公开(公告)号：US08070092B2

公开(公告)日：2011-12-06

申请号：US12262428

申请日：2008-10-31

申请人： Bruce Dan Bouldin ,  Ricardo Burdisso

发明人： Bruce Dan Bouldin ,  Ricardo Burdisso

IPC分类号： B64C39/06

CPC分类号： B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D2033/0206

摘要： A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage's leading edge.

摘要翻译： 一种用于管道风扇无人机的用于抑制噪声的支柱支撑系统，包括：限定开口的管道风扇机身; 发动机纵向延伸穿过机身中的开口; 驱动机构，其可旋转地安装在所述发动机上，其中风扇安装在由所述开口限定的导管内的所述驱动机构上; 以及在所述风扇风扇机身和所述发动机之间延伸的多个支柱，每个支柱包括通过曲线连接部连接在一起的第一腿部和第二腿部，其中所述第一腿部连接到所述风扇风扇机身，并且所述第二腿部连接到所述发动机 ，其中所述多个支柱位于所述风扇的上游，其中，所述多个支柱中的每一个的所述第一支腿与所述风扇风扇机身之间的连接处在所述风扇风扇机身的前缘的突出部之外。

公开(公告)号：US5515444A

公开(公告)日：1996-05-07

申请号：US320153

申请日：1994-10-07

申请人： Ricardo Burdisso ,  Chris R. Fuller ,  Walter F. O'Brien ,  Russell H. Thomas ,  Mary E. Dungan

发明人： Ricardo Burdisso ,  Chris R. Fuller ,  Walter F. O'Brien ,  Russell H. Thomas ,  Mary E. Dungan

IPC分类号： F01N1/00 ,  F02C7/045 ,  G10K11/178 ,  G10K11/16

CPC分类号： G10K11/1786 ,  G10K11/1788 ,  F05B2260/962 ,  G10K2210/107 ,  G10K2210/112 ,  G10K2210/121 ,  G10K2210/1281 ,  G10K2210/1291 ,  G10K2210/3032 ,  G10K2210/3042 ,  G10K2210/3045 ,  G10K2210/3046 ,  G10K2210/3226 ,  G10K2210/32271 ,  G10K2210/3229 ,  G10K2210/32291 ,  G10K2210/511

摘要： An active noise control system using a compact sound source is effective to reduce aircraft engine duct noise. The fan noise from a turbofan engine is controlled using an adaptive filtered-x LMS algorithm. Single multi channel control systems are used to control the fan blade passage frequency (BPF) tone and the BPF tone and the first harmonic of the BPF tone for a plane wave excitation. A multi channel control system is used to control any spinning mode. The multi channel control system to control both fan tones and a high pressure compressor BPF tone simultaneously. In order to make active control of turbofan inlet noise a viable technology, a compact sound source is employed to generate the control field. This control field sound source consists of an array of identical thin, cylindrically curved panels with an inner radius of curvature corresponding to that of the engine inlet. These panels are flush mounted inside the inlet duct and sealed on all edges to prevent leakage around the panel and to minimize the aerodynamic losses created by the addition of the panels. Each panel is driven by one or more piezoelectric force transducers mounted on the surface of the panel. The response of the panel to excitation is maximized when it is driven at its resonance; therefore, the panel is designed such that its fundamental frequency is near the tone to be canceled, typically 2000-4000 Hz.

摘要翻译： 使用紧凑声源的主动噪声控制系统有效地减少飞机发动机管道噪声。 来自涡扇发动机的风扇噪声使用自适应滤波x LMS算法进行控制。 单个多通道控制系统用于控制风扇叶片通过频率（BPF）音调和BPF音调以及用于平面波激励的BPF音调的一次谐波。 多通道控制系统用于控制任何旋转模式。 多通道控制系统同时控制风扇音调和高压压缩机BPF音调。 为了积极控制涡轮风扇入口噪声是一项可行的技术，采用紧凑型声源来产生控制领域。 该控制场声源由相同的薄的圆柱形曲面的阵列组成，其内径曲率对应于发动机入口的曲率半径。 这些面板齐平地安装在入口管道的内部，并密封在所有边缘上，以防止面板周围的泄漏，并最大限度地减少通过添加面板而产生的空气动力学损失。 每个面板由安装在面板表面上的一个或多个压电力传感器驱动。 当它的共振被驱动时，面板对激发的响应最大化; 因此，面板被设计成使得其基本频率接近待消除的音调，通常为2000-4000Hz。

公开(公告)号：US20110001017A1

公开(公告)日：2011-01-06

申请号：US12330024

申请日：2008-12-08

申请人： Ricardo Burdisso

发明人： Ricardo Burdisso

IPC分类号： B64C29/00

CPC分类号： B64C39/024

摘要： A ducted fan air-vehicle having an air duct and a fan is described. The air duct includes an outer rim and an inner rim, and the fan is located within the air duct and rotates in a direction. The fan also includes a hub, a plurality of struts extending from the hub and positioned adjacent the outer rim of the fan, a plurality of stators extending from the hub and positioned adjacent the inner rim of the fan, and a plurality of rotor blades extending from the hub and positioned between the plurality of struts and the plurality of stators. The stators are lean in a plane of fan rotation and swept in a plane normal to fan rotation to create the optimum amount of noise reduction in the ducted fan air-vehicle.

