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公开(公告)号：US5662136A
公开(公告)日：1997-09-02
申请号：US498489
申请日：1995-09-11
申请人： Tadeusz M. Drzewiecki , John B. Niemczuk , Christopher R. Fuller , Russell H. Thomas , Ricardo A. Burdisso
发明人： Tadeusz M. Drzewiecki , John B. Niemczuk , Christopher R. Fuller , Russell H. Thomas , Ricardo A. Burdisso
IPC分类号： G10K11/08 , G10K11/178 , F15C1/04 , F15C1/12
CPC分类号： G10K11/08 , G10K11/1788 , G10K2210/121 , G10K2210/1281 , G10K2210/32121 , Y10T137/0396 , Y10T137/2196
摘要： Reduction or cancellation of acoustic noise is achieved by providing an amplified, oppositely phased version of the noise by means of an acousto-fluidic amplifier. The amplified acoustic output noise is delivered through an impedance matching horn in destructively interfering relation with the original noise. Depending on the acoustic noise source and its spatial distribution, the acousto-fluidic amplifier may be a single stage amplifier or multiple stages connected in parallel and/or cascade, with output horns spatially distributed to have the maximum cancellation effect. Sensed noise, prior to fluidic amplification, may be processed in a manner to effect feedback or feedforward control of the amplified acoustic output signals.
摘要翻译： 通过声流放大器提供噪声放大的相反阶段版本来实现声学噪声的减少或消除。 放大的声输出噪声通过阻抗匹配喇叭与原始噪声具有破坏性干扰关系。 取决于声学噪声源及其空间分布，声流放大器可以是单级放大器或并联和/或级联连接的多级放大器，输出喇叭在空间上分布以具有最大的消除效果。 在流体放大之前的感测噪声可以以对所放大的声输出信号进行反馈或前馈控制的方式进行处理。
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公开(公告)号：US08651429B2
公开(公告)日：2014-02-18
申请号：US13214453
申请日：2011-08-22
申请人： Michael J Czech , Russell H. Thomas
发明人： Michael J Czech , Russell H. Thomas
CPC分类号： B64C9/18
摘要： An aircraft system includes a wing and a trailing edge device coupled to the wing. The trailing edge device is movable relative to the wing, and includes a leading edge and a trailing edge having a center flap portion and a plurality of outer edge portions integrally combined with the center flap portion such that the center flap portion is shorter in width than that of outer edge portions.
摘要翻译： 飞行器系统包括机翼和联接到机翼的后缘装置。 后缘装置相对于机翼可移动，并且包括前缘和后缘，该前缘和后缘具有中心翼片部分和与中心翼片部分整体结合的多个外边缘部分，使得中心翼片部分的宽度比 外边缘部分。
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3.发明申请Jet Engine Nozzle Exit Configurations, Including Projections Oriented Relative To Pylons, and Associated Systems and Methods 有权喷气发动机喷嘴出口配置，包括相对于塔架的投影，以及相关系统和方法公开(公告)号：US20080272228A1
公开(公告)日：2008-11-06
申请号：US11836517
申请日：2007-08-09
申请人： Vinod G. Mengle , Russell H. Thomas
发明人： Vinod G. Mengle , Russell H. Thomas
IPC分类号： B64D27/16
CPC分类号： B64D33/06 , B64D29/02 , B64D33/04 , F02K1/386 , F02K1/40 , F02K1/46 , F05D2250/11 , F05D2260/96 , Y02T50/671
摘要： Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.
摘要翻译： 公开了喷嘴出口配置和相关系统和方法。 根据一个实施例的飞行器系统包括具有内部流动表面和出口孔的喷气发动机排气喷嘴，其中出口孔具有包括沿向后方向延伸的多个突起的周边。 单个相邻突起的后部彼此间隔开间隔，并且多个的几何特征可以沿着周边的至少一部分以单调方式改变。 支撑塔和/或相关隔热罩附近的突出物可以具有特定的构造，包括比其它突起更大的流动浸没。
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公开(公告)号：US08876043B2
公开(公告)日：2014-11-04
申请号：US13214469
申请日：2011-08-22
CPC分类号： B64D33/06
摘要： The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.
摘要翻译： 飞机排气引擎喷嘴系统包括风扇喷嘴，用于接收来自布置在飞机机身表面上方的发动机附近的风扇的风扇流，设置在风扇喷嘴内并接收发动机芯流的芯喷嘴和支架 结构连接到核心喷嘴并且结构地附接到机身表面以将发动机固定到飞机上。
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公开(公告)号：US20120068011A1
公开(公告)日：2012-03-22
申请号：US13214481
申请日：2011-08-22
CPC分类号： B64C7/02 , B64C21/04 , B64C21/08 , B64C2220/00 , B64C2230/04 , B64C2230/06 , B64C2230/14 , B64C2230/16 , B64D27/18 , B64D27/26 , Y02T50/166
摘要： An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.
