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公开(公告)号：US10273014B2
公开(公告)日：2019-04-30
申请号：US15255043
申请日：2016-09-01
摘要： The invention relates to a suspension pylon comprising: at least one arm (3) for suspending a propulsion unit (4) from the fuselage (2) of an airplane (1), an oil exchange circuit (70) configured to be connected, on the one hand, to an oil pump (5) in the fuselage (2) and on the other hand, to the propulsion unit (4) the arm (3) whereof provides for suspension, said circuit (70) comprising a feed line (72) and a return line (74), which both extend inside said arm (3), an intermediate shaft (6) which extends in said arm (3), said shaft being configured, on the one hand, to be driven by the propulsion unit (4) the arm (3) whereof provides for suspension and, on the other hand, to drive the oil pump (5) in the fuselage (2), wherein the arm (3) has a structure adapted for cooling the oil exchange circuit at the arm (3).
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公开(公告)号：US20180180364A1
公开(公告)日：2018-06-28
申请号：US15665117
申请日：2017-07-31
摘要： The invention is directed to an article with a liquid-impregnated surface, the surface having a matrix of features thereupon, spaced sufficiently close to stably contain a liquid therebetween or therewithin, and preferable also a thin film thereupon. The surface provides the article with advantageous non-wetting properties. Compared to previous non-wetting surfaces, which include a gas (e.g., air) entrained within surface textures, these liquid-impregnated surfaces are resistant to impalement and frost formation, and are therefore more robust.
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13.发明申请公开(公告)号：US20180093775A1
公开(公告)日：2018-04-05
申请号：US15724995
申请日：2017-10-04
申请人： Jonathan B. Boreyko , Saurabh Nath , Caitlin Bisbano , Grady J. Iliff , Ryan Hansen , C. Patrick Collier
发明人： Jonathan B. Boreyko , Saurabh Nath , Caitlin Bisbano , Grady J. Iliff , Ryan Hansen , C. Patrick Collier
CPC分类号： B64D15/06 , B05D1/38 , B05D7/24 , B05D2350/33 , F25B47/006 , F25C1/06 , F25D21/04 , F28F19/006 , F28F19/02 , F28F2245/02
摘要： A method and device for reducing ice and frost on a surface comprising a wettable pattern on a surface. The pattern is wetted with water which is frozen into ice to create overlapping hygroscopic that cover the surface.
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公开(公告)号：US20170029126A1
公开(公告)日：2017-02-02
申请号：US15221170
申请日：2016-07-27
申请人： THALES
发明人： Claude SARNO , Romain HODOT
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , F28D15/0266 , F28D2021/0021 , G01F1/46 , G01P5/165
摘要： An aircraft provided with at least one piece of aeronautic equipment, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (70) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.
摘要翻译： 一种设置有至少一件航空设备的飞机，该设备（25）包括旨在布置在飞行器的皮肤（27）上的部件和用于加热该部件的元件，其特征在于，所述加热元件包括热力循环 包括其中传热流体循环的闭合回路，所述闭合回路包括与飞行器的功能元件（70）相关联的蒸发器（14），所述蒸发器形成在其操作期间发热的热源，并且其中冷凝 传热流体可以在附件中发生以加热它，并且在蒸发器外部，流体循环的回路由具有空的部分的管状通道形成。
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公开(公告)号：US20170029120A1
公开(公告)日：2017-02-02
申请号：US15220417
申请日：2016-07-27
申请人： THALES
CPC分类号： B64D15/06 , B33Y10/00 , B33Y50/02 , B33Y80/00 , B64D15/12 , B64D33/08 , B64D43/02 , B64F5/00 , F28D15/0266 , F28D15/043 , F28D2021/0021 , G01P5/165 , G01P13/025
摘要： A heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment (25) includes a part (30, 31) intended to be arranged at the skin (27) of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.
