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    Serrated nozzle trailing edge for exhaust noise suppression
    1.
    发明授权
    Serrated nozzle trailing edge for exhaust noise suppression 有权
    锯齿喷嘴后缘用于排气噪声抑制

    公开(公告)号：US07543452B2

    公开(公告)日：2009-06-09

    申请号：US11200616

    申请日：2005-08-10

    申请人： Ramons Andris Reba ,  Brian Ernest Wake ,  Satish Narayanan ,  Thierry Maeder

    发明人： Ramons Andris Reba ,  Brian Ernest Wake ,  Satish Narayanan ,  Thierry Maeder

    IPC分类号： F02K1/00

    CPC分类号： F02K1/40 ,  F02K1/386 ,  F02K1/46 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2260/96

    摘要： A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining exit portion. The base portion is typically generally frustoconical in shape and includes an arcuate contour in an axial direction. The exit portion includes undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges. One of the lobe and trough trailing edges are recessed from the other of the lobe and trough trailing edges in a generally axial direction. The other of the lobe and trough trailing edges form apexes with the apexes provided on tabs. The troughs extend radially inward in the axial direction towards the trough trailing edges.

    摘要翻译： 用于燃气涡轮发动机的喷嘴在芯和/或风扇排气流喷嘴上设置有起伏。 环形壁限定流体流动通道并且包括基部和相邻的出口部分。 基部通常在形状上通常为截头圆锥形，并且在轴向方向上包括弧形轮廓。 出口部分包括在大致径向方向上的波纹，其提供每个分别包括后缘的波瓣和波谷。 叶片和槽的后缘中的一个在大致轴向方向上从另一个叶片和槽的后缘凹入。 另一个叶片和槽尾缘形成顶点，顶点设在翼片上。 槽沿着轴向朝向槽的后缘径向向内延伸。

    Serrated nozzle trailing edge for exhaust noise suppression
    2.
    发明申请
    Serrated nozzle trailing edge for exhaust noise suppression 有权
    锯齿喷嘴后缘用于排气噪声抑制

    公开(公告)号：US20070033922A1

    公开(公告)日：2007-02-15

    申请号：US11200616

    申请日：2005-08-10

    申请人： Ramons Reba ,  Brian Wake ,  Satish Narayanan ,  Thierry Maeder

    发明人： Ramons Reba ,  Brian Wake ,  Satish Narayanan ,  Thierry Maeder

    IPC分类号： F02K1/38

    CPC分类号： F02K1/40 ,  F02K1/386 ,  F02K1/46 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2260/96

    摘要： A nozzle for a gas turbine engine is provided with undulations on a core and/or fan exhaust flow nozzle. An annular wall defines a fluid flow passage and includes a base portion and an adjoining exit portion. The base portion is typically generally frustoconical in shape and includes an arcuate contour in an axial direction. The exit portion includes undulations in a generally radial direction that provide lobes and troughs each respectively including trailing edges. One of the lobe and trough trailing edges are recessed from the other of the lobe and trough trailing edges in a generally axial direction. The other of the lobe and trough trailing edges form apexes with the apexes provided on tabs. The troughs extend radially inward in the axial direction towards the trough trailing edges.

    摘要翻译： 用于燃气涡轮发动机的喷嘴在芯和/或风扇排气流喷嘴上设置有起伏。 环形壁限定流体流动通道并且包括基部和相邻的出口部分。 基部通常在形状上通常为截头圆锥形，并且在轴向方向上包括弧形轮廓。 出口部分包括在大致径向方向上的波纹，其提供每个分别包括后缘的波瓣和波谷。 叶片和槽的后缘中的一个在大致轴向方向上从另一个叶片和槽的后缘凹入。 另一个叶片和槽尾缘形成顶点，顶点设在翼片上。 槽沿着轴向朝向槽的后缘径向向内延伸。

    Jet exhaust noise reduction system and method
    3.
    发明授权
    Jet exhaust noise reduction system and method 有权
    喷气排气降噪系统及方法

    公开(公告)号：US07114323B2

    公开(公告)日：2006-10-03

    申请号：US10794968

    申请日：2004-03-05

    申请人： Robert Schlinker ,  Satish Narayanan ,  Wesley K. Lord ,  Gregory A. Kohlenberg ,  Ramons Reba ,  John Simonich ,  Marios C. Soteriou ,  Thierry Maeder

    发明人： Robert Schlinker ,  Satish Narayanan ,  Wesley K. Lord ,  Gregory A. Kohlenberg ,  Ramons Reba ,  John Simonich ,  Marios C. Soteriou ,  Thierry Maeder

    IPC分类号： B63H11/00 ,  B64G9/00 ,  F02K9/00 ,  F03H9/00 ,  F23R9/00

    CPC分类号： F02K1/386 ,  Y02T70/56

    摘要： A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.

