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1. 发明申请

US20110180146A1 MICROVANES FOR AIRCRAFT AFT BODY DRAG REDUCTION 有权
标题翻译：飞机机身减速机的微型飞机
公开(公告)号：US20110180146A1
公开(公告)日：2011-07-28
申请号：US12406819
申请日：2009-03-18
申请人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
发明人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
IPC分类号： B64C1/38
CPC分类号： B64C23/06 , B64C1/0009 , B64C2230/26 , F15D1/0035 , Y02T50/12 , Y02T50/162 , Y02T50/166 , Y10T137/0318
摘要： The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.
摘要翻译：本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度，减阻元件被定位。

2. 发明授权

US08226038B2 Microvanes for aircraft aft body drag reduction 有权
标题翻译：飞机尾灯微型车身减阻
公开(公告)号：US08226038B2
公开(公告)日：2012-07-24
申请号：US12406819
申请日：2009-03-18
申请人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
发明人： Brian R. Smith , Brant H. Maines , Edward C. Ma , Edward A. DiGirolamo , Patrick J. Yagle
IPC分类号： B64C1/38
CPC分类号： B64C23/06 , B64C1/0009 , B64C2230/26 , F15D1/0035 , Y02T50/12 , Y02T50/162 , Y02T50/166 , Y10T137/0318
摘要： The invention relates a method and apparatus for reducing the drag on aircraft, particularly aircraft with an upswept afterbody. The method includes the steps of positioning a plurality of drag reducing elements on the fuselage of the aircraft, wherein the drag reducing elements are positioned on the fuselage from a position at the breakline of the fuselage and extending toward the tail of the aircraft. In preferred embodiments, each of the plurality of drag reducing elements is positioned such that a first end of the drag reducing element is at an angle of between approximately 15 and 35° nose up relative to the flow of air about the fuselage at the location where the drag reducing element is positioned.
摘要翻译：本发明涉及一种用于减少飞机上的阻力的方法和装置，特别是具有上升后的身体的飞机。该方法包括以下步骤：将多个减阻元件放置在飞行器的机身上，其中减阻元件从机身的断线处的位置定位在机身上并朝向飞行器的尾部延伸。在优选实施例中，多个减阻元件中的每一个被定位成使得减阻元件的第一端相对于在机身周围的空气流过大约15和35°之间的角度，减阻元件被定位。

3. 发明授权

US08402738B2 Flow control redistribution to mitigate high cycle fatigue 有权
标题翻译：流量控制重新分配以减轻高周期疲劳
公开(公告)号：US08402738B2
公开(公告)日：2013-03-26
申请号：US12497225
申请日：2009-07-02
申请人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
发明人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
IPC分类号： B63H11/00
CPC分类号： F02C7/04 , F05D2270/18 , Y10S415/914 , Y10T137/0536 , Y10T137/0645
摘要： A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
摘要翻译：公开了可操作以改善发动机入口内的压力恢复和/或变形的方法。第一流体流被提供给初级喷射涡流发生器，其可操作以将流体以第一注入速率注入到入口内的主流体流的边界层中。第二流体流以第二喷射速率被二次喷射涡流发生器注入到主流体流的边界层中。以第一注射速率和第二注射速率注入的流体可操作以在边界层内引发二次流动结构。然后，这些二次闭合结构可操作以改善或操纵入口的压力恢复。在特定发动机条件下，该方法可以重新分配第一喷射速率和第二喷射速率的比率，以便在特定的发动机条件下改善进气口的压力恢复和/或变形。

4. 发明申请

US20100003129A1 Flow control redistribution to mitigate high cycle fatigue 有权
标题翻译：流量控制重新分配以减轻高周期疲劳
公开(公告)号：US20100003129A1
公开(公告)日：2010-01-07
申请号：US12497225
申请日：2009-07-02
申请人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
发明人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
IPC分类号： F01D25/24
CPC分类号： F02C7/04 , F05D2270/18 , Y10S415/914 , Y10T137/0536 , Y10T137/0645
摘要： The present invention provides a method operable to improve pressure recovery and/or distortion within engine inlet. This method involves providing a first fluid flow to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow. The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions. Such engine conditions may be associated with a natural blade frequency of the engine at a particular speed. Embodiments of the invention allow blade vibration problems associated with engine operation at particular speeds to be solved without adding damping or increasing blade strength to change the natural frequency of the blades, thereby reducing weight and improving engine performance.
摘要翻译：本发明提供了一种可以改进发动机入口内的压力恢复和/或变形的方法。该方法包括向初级喷射涡流发生器提供第一流体流，其可操作以将流体以第一注入速率注入入口内的主流体流的边界层。第二流体流以第二喷射速率被二次喷射涡流发生器注入到主流体流的边界层中。以第一注射速率和第二注射速率注入的流体可操作以在边界层内引发二次流动结构。然后，这些二次闭合结构可操作以改善或操纵入口的压力恢复。在特定发动机条件下，该方法可以重新分配第一喷射速率和第二喷射速率的比率，以便在特定的发动机条件下改善进气口的压力恢复和/或变形。这种发动机条件可以以特定速度与发动机的天然叶片频率相关联。本发明的实施例允许解决与特定速度下的发动机操作相关的叶片振动问题，而不增加阻尼或增加叶片强度以改变叶片的固有频率，从而减轻重量并改善发动机性能。

5. 发明授权

US07617670B2 Flow control redistribution to mitigate high cycle fatigue 有权
标题翻译：流量控制重新分配以减轻高周期疲劳
公开(公告)号：US07617670B2
公开(公告)日：2009-11-17
申请号：US11418336
申请日：2006-05-04
申请人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
发明人： Philip P. Truax , Daniel N. Miller , Edward C. Ma
IPC分类号： F02K3/00
CPC分类号： F02C7/04 , F05D2270/18 , Y10S415/914 , Y10T137/0536 , Y10T137/0645
摘要： A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.
摘要翻译：公开了可操作以改善发动机入口内的压力恢复和/或变形的方法。第一流体流被提供给初级喷射涡流发生器，其可操作以将流体以第一注入速率注入到入口内的主流体流的边界层中。第二流体流以第二注射速率被二次喷射涡流发生器注入到主流体流的边界层中。以第一注射速率注入的流体和第二注射速率可操作以在第二注射速率边界层。然后，这些二次闭合结构可操作以改善或操纵入口的压力恢复。在特定发动机条件下，该方法可以重新分配第一喷射速率和第二喷射速率的比率，以便在特定的发动机条件下改善进气口的压力恢复和/或变形。

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