摘要翻译： 描述了具有空气管道和风扇的管道风扇空气车辆。 风道包括外缘和内缘，风扇位于空气管道内并沿一个方向旋转。 所述风扇还包括轮毂，从所述轮毂延伸并且定位成邻近所述风扇的外缘的多个支柱;多个定子，其从所述轮毂延伸并且邻近所述风扇的内缘设置;以及多个定子，其延伸 并且定位在多个支柱和多个定子之间。 定子在风扇旋转平面内倾斜，并在垂直于风扇旋转的平面中扫掠，以在管道式风扇飞行器中产生最佳的噪音降低量。

公开(公告)号：US5355417A

公开(公告)日：1994-10-11

申请号：US964604

申请日：1992-10-21

申请人： Ricardo Burdisso ,  Chris R. Fuller ,  Walter F. O'Brien ,  Russell H. Thomas ,  Mary E. Dungan

发明人： Ricardo Burdisso ,  Chris R. Fuller ,  Walter F. O'Brien ,  Russell H. Thomas ,  Mary E. Dungan

IPC分类号： G10K11/178 ,  G10K11/16

CPC分类号： G10K11/1786 ,  G10K11/1788 ,  F05B2260/962 ,  G10K2210/107 ,  G10K2210/112 ,  G10K2210/121 ,  G10K2210/1281 ,  G10K2210/1291 ,  G10K2210/3032 ,  G10K2210/3042 ,  G10K2210/3045 ,  G10K2210/3046 ,  G10K2210/3226 ,  G10K2210/32271 ,  G10K2210/3229 ,  G10K2210/32291 ,  G10K2210/511

摘要： An active noise control system using a compact sound source is effective to reduce aircraft engine duct noise. The fan noise from a turbofan engine is controlled using an adaptive filtered-x LMS algorithm. Single multi channel control systems are used to control the fan blade passage frequency (BPF) tone and the BPF tone and the first harmonic of the BPF tone for a plane wave excitation. A multi channel control system is used to control any spinning mode. The multi channel control system to control both fan tones and a high pressure compressor BPF tone simultaneously. In order to make active control of turbofan inlet noise a viable technology, a compact sound source is employed to generate the control field. This control field sound source consists of an array of identical thin, cylindrically curved panels with an inner radius of curvature corresponding to that of the engine inlet. These panels are flush mounted inside the inlet duct and sealed on all edges to prevent leakage around the panel and to minimize the aerodynamic losses created by the addition of the panels. Each panel is driven by one or more piezoelectric force transducers mounted on the surface of the panel. The response of the panel to excitation is maximized when it is driven at its resonance; therefore, the panel is designed such that its fundamental frequency is near the tone to be canceled, typically 2000-4000 Hz.

摘要翻译： 使用紧凑声源的主动噪声控制系统有效地减少飞机发动机管道噪声。 来自涡扇发动机的风扇噪声使用自适应滤波x LMS算法进行控制。 单个多通道控制系统用于控制风扇叶片通过频率（BPF）音调和BPF音调以及用于平面波激励的BPF音调的一次谐波。 多通道控制系统用于控制任何旋转模式。 多通道控制系统同时控制风扇音调和高压压缩机BPF音调。 为了积极控制涡轮风扇入口噪声是一项可行的技术，采用紧凑型声源来产生控制领域。 该控制场声源由相同的薄的圆柱形曲面的阵列组成，其内径曲率对应于发动机入口的曲率半径。 这些面板齐平地安装在入口管道的内部，并密封在所有边缘上，以防止面板周围的泄漏，并最大限度地减少通过添加面板而产生的空气动力学损失。 每个面板由安装在面板表面上的一个或多个压电力传感器驱动。 当它的共振被驱动时，面板对激发的响应最大化; 因此，面板被设计成使得其基本频率接近待消除的音调，通常为2000-4000Hz。

公开(公告)号：US20100108809A1

公开(公告)日：2010-05-06

申请号：US12262428

申请日：2008-10-31

申请人： Bruce Dan Bouldin ,  Ricardo Burdisso

发明人： Bruce Dan Bouldin ,  Ricardo Burdisso

IPC分类号： B64C1/40

CPC分类号： B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  B64D2033/0206

摘要： A strut support system for a ducted fan unmanned aerial vehicle to suppress noise comprising: a ducted fan fuselage that defines an opening; an engine that extends longitudinally through the opening in the fuselage; a drive mechanism rotatably mounted to the engine, wherein a fan is mounted on the drive mechanism within a duct defined by the opening; and a plurality of struts extending between the ducted fan fuselage and the engine each comprising a first leg and a second leg joined together by a curvilinear junction, wherein the first leg is attached to the ducted fan fuselage and the second leg is attached to the engine, wherein the plurality of struts are positioned upstream of the fan, wherein the junction between the first leg of each of the plurality of struts and the ducted fan fuselage is outside the highlight of the ducted fan fuselage's leading edge.

摘要翻译： 一种用于管道风扇无人机的用于抑制噪声的支柱支撑系统，包括：限定开口的管道风扇机身; 发动机纵向延伸穿过机身中的开口; 驱动机构，其可旋转地安装在所述发动机上，其中风扇安装在由所述开口限定的导管内的所述驱动机构上; 以及在所述风扇风扇机身和所述发动机之间延伸的多个支柱，每个支柱包括通过曲线连接部连接在一起的第一腿部和第二腿部，其中所述第一腿部连接到所述风扇风扇机身，并且所述第二腿部连接到所述发动机 ，其中所述多个支柱位于所述风扇的上游，其中，所述多个支柱中的每一个的所述第一支腿与所述风扇风扇机身之间的连接处在所述风扇风扇机身的前缘的突出部之外。