-
公开(公告)号：US09488067B2
公开(公告)日：2016-11-08
申请号：US14154967
申请日：2014-01-14
Applicant: The Boeing Company
Inventor： Rick A. Johnson , Victor D. Pham , Daniel H. Gally , Joseph James Seydel , Edward Charles Natsui
CPC classification number: F01D25/02 , B64D15/04 , F02C7/047 , Y02T50/671
Abstract: Apparatus and methods to lower peak temperatures and improve performance of aircraft anti-icing systems are described herein. One described example apparatus includes a skin on an inlet side of a nacelle of an aircraft defining an annular chamber, a gas delivery system disposed within the annular chamber to provide a first gas to mix with and entrain a second gas in the annular chamber to define a flow through the annular chamber, and a deflector vane disposed within the annular chamber to redirect the flow through the annular chamber. The second gas is at a different temperature from the first gas.
Abstract translation: 本文描述了降低峰值温度并提高飞机防冰系统性能的装置和方法。 一种描述的示例性装置包括在限定环形室的飞行器的机舱的入口侧上的皮肤，设置在环形室内的气体输送系统，以提供第一气体与第二气体混合并夹带在环形室中以限定 通过环形室的流动，以及设置在环形室内的偏转叶片，以重新定向流过环形室的流体。 第二气体处于与第一气体不同的温度。
-
公开(公告)号：US11912420B2
公开(公告)日：2024-02-27
申请号：US17717202
申请日：2022-04-11
Applicant: THE BOEING COMPANY
Inventor： Edward Charles Natsui , Melissa Marie Bravin , Erik Marc Langhofer
Abstract: A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.
-
公开(公告)号：US20230322393A1
公开(公告)日：2023-10-12
申请号：US17717202
申请日：2022-04-11
Applicant: THE BOEING COMPANY
Inventor： Edward Charles Natsui , Melissa Marie Bravin , Erik Marc Langhofer
Abstract: A system and method include a first icing detector configured to detect a first icing condition in relation to one or more portions of an aircraft. The first icing detector is configured to output a first icing signal indicative of the first icing condition. A second icing detector is configured to detect a second icing condition in relation to the one or more portions of the aircraft. The second icing detector is configured to output a second icing signal indicative of the second icing condition. A control unit is in communication with the first icing detector and the second icing detector. The control unit is configured to receive the first icing signal from the first icing detector and the second icing signal from the second icing detector. The control unit is further configured to distinguish between presence of supercooled liquid water and ice crystal icing in response to receiving one or both of the first icing signal or the second icing signal.
-
公开(公告)号：US20150198061A1
公开(公告)日：2015-07-16
申请号：US14154967
申请日：2014-01-14
Applicant: The Boeing Company
Inventor： Rick A. Johnson , Victor D. Pham , Daniel H. Gally , Joseph James Seydel , Edward Charles Natsui
CPC classification number: F01D25/02 , B64D15/04 , F02C7/047 , Y02T50/671
Abstract: Apparatus and methods to lower peak temperatures and improve performance of aircraft anti-icing systems are described herein. One described example apparatus includes a skin on an inlet side of a nacelle of an aircraft defining an annular chamber, a gas delivery system disposed within the annular chamber to provide a first gas to mix with and entrain a second gas in the annular chamber to define a flow through the annular chamber, and a deflector vane disposed within the annular chamber to redirect the flow through the annular chamber. The second gas is at a different temperature from the first gas.
Abstract translation: 本文描述了降低峰值温度并提高飞机防冰系统性能的装置和方法。 一种描述的示例性装置包括在限定环形室的飞行器的机舱的入口侧上的皮肤，设置在环形室内的气体输送系统，以提供第一气体与第二气体混合并夹带在环形室中以限定 通过环形室的流动，以及设置在环形室内的偏转叶片，以重新定向流过环形室的流体。 第二气体处于与第一气体不同的温度。
-
-
-
Search Results
4
records
(took 0.015 seconds)