摘要翻译： 一架旨在安排在飞机皮肤上的航空设备的加热。 设备（25）包括旨在布置在飞行器的皮肤（27）上的部分（30,31）和用于加热部件的元件。 加热元件包括热力循环，其包括传热流体循环的封闭回路，包括蒸发器（14）的闭合回路和附加部分中可能发生传热流体的冷凝以加热的区域。 在蒸发器（14）的外部，流体循环的回路由具有空的部分的管状通道形成。 至少部分设备由具有低导热性的材料制成。
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公开(公告)号：US07131612B2
公开(公告)日：2006-11-07
申请号：US10628368
申请日：2003-07-29
IPC分类号： B64D15/06
CPC分类号： F02C7/14 , B64D15/06 , B64D33/02 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , Y02T50/675
摘要： A nacelle for housing a gas turbine engine having a pressurized oil system for lubricating components thereof comprises an inlet lip defining a leading edge of the nacelle, the inlet lip having a conduit therein in fluid flow communication with the pressurized oil system of the gas turbine engine and defining an oil passage for circulation of pressurized engine oil therethrough. The conduit is in heat transfer communication with an outer surface of the inlet lip.
摘要翻译： 用于容纳具有用于润滑其部件的加压油系统的燃气涡轮发动机的机舱包括限定所述机舱的前缘的入口唇缘，所述入口唇缘具有与所述燃气涡轮发动机的加压油系统流体流动连通的导管 并且限定用于使加压发动机油循环的油通道。 导管与入口唇缘的外表面传热连通。
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公开(公告)号：US5681882A
公开(公告)日：1997-10-28
申请号：US65237
申请日：1993-05-20
IPC分类号： B64D15/06 , C08F16/14 , C08F20/26 , C08F20/28 , C08F220/28 , C08F290/06 , C08L29/10 , C08L71/02 , C08L101/00 , C08L101/12 , C09K3/18 , C08K5/05
CPC分类号： C08F290/062 , C09K3/18
摘要： An anti-icing fluid suitable for ground treatment of aircraft, being a glycol-based, aqueous solution containing a hydrophobe-bearing, macromonomer-containing polymer thickener in an amount of less than about 5 weight %. Thickening occurs predominantly by association among hydrophobe groups. Thickening may be enhanced by addition of a surfactant or other materials which act as co-thickeners. Use of this thickened fluid does not adversely affect airfoil lift characteristics during takeoff, because the fluid exhibits shear thinning and readily flows off the aircraft surfaces when exposed to wind shear during the aircraft's takeoff run.
摘要翻译： 一种适用于飞机地面处理的防冰液体，它是含有少于约5重量％量的含疏水物，含大分子单体的聚合物增稠剂的基于二醇的水溶液。 增稠主要通过疏水基团之间的结合发生。 可以通过加入作为共增稠剂的表面活性剂或其它材料来增强增稠。 这种增稠流体的使用不会对起飞期间的翼型升力特性造成不利影响，因为在飞机起飞运行期间暴露于风切变时，流体表现出剪切变稀并容易流出飞机表面。
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公开(公告)号：US3530881A
公开(公告)日：1970-09-29
申请号：US3530881D
申请日：1967-05-10
CPC分类号： B64D15/06 , F16L39/00 , G05D7/0186 , G05D11/02 , Y10T137/8593
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公开(公告)号：US20220212806A1
公开(公告)日：2022-07-07
申请号：US17699921
申请日：2022-03-21
申请人： SUBARU CORPORATION
发明人： Kazuaki KOTANI
摘要： According to one implementation, a propulsion system includes a rotor, a motor and an anti-icing mechanism. The rotor has blades. The motor rotates the rotor. The anti-icing mechanism deices the blades using heat generated by driving of the motor. Further, according to one implementation, an aircraft includes the above-mentioned propulsion system. Further, according to one implementation, an anti-icing method of a rotor having blades includes deicing the blades using heat generated by driving of a motor for rotating the rotor.
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20.发明授权公开(公告)号：US11214381B2
公开(公告)日：2022-01-04
申请号：US15227501
申请日：2016-08-03
发明人： Anthony Jones , Andre Julien , David Menheere , Jean Thomassin , Richard Ullyott , Daniel Van Den Hende
摘要： An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.
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