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1. 发明申请

WO2009079046A3 SYSTEMS AND METHODS FOR CONTROL OF ENGINE EXHAUST FLOW 审中-公开
标题翻译：用于控制发动机排气流量的系统和方法
公开(公告)号：WO2009079046A3
公开(公告)日：2009-12-17
申请号：PCT/US2008076857
申请日：2008-09-18
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , GREGG ROBERT D III , CLARK ROGER W
发明人： SHMILOVICH ARVIN , YADLIN YORAM , GREGG ROBERT D III , CLARK ROGER W
IPC分类号： B64C23/06
CPC分类号： B64C21/04 , B64C9/38 , Y02T50/166
摘要： Coanda.Effect and lift produced along a surface of an airfoil are increased by- ducting (112) compressed fluid from the engine to the surface of the airfoil. An engine produces exhaust gases that are predominantly directed toward an aft end of the aircraft by a cowling (102) or other structure as an exhaust plume. One or more internal ducts extend (112) from the engine to the surface of the airfoil to thereby transmit a compressed fluid from the engine to the surface in order to suppress flow separation along the surface, thereby causing the engine exhaust flow to remain attached to the surface over a wider span. Such structures and techniques may find particular use in aircraft designed to exploit upper surface blowing (USB) techniques and structures for short takeoff and landing (STOL) performance.
摘要翻译：沿着翼面的表面产生的效应和升力通过将发动机的压缩流体（112）增加到翼型件的表面而增加。发动机产生主要通过整流罩（102）或其它结构作为排气羽流朝向飞行器后端的废气。一个或多个内部管道从发动机延伸（112）到翼型件的表面，从而将压缩流体从发动机传递到表面，以便抑制沿着表面的流动分离，从而使发动机排气流量保持附着于表面越宽越宽。这种结构和技术可以在设计用于利用上表面吹风（USB）技术和用于短起飞和着陆（STOL））性能的结构的飞机中发现。

2. 发明申请

WO2008057065A3 LIFT AUGMENTATION SYSTEM AND ASSOCIATED METHOD 审中-公开
标题翻译：提升系统及相关方法
公开(公告)号：WO2008057065A3
公开(公告)日：2008-09-25
申请号：PCT/US2006029092
申请日：2006-07-26
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W
IPC分类号： B64C21/02
CPC分类号： B64C9/16 , B64C9/22 , B64C21/025 , B64C2230/04 , B64C2230/06 , B64C2230/18 , Y02T50/166 , Y02T50/32 , Y02T50/44
摘要： A system and method for generating lift provided by a multi-element aircraft wing are provided. The system includes a main wing element (14), a slat (12) interconnected to the main wing element, and a flap (16) interconnected to the main wing element. The system also includes at least one port (s1, s2, ml, m2, m3, m4, m5, fl, f2, f9, f4, f5) defined in at least one of the slat, main wing element, and flap. In addition, the system includes at least one fluidic device operable to regulate fluid flow into and out of the at least one port to control boundary layer flow over at least one of the slat, main wing element, and flap.
摘要翻译：提供了一种用于产生由多元件飞机机翼提供的升降机的系统和方法。该系统包括主翼元件（14），与主翼元件互连的板条（12）和与主翼元件相互连接的挡板（16）。该系统还包括限定在板条，主翼元件和翼片中的至少一个中的至少一个端口（s1，s2，ml，m2，m3，m4，m5，fl，f2，f9，f4，f5）。此外，该系统包括至少一个流体装置，其可操作以调节进入和离开至少一个端口的流体流动，以控制边界层在板条，主翼元件和翼片中的至少一个上的流动。

3. 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。

4. 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。

5. 发明申请

WO2007021480A3 SYSTEM FOR AERODYNAMIC FLOWS AND ASSOCIATED METHOD 审中-公开
标题翻译：气动流量系统及相关方法
公开(公告)号：WO2007021480A3
公开(公告)日：2007-05-10
申请号：PCT/US2006029134
申请日：2006-07-26
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , MANLEY DAVID J
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W , MANLEY DAVID J
IPC分类号： B64C21/02
CPC分类号： B64C9/16 , B64C9/22 , B64C21/02 , B64C21/04 , B64C2230/04 , B64C2230/06 , Y02T50/166 , Y02T50/32
摘要： A system and method for controlling boundary layer flow over an aircraft wing are provided. The system includes at least one wing element (12, 14, 16) , and a plurality of ports (s1, s2, m2, m3, fl, f2) defined in the wing element and in fluid communication with one another. The system also includes at least one fluidic device operable to continuously ingest the fluid through at least one of the ports and eject the fluid out of at least one other port to control boundary layer flow of the fluid over the wing element .
摘要翻译：提供一种用于控制飞机机翼上的边界层流动的系统和方法。该系统包括至少一个翼元件（12,14,16）和限定在机翼元件中并且彼此流体连通的多个端口（s1，s2，m2，m3，f1，f2）。该系统还包括至少一个流体装置，其可操作以通过至少一个端口连续摄取流体并将流体从至少一个其它端口排出，以控制流体在翼元件上的边界层流动。

