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公开(公告)号：US20230182905A1
公开(公告)日：2023-06-15
申请号：US17548702
申请日：2021-12-13
Applicant: THE BOEING COMPANY
Inventor： Warren A. Atkey , Gene Stubbs
IPC: B64D13/02
CPC classification number: B64D13/02 , B64D2013/0603
Abstract: A ram air system includes a ram air inlet, a ram air outlet, a conduit fluidly coupling the ram air inlet to the ram air outlet, and a relief port disposed within the conduit. A method of controlling a ram air system includes disposing a relief port within a conduit of the ram air system, wherein the conduit fluidly couples a ram air inlet to a ram air outlet in order to minimize or otherwise reduce drag, and to control unstable airflow that can otherwise cause resonant instability.
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公开(公告)号：US20210122477A1
公开(公告)日：2021-04-29
申请号：US16662855
申请日：2019-10-24
Applicant: THE BOEING COMPANY
Inventor： Michael L. Trent , Warren A. Atkey
IPC: B64D13/08
Abstract: An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.
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公开(公告)号：US20210122476A1
公开(公告)日：2021-04-29
申请号：US16662793
申请日：2019-10-24
Applicant: THE BOEING COMPANY
Inventor： Michael L. Trent , Warren A. Atkey
Abstract: An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.
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公开(公告)号：US11518522B2
公开(公告)日：2022-12-06
申请号：US16662855
申请日：2019-10-24
Applicant: THE BOEING COMPANY
Inventor： Michael L. Trent , Warren A. Atkey
Abstract: An aircraft includes a fuselage defining a cabin region and a crown region. The aircraft also includes a duct disposed within the fuselage. The duct is coupled to one or more drying air vents disposed in the crown region and coupled to one or more cabin vents disposed with the cabin region. The one or more drying air vents are configured to output drying air, received via the duct, into the crown region, and the one or more cabin vents are configured to output conditioned air, received via the duct, into the cabin region. The aircraft further includes one or more valves coupled to the duct and configured to, in a first valve position, route airflow within the duct to the one or more drying air vents and configured to, in a second valve position, route the airflow within the duct to the one or more cabin vents.
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公开(公告)号：US20190100318A1
公开(公告)日：2019-04-04
申请号：US15724647
申请日：2017-10-04
Applicant: The Boeing Company
Inventor： David R. Space , Stephen M. Trent , Dale A. Scheer , Warren A. Atkey , Anil Kumar Salgar
Abstract: An Environmental Control Systems (ECS) for an aerospace vehicle comprises an air supply airflow path inputting, monitoring, and conditioning air from external to the vehicle, and a recirculation airflow path inputting, monitoring, filtering, and moving air from one portion of the interior of the vehicle to another portion. The air supply airflow can include a dynamically controlled VOC/ozone converter, which can be operated when the aerospace vehicle is on the ground. The recirculation airflow path can include a dynamically controlled regenerative gas contaminant filter and/or VOC/CO2 removal device. The filter/adsorption media of the controlled regenerative gas contaminant filter and/or VOC/CO2 removal device can be regenerated by suppling hot air or a vacuum, and gaseous contaminants can be broken down for removal from the regenerative gas contaminant filter by controlling UV irradiation. The controller can alert a flight crew if air quality falls outside predetermined or programmable parameters.
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Patent Agency Ranking
公开(公告)号：US09669936B1
公开(公告)日：2017-06-06
申请号：US13659897
申请日：2012-10-24
Applicant: The Boeing Company
Inventor： Charles J. Fiterman , Warren A. Atkey
CPC classification number: B64D13/06 , B64D2013/0618 , B64D2013/0648 , B64D2013/0662 , B64D2013/0674
Abstract: There are provided aircraft air conditioning systems and methods. The aircraft air conditioning system has a duct in an aircraft connected to an aircraft cabin and configured to flow pressurized cabin outflow air from the aircraft cabin. The aircraft air conditioning system further has a turbine connected to the duct and configured to reduce a temperature of the pressurized cabin outflow air and to generate power, and further has a compressor configured to generate a compressed inlet air stream, and further has an air conditioning pack configured to receive a reduced temperature cabin outflow air from the turbine and configured to receive the compressed inlet air stream from the compressor. The air conditioning pack has a cooling cycle system, a humidity control system, and one or more heat exchangers configured to use the reduced temperature cabin outflow air as a heat sink.
