. The example apparatus also includes a clutch disposed between the first drive shaft and the gearbox to selectively disconnect the first drive shaft from the gearbox.

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