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公开(公告)号：US20190072222A1
公开(公告)日：2019-03-07
申请号：US16124995
申请日：2018-09-07
申请人： Goodrich Corporation
发明人： Michael John Giamati
IPC分类号： F16L53/34
CPC分类号： F16L53/34 , B64D13/02 , B64D13/08 , F28D15/0275 , H05B3/58
摘要： An air supply line includes an aluminum tube with a one inch diameter, a network of fins located within the aluminum tube to promote heat exchange, and a wall structure containing a heater wrapped around the aluminum tube to allow for temperature control and prevent freezing upstream of valves.
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公开(公告)号：US10059458B2
公开(公告)日：2018-08-28
申请号：US15231191
申请日：2016-08-08
发明人： Steven E. Squier
CPC分类号： B64D13/08 , B64D13/02 , B64D2013/0618 , B64D2013/0648 , B64D2013/0688 , F25B9/004 , F25B9/10 , Y02T50/56
摘要： An environmental control system for an aircraft includes a bleed air system. Also included is a ram air system. Further included is an air pressure and temperature conditioning system, wherein bleed air and ram air are mixed to satisfy a cabin fresh air requirement.
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公开(公告)号：US20180216538A1
公开(公告)日：2018-08-02
申请号：US15420808
申请日：2017-01-31
CPC分类号： F02C9/18 , B64C2230/04 , B64C2230/06 , B64D13/006 , B64D13/02 , B64D13/08 , B64D15/04 , B64D2013/0618 , B64D2033/0233 , F02C6/08 , F02C7/047 , F02C7/185 , Y02T50/675
摘要： A method of controlling an aircraft bleed may include the steps of monitoring a temperature of a precooled airflow exiting a precooler, and determining a status of a wing anti-ice system of an aircraft. The wing anti-ice system may be configured to receive the precooled airflow from the precooler. The method may further comprise the steps of determining whether an engine operating condition of the aircraft is within an icing envelope, selecting a temperature set point for the precooled airflow based on the status of the wing anti-ice system and whether the aircraft is within an icing envelope, and modulating a fan airflow from a fan to the precooler to adjust the temperature of the precooled airflow to the temperature set point.
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公开(公告)号：US09994323B2
公开(公告)日：2018-06-12
申请号：US14638469
申请日：2015-03-04
发明人： Louis J. Bruno , Thomas M. Zywiak , Erin G. Kline , Christina W. Millot , Harold W Hipsky, Jr. , Donald E. Army, Jr. , Paul M. D'Orlando
CPC分类号： B64D13/08 , B64D13/02 , B64D13/06 , B64D37/32 , B64D2013/0618 , B64D2013/064 , B64D2013/0648 , Y02T50/56
摘要： A replacement system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The replacement system employs a subsystem to treat the medium from the low-pressure location of the engine before it is received by the inerting system.
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公开(公告)号：US20180111693A1
公开(公告)日：2018-04-26
申请号：US15332443
申请日：2016-10-24
发明人： Brian R. Shea
IPC分类号： B64D13/06
CPC分类号： B64D13/06 , B64D13/02 , B64D13/08 , B64D2013/0618 , B64D2013/0625 , B64D2013/064
摘要： An environmental control system includes a turbo-compressor assembly and a ram air system. The turbo-compressor assembly includes a first turbine, a first compressor, and a first heat exchanger. The first heat exchanger has a first heat exchanger first side in fluid communication a first turbine outlet, a first heat exchanger second side, a first heat exchanger inlet in fluid communication a first compressor outlet, and a first heat exchanger outlet. The ram air system has a first ram air inlet, a second ram air inlet being in fluid communication with the first heat exchanger second side, and a second heat exchanger being in fluid communication with at least one of the first ram air inlet and the second ram air inlet.