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7.发明申请Turbo-Compressor System and Method for Extracting Energy from an Aircraft Engine 有权涡轮压缩机系统和从飞机发动机提取能量的方法公开(公告)号：US20150251766A1
公开(公告)日：2015-09-10
申请号：US14203533
申请日：2014-03-10
Applicant: THE BOEING COMPANY
Inventor： Warren A. Atkey
CPC classification number: B64D13/08 , B64D13/06 , B64D41/007 , B64D2013/0618 , B64D2013/0644 , B64D2013/0648 , B64D2013/0688 , F02C7/32 , F25B27/00 , F25B31/026 , Y02T50/56
Abstract: A turbo-compressor (TC) system for extracting energy from an aircraft engine. The TC system has a TC assembly with a turbine mechanically coupled to at least one compressor. The TC system has a TC inlet in fluid communication with a bleed air system in the aircraft engine and a TC outlet in fluid communication with an air conditioning (AC) pack of an aircraft air conditioning system and configured to extract reduced temperature pack inlet air from the TC assembly into the air conditioning pack. The TC system has a ram air inlet coupled to the at least one compressor. The TC system has a TC control valve, and a TC check valve or a TC shutoff valve, both coupled to the TC assembly via a plurality of connective ducts. The TC system extracts energy from the bleed air to reduce bleed air flow and AC pack ram air usage.
Abstract translation: 一种用于从飞机发动机提取能量的涡轮压缩机（TC）系统。 TC系统具有TC组件，其具有机械耦合到至少一个压缩机的涡轮机。 TC系统具有与飞机发动机中的放气系统流体连通的TC入口和与飞机空调系统的空调（AC）包流体连通的TC出口，并配置成从 TC组装入空调包装。 TC系统具有联接到至少一个压缩机的冲压空气入口。 TC系统具有TC控制阀和TC止回阀或TC截止阀，两者都通过多个连接管耦合到TC组件。 TC系统从排气中提取能量，以减少排气流量和AC组件冲压空气使用。
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公开(公告)号：US11427332B2
公开(公告)日：2022-08-30
申请号：US16719466
申请日：2019-12-18
Applicant: The Boeing Company
Inventor： Brian C. Christenson , Warren A. Atkey , Bryce A. Tillack
Abstract: Example implementations for maintaining airflow into a flight deck of an aircraft are described herein. An example method may involve detecting, at a computing system and using a flow sensor, a decrease in a level of airflow entering into the flight deck such that the level of airflow is below a threshold level. The aircraft may include air sources configured to direct airflow towards occupancy areas (e.g., the cabin and flight deck) of the aircraft. The method may further involve adjusting a control valve to cause an increase in the level of airflow entering into the flight deck based on detecting the decrease in level of airflow entering into the flight deck. The control valve may be configured to enable and disable airflow from entering into the flight deck.
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公开(公告)号：US10737791B2
公开(公告)日：2020-08-11
申请号：US15724647
申请日：2017-10-04
Applicant: The Boeing Company
Inventor： David R. Space , Stephen M. Trent , Dale A. Scheer , Warren A. Atkey , Anil Kumar Salgar
Abstract: An Environmental Control Systems (ECS) for an aerospace vehicle comprises an air supply airflow path inputting, monitoring, and conditioning air from external to the vehicle, and a recirculation airflow path inputting, monitoring, filtering, and moving air from one portion of the interior of the vehicle to another portion. The air supply airflow can include a dynamically controlled VOC/ozone converter, which can be operated when the aerospace vehicle is on the ground. The recirculation airflow path can include a dynamically controlled regenerative gas contaminant filter and/or VOC/CO2 removal device. The filter/adsorption media of the controlled regenerative gas contaminant filter and/or VOC/CO2 removal device can be regenerated by suppling hot air or a vacuum, and gaseous contaminants can be broken down for removal from the regenerative gas contaminant filter by controlling UV irradiation. The controller can alert a flight crew if air quality falls outside predetermined or programmable parameters.
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10.发明申请公开(公告)号：US20150274303A1
公开(公告)日：2015-10-01
申请号：US14230348
申请日：2014-03-31
Applicant: The Boeing Company
Inventor： John C. Gray , Warren A. Atkey
Abstract: An aircraft including a fuselage defining an upper lobe and a lower lobe, the fuselage including a wall structure that includes an outboard boundary and an inboard boundary spaced from the outboard boundary, wherein the outboard boundary and the inboard boundary define a wall volume therebetween, and at least one sealing member positioned in the wall volume.
Abstract translation: 一种包括限定上凸耳和下凸角的机身的飞机，所述机身包括包括外侧边界和与所述外侧边界隔开的内侧边界的壁结构，其中所述外侧边界和所述内侧边界在其间限定壁体积， 位于所述壁体积中的至少一个密封构件。
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