6. 发明申请

WO2008054500A2 INTEGRATED ENGINE EXHAUST SYSTEMS AND METHODS FOR DRAG AND THERMAL STRESS REDUCTION 审中-公开
标题翻译：集成式发动机排气系统及其应用和减少热应力的方法
公开(公告)号：WO2008054500A2
公开(公告)日：2008-05-08
申请号：PCT/US2007008696
申请日：2007-04-06
申请人： BOEING CO , SHMILOVICH ARVIN , YADLIN YORAM , SMITH DAVID M , CLARK ROGER W
发明人： SHMILOVICH ARVIN , YADLIN YORAM , SMITH DAVID M , CLARK ROGER W
CPC分类号： B64D33/06 , F02K1/06 , F02K3/06 , F05D2250/14 , Y02T50/671
摘要： Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation configured to be mounted on a wing assembly of an aircraft. The engine installation includes an engine, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle configured to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle that exhausts a core exhaust flow, and an outer nozzle that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.
摘要翻译：公开了用于减少阻力和热负荷的集成发动机排气系统和方法。在一个实施例中，推进系统包括构造成安装在飞行器的翼组件上的发动机装置。发动机安装包括发动机和可操作地联接到发动机的排气系统。排气系统包括至少一个喷嘴，其构造成排出来自发动机的排气流。喷嘴包括可变部分，其被配置为将喷嘴的出口孔从第一形状改变到第二形状，以改变靠近翼组件的喷嘴流场的至少一部分的流场形状，从而减少阻力和机翼组件上的热负荷。在另一个实施例中，排气系统包括排出核心排气流的内部喷嘴和排出二次排气流的外部喷嘴，外部喷嘴具有可变部分，以改变外部喷嘴的出口孔径。

7. 发明专利

AU2011233687A1 Low noise wing slat system with deployable wing leading edge elements 未知
公开(公告)号：AU2011233687A1
公开(公告)日：2012-09-06
申请号：AU2011233687
申请日：2011-02-28
申请人： BOEING CO
发明人： SHMILOVICH ARVIN , YADLIN YORAM
IPC分类号： B64C3/50 , B64C9/24
摘要： Concepts and technologies described herein provide for a low noise aircraft wing slat system. According to one aspect of the disclosure provided herein, a cove-filled wing slat (202) is used in conjunction with a moveable leading edge element (402, 502) of an aircraft wing to provide a high lift system. The moveable leading edge element may include a one-piece (402) or two-piece panel (502) that retracts within the aircraft wing to accommodate the cove-filled slat in the stowed position. Upon deployment of the cove-filled slat, the moveable leading edge element deploys outward to create a continuous outer mold line shape with the wing.

8. 发明专利

CA2646629C INTEGRATED ENGINE EXHAUST SYSTEMS AND METHODS FOR DRAG AND THERMAL STRESS REDUCTION 未知
公开(公告)号：CA2646629C
公开(公告)日：2011-01-04
申请号：CA2646629
申请日：2007-04-06
申请人： BOEING CO
发明人： SHMILOVICH ARVIN , YADLIN YORAM , SMITH DAVID M , CLARK ROGER W
IPC分类号： B64D33/04 , F02K1/06 , F02K3/06
摘要： Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation 120 configured to be mounted on a wing assembly 104 of an aircraft. The engine installation includes an engine 122, and an exhaust system operatively coupled to the engine. The exhaust system includes at least one nozzle 126 configured to exhaust an exhaust flow from the engine. The nozzle includes a variable portion configured to vary an exit aperture of the nozzle from a first shape to a second shape to change a flowfield shape of at least a portion of the nozzle flowfield proximate the wing assembly, thereby reducing at least one of drag and thermal loading on the wing assembly. In a further embodiment, the exhaust system includes an inner nozzle 126 that ' exhausts a core exhaust flow, and an outer nozzle 128 that exhausts a secondary exhaust flow, the outer nozzle having the variable portion configured to vary the exit aperture of the outer nozzle.

9. 发明专利

CA2593953C ACTIVE SYSTEMS AND METHODS FOR CONTROLLING AN AIRFOIL VORTEX 未知
公开(公告)号：CA2593953C
公开(公告)日：2010-09-28
申请号：CA2593953
申请日：2007-07-17
申请人： BOEING CO
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W
IPC分类号： B64C23/00 , B64C3/00 , B64C15/14 , B64C21/04 , F15D1/00
摘要： Active systems and methods for controlling aircraft vortices 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 an orifice positioned to direct a flow of fluid outwardly from the tip, an actuator operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip, and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.

10. 发明专利

DE602007005424D1 未知
公开(公告)号：DE602007005424D1
公开(公告)日：2010-05-06
申请号：DE602007005424
申请日：2007-07-25
申请人： BOEING CO
发明人： SHMILOVICH ARVIN , YADLIN YORAM , CLARK ROGER W
IPC分类号： B64C23/06
摘要： Active systems and methods for controlling aircraft vortices are disclosed. An apparatus (50) in accordance with one embodiment is directed to an aircraft system that includes an airfoil (14) having first and second oppositely facing flow surfaces (23,24) and a tip (20). The system can further include a vortex dissipation device (50) carried by the airfoil (14), with the vortex dissipation device (14) including an orifice (66) positioned to direct a flow of fluid outwardly from the tip (20), an actuator (92) operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip (20), and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.

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