    摘要翻译： 一种用于减少来自内部混合燃气涡轮发动机排气的喷射噪声发射的系统，包括具有多个混合器叶片的风扇/芯流混合器和具有相同数量的翼片的公共流动喷嘴，所述翼片沿着沿着 喷嘴。 在多个混合器叶片和多个喷嘴翼片之间存在预定的时钟关系，其导致减少的排气噪声发射，在较低的频率范围中最明显。 一种用于减少内部混合燃气涡轮发动机废气排放的喷射噪声的方法包括：选择性地将由风扇/核心混合器产生的混合涡流场的周向分布与由改进的公共流动喷嘴产生的周向分布的排气涡流场对齐 发动机排气口的出口面。

    Jet exhaust noise reduction system and method
    4.
    发明申请
    Jet exhaust noise reduction system and method 有权
    喷气排气降噪系统及方法

    公开(公告)号：US20050193716A1

    公开(公告)日：2005-09-08

    申请号：US10794968

    申请日：2004-03-05

    申请人： Robert Schlinker ,  Satish Narayanan ,  Wesley Lord ,  Gregory Kohlenberg ,  Ramons Reba ,  John Simonich ,  Marios Soteriou ,  Thierry Maeder

    发明人： Robert Schlinker ,  Satish Narayanan ,  Wesley Lord ,  Gregory Kohlenberg ,  Ramons Reba ,  John Simonich ,  Marios Soteriou ,  Thierry Maeder

    IPC分类号： B64G99/00 ,  F02K1/34

    CPC分类号： F02K1/386 ,  Y02T70/56

    摘要： A system for reducing jet noise emission from an internally mixed gas turbine engine exhaust, comprising a fan/core flow mixer having a plurality of mixer lobes and a common flow nozzle having an equal number of tabs located along a circumferential edge of an aft end of the nozzle. There is a predetermined clocking relationship between the plurality of mixer lobes and the plurality of nozzle tabs that results in reduced exhaust noise emission, most evident in the lower frequency range. A method for reducing jet noise emission from an internally mixed gas turbine engine exhaust comprises selectively aligning a circumferential distribution of a mixed flow vorticity field produced by a fan/core mixer with a circumferentially distributed exhaust flow vorticity field produced by a modified common flow nozzle at an exit plane of the engine exhaust.

    摘要翻译： 一种用于减少来自内部混合燃气涡轮发动机排气的喷射噪声发射的系统，包括具有多个混合器叶片的风扇/芯流混合器和具有相同数量的翼片的公共流动喷嘴，所述翼片沿着沿着 喷嘴。 在多个混合器叶片和多个喷嘴翼片之间存在预定的时钟关系，其导致减少的排气噪声发射，在较低的频率范围中最明显。 一种用于减少内部混合燃气涡轮发动机废气排放的喷射噪声的方法包括：选择性地将由风扇/核心混合器产生的混合涡流场的周向分布与由改进的公共流动喷嘴产生的周向分布的排气涡流场对齐 发动机排气口的出口面。

    Asymmetric serrated nozzle for exhaust noise reduction
    6.
    发明授权
    Asymmetric serrated nozzle for exhaust noise reduction 有权
    用于排气噪声降低的不对称锯齿喷嘴

    公开(公告)号：US07520124B2

    公开(公告)日：2009-04-21

    申请号：US11519606

    申请日：2006-09-12

    申请人： Satish Narayanan ,  John Simonich ,  Robert Hans Schlinker

    发明人： Satish Narayanan ,  John Simonich ,  Robert Hans Schlinker

    IPC分类号： F02K1/38

    CPC分类号： F02K1/48 ,  B64D33/06 ,  F02K1/386 ,  F02K1/827 ,  Y02T50/671

    摘要： An exhaust nozzle for use in a gas turbine engine comprises a flow body for receiving exhaust gas from the turbine engine and includes a leading edge and a trailing edge. The leading edge connects with the gas turbine engine such that the flow body surrounds a centerline of the engine. The trailing edge comprises a serrated portion and a non-serrated portion. The serrated portion is formed from a plurality of tabs for mixing exhaust gas exiting the flow body with gases passing by an exterior of the flow body. The non-serrated portion is positioned along a lower portion of the trailing edge with respect to the engine centerline.

    摘要翻译： 用于燃气涡轮发动机的排气喷嘴包括用于从涡轮发动机接收废气并包括前缘和后缘的流体。 前缘与燃气涡轮发动机连接，使得流体围绕发动机的中心线。 后缘包括锯齿状部分和非锯齿形部分。 锯齿形部分由多个翼片形成，用于将从流体体排出的排气与通过流体的外部的气体混合。 非锯齿形部分相对于发动机中心线沿着后缘的下部定位。

    SYSTEM AND METHOD FOR THREAT PROPAGATION ESTIMATION
    9.
    发明申请
    SYSTEM AND METHOD FOR THREAT PROPAGATION ESTIMATION 审中-公开
    威胁传播估算系统与方法

    公开(公告)号：US20100204969A1

    公开(公告)日：2010-08-12

    申请号：US12733757

    申请日：2007-09-19

    申请人： Nathan S. Hariharan ,  Troy Ray Smith ,  Andrzej Banaszuk ,  Satish Narayanan

    发明人： Nathan S. Hariharan ,  Troy Ray Smith ,  Andrzej Banaszuk ,  Satish Narayanan

    IPC分类号： G06F17/10 ,  G06G7/48 ,  G06N7/02

    CPC分类号： G08B31/00

    摘要： A threat propagation estimator generates threat propagation estimates for a region based on a combination of sensor data (z) and model-based threat propagation estimates. The threat propagation estimator receives sensor data (z) from one or more sensor devices, and employs threat propagation model (M) to generate a model-based threat propagation estimate. A threat propagation algorithm (20) is used to combine the sensor data (z) and the model-based threat propagation estimate to generate a threat propagation estimate (Jc).

    摘要翻译： 威胁传播估计器基于传感器数据（z）和基于模型的威胁传播估计的组合，为区域生成威胁传播估计。 威胁传播估计器从一个或多个传感器设备接收传感器数据（z），并使用威胁传播模型（M）来生成基于模型的威胁传播估计。 威胁传播算法（20）用于组合传感器数据（z）和基于模型的威胁传播估计，以产生威胁传播估计（Jc）。