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公开(公告)号：US09874239B2
公开(公告)日：2018-01-23
申请号：US14883120
申请日：2015-10-14
CPC分类号： F16C3/02 , B64D13/02 , B64D13/06 , B64D13/08 , B64D2013/0614 , F16C17/024 , F16C37/002 , F16C2240/54
摘要： A turbine thrust shaft providing a thrust disk having a surface P and a surface Q, and a shaft body formed through the thrust disk, the shaft body including a first plurality of holes, wherein the first plurality of holes are spaced apart and each hole of the first plurality of holes has a first diameter between 0.0600 inches to 0.0680 inches and has a first center disposed a first distance between 0.1400 inches to 0.1600 inches from surface P, and a second plurality of holes wherein the second plurality of holes are spaced apart and each hole of the second plurality of holes has a second diameter between 0.0960 inches to 0.1040 inches and has a second center disposed a second distance between 2.1350 inches to 2.1550 inches from surface Q.
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公开(公告)号：US20170334573A1
公开(公告)日：2017-11-23
申请号：US15597223
申请日：2017-05-17
发明人： Ilja WAIGL , Matias MAIL , Thorsten KNIJNENBURG
CPC分类号： B64D45/00 , B64C25/001 , B64C25/34 , B64D13/02 , B64D13/04 , B64D2045/0085 , G01L13/00 , G01L19/0007
摘要： A differential pressure sensor system for use in an aircraft comprises a differential pressure sensor for determining a differential pressure between a pressurizable aircraft cabin and an aircraft environment, the differential pressure sensor having a first port connectable to the pressurizable aircraft cabin via a first line and a second port connectable to the aircraft environment via a second line. A shut-off device of the differential pressure sensor system is arranged in the second line which is switchable between an open position in which it opens the second line, such that a pressure prevailing in the aircraft environment acts on the second port of the differential pressure sensor, and a shut-off position in which it closes the second line, such that the second port of the differential pressure sensor is shut off from the pressure prevailing in the aircraft environment.
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公开(公告)号：US09809313B2
公开(公告)日：2017-11-07
申请号：US11625764
申请日：2007-01-22
申请人： Kevin J Conner , Yasuo Ishihara , Steve C. Johnson
发明人： Kevin J Conner , Yasuo Ishihara , Steve C. Johnson
IPC分类号： B64D13/02
CPC分类号： B64D13/02
摘要： Systems and methods for intelligently alerting the flight crew of a cabin depressurization. An example system includes a cabin altimeter that generates a cabin pressure value, an alerting device, such as a speaker system and a processing device in data communication with the cabin altimeter and the alerting device. The processing device determines if there is a problem with the cabin pressure received from the cabin altimeter, determines rate of change of the cabin pressure, and sets at least one of an alert volume or an alert frequency based on the cabin pressure and the rate of change of the cabin pressure if it was determined that a problem exists with the cabin pressure. The processing device also issues a cabin depressurization alert over the alerting device based on at least one of the set alert volume or alert frequency, if there is a problem with the cabin pressure value.
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公开(公告)号：US09802708B2
公开(公告)日：2017-10-31
申请号：US13381488
申请日：2010-06-30
CPC分类号： B64D13/02 , F16K1/165 , F16K15/038 , Y10T137/598 , Y10T137/6017 , Y10T137/6906 , Y10T137/7837
摘要： A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is configured to facilitate removal of a first flange and the flow duct by moving the first flange and flow duct a second distance that is less than the first distance. The check valve is offset into the upstream side of a second flange to provide the reduction in the distance that the first flange has to be displaced to remove the first flange and flow duct from the check valve. A first alternate configuration of the fluid check valve utilizes rotational stops attached to the downstream surface of the flow flaps and in a second alternate embodiment configuration, rotational stops extend upstream from the flow flaps.
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公开(公告)号：US09789967B2
公开(公告)日：2017-10-17
申请号：US14971297
申请日：2015-12-16
CPC分类号： B64D13/08 , B64D13/02 , B64D13/06 , B64D2013/0618 , B64D2013/0662 , B64D2013/0666
摘要： A method of controlling an outlet temperature of a heat exchanger of an aircraft includes operating an air cycle machine at a first operating speed. The air cycle machine is operatively coupled to an air cycle machine bypass valve at a first position. The air cycle machine is fluidly connected to a first heat exchanger disposed adjacent to a second heat exchanger. In response to a second heat exchanger outlet temperature less than a second heat exchanger outlet temperature threshold while the aircraft is operating at an altitude less than an altitude threshold, the method moves the air cycle bypass valve from the first position toward a second position.
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