摘要翻译： 用于飞行器的主动式塔式噪音控制系统包括将发动机系统与飞行器的机身表面连接并具有至少一个孔以供应通过其中的气体或流体的塔架结构，连接到塔架结构以吸入气体的进气部分 或流体，经由多个管道与进气部分连接的调节器，以调节气体或流体的压力;形成在塔架结构内并与调节器连接的增压室，并且被构造成接收被调节的气体或流体 通过调节器和与充气室连通的多个喷射器以主动地将气体或流体喷射通过塔架结构的多个孔。
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公开(公告)号：US08015819B2
公开(公告)日：2011-09-13
申请号：US11536790
申请日：2006-09-29
申请人： Russell H. Thomas , Kevin W. Kinzie
发明人： Russell H. Thomas , Kevin W. Kinzie
IPC分类号： F02K1/00
CPC分类号： F02K1/34 , B64D33/06 , F02K1/46 , F05D2250/70 , F05D2260/232 , F05D2260/60 , Y02T50/675
摘要： Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.
摘要翻译： 在与喷气发动机相关联的一个或多个喷嘴的后缘处或朝向与喷气发动机相关联的一个或多个喷嘴的后缘处的喷射口是可以选择性地将水流排放到喷嘴流动流中的注入口，以便以类似于机械设置的方式增加湍流 人字纹已经在已知的艺术中完成。 与已知技术的机械设置的人字形不同，可以确保流体流动，从而提高发动机效率。 可以使各种流动模式，水压力，孔口设计或其他因素可操作以提供期望的性能特征。
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7.发明授权Active control of aircraft engine inlet noise using compact sound sources and distributed error sensors 失效使用紧凑型声源和分布式误差传感器主动控制飞机发动机进气噪声
公开(公告)号：US5515444A
公开(公告)日：1996-05-07
申请号：US320153
申请日：1994-10-07
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。
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公开(公告)号：US20120061525A1
公开(公告)日：2012-03-15
申请号：US13214453
申请日：2011-08-22
CPC分类号： B64C9/18
摘要： An aircraft system includes a wing and a trailing edge device coupled to the wing. The trailing edge device is movable relative to the wing, and includes a leading edge and a trailing edge having a center flap portion and a plurality of outer edge portions integrally combined with the center flap portion such that the center flap portion is shorter in width than that of outer edge portions.
摘要翻译： 飞行器系统包括机翼和联接到机翼的后缘装置。 后缘装置相对于机翼可移动，并且包括前缘和后缘，该前缘和后缘具有中心翼片部分和与中心翼片部分整体结合的多个外边缘部分，使得中心翼片部分的宽度比 外边缘部分。
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公开(公告)号：US20120061510A1
公开(公告)日：2012-03-15
申请号：US13214469
申请日：2011-08-22
CPC分类号： B64D33/06
摘要： The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.
摘要翻译： 飞机排气引擎喷嘴系统包括风扇喷嘴，用于接收来自布置在飞机机身表面上方的发动机附近的风扇的风扇流，设置在风扇喷嘴内并接收发动机芯流的芯喷嘴和支架 结构连接到核心喷嘴并且结构地附接到机身表面以将发动机固定到飞机上。
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公开(公告)号：US20080078159A1
公开(公告)日：2008-04-03
申请号：US11536790
申请日：2006-09-29
申请人： Russell H. Thomas , Kevin W. Kinzie
发明人： Russell H. Thomas , Kevin W. Kinzie
IPC分类号： F02C7/08
CPC分类号： F02K1/34 , B64D33/06 , F02K1/46 , F05D2250/70 , F05D2260/232 , F05D2260/60 , Y02T50/675
摘要： Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.
摘要翻译： 在与喷气发动机相关联的一个或多个喷嘴的后缘处或朝向与喷气发动机相关联的一个或多个喷嘴的后缘处的喷射口是可以选择性地将水流排放到喷嘴流动流中的注入口，以便以类似于机械设置的方式增加湍流 人字纹已经在已知的艺术中完成。 与已知技术的机械设置的人字形不同，可以确保流体流动，从而提高发动机效率。 可以使各种流动模式，水压力，孔口设计或其他因素可操作以提供期望的性能特征。
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