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1. 发明申请

WO2008051269A3 SYSTEMS AND METHODS FOR DESTABILIZING AN AIRFOIL VORTEX 审中-公开
公开(公告)号：WO2008051269A3
公开(公告)日：2008-05-02
申请号：PCT/US2007/005253
申请日：2007-03-02
申请人： THE BOEING COMPANY , SHMILOVICH, Arvin , YADLIN, Yoram , CLARK, Roger, W. , LEOPOLD, Donald, H.
发明人： SHMILOVICH, Arvin , YADLIN, Yoram , CLARK, Roger, W. , LEOPOLD, Donald, H.
IPC分类号： B64C23/06
摘要： Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device (2230) carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle (1590), a valve device (2231), and a controller (2233). The fluid flow nozzle can be coupleable to a source of pressurized fluid (2232) 'and can include an orifice (1591) positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.

2. 发明申请

WO2008051269B1 SYSTEMS AND METHODS FOR DESTABILIZING AN AIRFOIL VORTEX 审中-公开
标题翻译：用于减轻AIRFOIL VORTEX的系统和方法
公开(公告)号：WO2008051269B1
公开(公告)日：2008-09-12
申请号：PCT/US2007005253
申请日：2007-03-02
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , LEOPOLD DONALD H
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , LEOPOLD DONALD H
IPC分类号： B64C23/06
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device (2230) carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle (1590), a valve device (2231), and a controller (2233). The fluid flow nozzle can be coupleable to a source of pressurized fluid (2232) 'and can include an orifice (1591) positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.
摘要翻译：公开了用于受控拖尾尾流的装置和方法。根据一个实施例的装置涉及飞行器系统，该飞行器系统包括具有第一和第二相对面的流动表面和尖端的翼型件（14）。该系统还可以包括由翼型件携带的涡流消散装置（2230），其中涡流消散装置包括流体流动喷嘴（1590），阀装置（2231）和控制器（2233）。流体流动喷嘴可以耦合到加压流体源（2232）'，并且可以包括定位成将流体流从尖端向外引导的孔口（1591）。阀装置可以与流体流动喷嘴流体连通地联接，以选择性地控制通过孔口的流动。控制器可以联接到阀装置以引导阀装置的操作。因此，可以启动涡流消散装置以加速涡流（例如，翼尖涡流）在其产生之后消散的速率。

3. 发明申请

WO2008051269A2 SYSTEMS AND METHODS FOR DESTABILIZING AN AIRFOIL VORTEX 审中-公开
标题翻译：用于减轻AIRFOIL VORTEX的系统和方法
公开(公告)号：WO2008051269A2
公开(公告)日：2008-05-02
申请号：PCT/US2007005253
申请日：2007-03-02
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , LEOPOLD DONALD H
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , LEOPOLD DONALD H
IPC分类号： B64C23/06
CPC分类号： B64C23/076 , B64C23/065 , Y02T50/164
摘要： Apparatuses and methods for the controlled trailing wake flows are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including a fluid flow nozzle, a valve device, and a controller. The fluid flow nozzle can be coupleable to a source of pressurized fluid and can include an orifice positioned to direct a flow of fluid outwardly from the tip. The valve device can be coupled in fluid communication with the fluid flow nozzle to selectively control the flow passing through the orifice. The controller can be coupled to the valve device to direct the operation of the valve device. Accordingly, the vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated.
摘要翻译：公开了用于受控拖尾尾流的装置和方法。根据一个实施例的装置涉及一种飞行器系统，其包括具有第一和第二相对面向的流动表面和尖端的翼型件。该系统还可以包括由翼型件携带的涡流消散装置，涡流消散装置包括流体流动喷嘴，阀装置和控制器。流体流动喷嘴可以耦合到加压流体源，并且可以包括定位成将流体流从尖端向外引导的孔。阀装置可以与流体流动喷嘴流体连通地联接，以选择性地控制通过孔口的流动。控制器可以联接到阀装置以引导阀装置的操作。因此，可以启动涡流消散装置以加速涡流（例如，翼尖涡流）在其产生之后消散的速率。

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