专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08702042B2 Flow body, in particular for aircraft 有权
标题翻译：流体，特别是飞机
公开(公告)号：US08702042B2
公开(公告)日：2014-04-22
申请号：US13441944
申请日：2012-04-09
申请人： Martin Gerber , Geza Schrauf
发明人： Martin Gerber , Geza Schrauf
IPC分类号： B64C21/02
CPC分类号： B64C21/06 , B64C2230/04 , B64C2230/22 , B64D2033/0226 , Y02T50/166 , Y10T137/0536 , Y10T137/6906
摘要： A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.
摘要翻译：公开了流体，特别是用于飞行器。流体包括以流体在冲击流动方向上以预定方式冲击的外侧，流体在其外侧具有至少一个流量控制装置，其包括布置在外部的至少一个部分中的微穿孔至少一个连接通道经由至少一个吸入室与微穿孔连通，因此流过微穿孔的流体经由吸入室流入连接通道，至少一个抽吸装置具有与连接的第一入口连通通道，第二入口与至少一个冲压流体进料管线连通，其中柱塞流体进料管线位于流动体的与流动体的冲击流动方向相反的区域中，以及用于排出流体的出口装置。

2. 发明申请

US20130025727A1 FLOW BODY, IN PARTICULAR FOR AIRCRAFT 有权
标题翻译：流体，特别是飞机
公开(公告)号：US20130025727A1
公开(公告)日：2013-01-31
申请号：US13441944
申请日：2012-04-09
申请人： Martin Gerber , Geza Schrauf
发明人： Martin Gerber , Geza Schrauf
IPC分类号： B64C21/06
CPC分类号： B64C21/06 , B64C2230/04 , B64C2230/22 , B64D2033/0226 , Y02T50/166 , Y10T137/0536 , Y10T137/6906
摘要： A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.
摘要翻译：公开了流体，特别是用于飞行器。流体包括以流体在冲击流动方向上以预定方式冲击的外侧，流体在其外侧具有至少一个流量控制装置，其包括布置在外部的至少一个部分中的微穿孔至少一个连接通道经由至少一个吸入室与微穿孔连通，因此流过微穿孔的流体经由吸入室流入连接通道，至少一个抽吸装置具有与连接的第一入口连通通道，第二入口与至少一个冲压流体进料管线连通，其中柱塞流体进料管线位于流动体的与流动体的冲击流动方向相反的区域中，以及用于排出流体的出口装置。

3. 发明授权

US08191834B2 Cooling system on the basis of suction of a boundary layer 有权
标题翻译：基于吸附边界层的冷却系统
公开(公告)号：US08191834B2
公开(公告)日：2012-06-05
申请号：US12148953
申请日：2008-04-23
申请人： Andreas Westenberger , Martin Arendt , Till Marquardt , Lars Frahm , Geza Schrauf
发明人： Andreas Westenberger , Martin Arendt , Till Marquardt , Lars Frahm , Geza Schrauf
IPC分类号： B64C21/06
CPC分类号： B64C21/08 , B64D2013/0622 , Y02T50/166 , Y02T50/56
摘要： A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.
摘要翻译：飞机上的冷却系统包括用于通过抽吸除去边界层的装置和通过抽吸除去的边界层空气流过的热交换器。取决于飞行阶段，通过冲压空气通道的冷却可以减少或完全停止，从而可以减少飞行器的空气阻力并因此降低燃料消耗。

4. 发明授权

US07757994B2 Method and device for suctioning the boundary layer 有权
标题翻译：吸附边界层的方法和装置
公开(公告)号：US07757994B2
公开(公告)日：2010-07-20
申请号：US10596912
申请日：2004-12-22
申请人： Geza Schrauf
发明人： Geza Schrauf
IPC分类号： B64C21/06
CPC分类号： B64C21/025 , B64D2013/0622 , Y02T50/166 , Y02T50/56
摘要： A method for suctioning the boundary layer at the surface (1) of an aircraft having an air-conditioning system (4), at whose flow-critical points of the surface multiple suction openings (2) are provided, the air quantity suctioned via these being discharged to the atmosphere again via at least one outlet (7) placed in a way favorable for flow, the air quantity suctioned from the surface (1) being fed to the air-conditioning system (4) of the aircraft, via whose outlet (7) the air quantity suctioned is discharged to the atmosphere together with the exhaust air of the air-conditioning system (4), to reduce flow losses.
摘要翻译：一种用于在具有空调系统（4）的飞机的表面（1）处抽吸边界层的方法，其中设置有表面多个吸入口（2）的流动临界点，经由这些吸入口通过以有利于流动的方式放置的至少一个出口（7）再次排放到大气中，从表面（1）吸入的空气量通过其出口被供给到飞行器的空调系统（4）（7）抽吸的空气量与空调系统（4）的排气一起排放到大气中，以减少流量损失。

5. 发明申请

US20090020653A1 METHOD AND DEVICE FOR SUCTIONING THE BOUNDARY LAYER 有权
标题翻译：用于消除边界层的方法和装置
公开(公告)号：US20090020653A1
公开(公告)日：2009-01-22
申请号：US10596912
申请日：2004-12-22
申请人： Geza Schrauf
发明人： Geza Schrauf
IPC分类号： B64C21/06 , B64D13/06 , B64C21/02 , B64D13/08
CPC分类号： B64C21/025 , B64D2013/0622 , Y02T50/166 , Y02T50/56
摘要： A method for suctioning the boundary layer at the surface (1) of an aircraft having an air-conditioning system (4), at whose flow-critical points of the surface multiple suction openings (2) are provided, the air quantity suctioned via these being discharged to the atmosphere again via at least one outlet (7) placed in a way favorable for flow, the air quantity suctioned from the surface (1) being fed to the air-conditioning system (4) of the aircraft, via whose outlet (7) the air quantity suctioned is discharged to the atmosphere together with the exhaust air of the air-conditioning system (4), to reduce flow losses.
摘要翻译：一种用于在具有空调系统（4）的飞机的表面（1）处抽吸边界层的方法，其中设置有表面多个吸入口（2）的流动临界点，经由这些吸入口通过以有利于流动的方式放置的至少一个出口（7）再次排放到大气中，从表面（1）吸入的空气量通过其出口被供给到飞行器的空调系统（4）（7）抽吸的空气量与空调系统（4）的排气一起排放到大气中，以减少流量损失。

6. 发明申请

US20090014593A1 Cooling system on the basis of suction of a boundary layer 有权
标题翻译：基于吸附边界层的冷却系统
公开(公告)号：US20090014593A1
公开(公告)日：2009-01-15
申请号：US12148953
申请日：2008-04-23
申请人： Andreas Westenberger , Martin Arendt , Till Marquardt , Lars Frahm , Geza Schrauf
发明人： Andreas Westenberger , Martin Arendt , Till Marquardt , Lars Frahm , Geza Schrauf
IPC分类号： B64C21/06 , F28D15/00
CPC分类号： B64C21/08 , B64D2013/0622 , Y02T50/166 , Y02T50/56
摘要： A cooling system on board an aircraft includes a device for removing by suction a boundary layer, and a heat exchanger through which flows the boundary layer air that has been removed by suction. Cooling by way of a ram air channel can be reduced or entirely stopped, depending on the flight phase, such that the air drag of the aircraft and thus the fuel consumption can be reduced.
摘要翻译：飞机上的冷却系统包括用于通过抽吸除去边界层的装置和通过抽吸除去的边界层空气流过的热交换器。取决于飞行阶段，通过冲压空气通道的冷却可以减少或完全停止，从而可以减少飞行器的空气阻力并因此降低燃料消耗。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式