公开(公告)号：US20060137352A1

公开(公告)日：2006-06-29

申请号：US11025402

申请日：2004-12-29

申请人： Dilip Prasad ,  Jinzhang Feng ,  William Proscia

发明人： Dilip Prasad ,  Jinzhang Feng ,  William Proscia

IPC分类号： F02K3/10

CPC分类号： F23R3/002 ,  F02K1/827 ,  F05D2260/96 ,  F23M20/005 ,  F23R2900/00014

摘要： An augmentor liner is provided that includes an annulus disposed between a first wall and a second wall, and a plurality of baffles. The first wall is disposed radially inside of the second wall. The plurality of baffles extend heightwise between the first wall and the second wall, and are circumferentially spaced apart from one another by a distance. The distance between adjacent baffles is such that an acoustic wave entering an annulus compartment will travel between the first wall and second wall in a direction having a radial component that is substantially greater than a circumferential component. The baffle spacing may alternatively be described as being such that the circumferential component of the acoustic wave is substantially damped and therefore does not materially contribute to undesirable screech.

摘要翻译： 提供增强衬套，其包括设置在第一壁和第二壁之间的环形空间，以及多个挡板。 第一壁径向设置在第二壁的内侧。 多个挡板在第一壁和第二壁之间的高度方向上延伸，并且彼此间隔开一定距离。 相邻挡板之间的距离使得进入环形隔室的声波将沿着具有基本上大于周向部件的径向分量的方向在第一壁和第二壁之间移动。 挡板间隔可替代地被描述为使得声波的圆周分量基本上被阻尼，因此不会对不期望的尖叫声产生实质的影响。

公开(公告)号：US20070163229A1

公开(公告)日：2007-07-19

申请号：US11588544

申请日：2006-10-27

申请人： Dilip Prasad ,  Jinzhang Feng ,  Jayant Sabnis

发明人： Dilip Prasad ,  Jinzhang Feng ,  Jayant Sabnis

IPC分类号： F02K3/02

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  Y10T137/0536

摘要： A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

摘要翻译： 包括风扇部分，压缩机，燃烧器和涡轮机的燃气涡轮发动机包括具有限定入口管道的内部机舱表面的机舱，其设计成减小入口管道的入口管道面积以增加声学衰减。 燃气涡轮发动机还包括设置在风扇部分的前方的旋转器，其包括增加声衰减的特征。 在本发明的一个实施例中，机舱包括从内部机舱表面径向向内突出以缩小入口管道面积的机舱轮廓表面。 在本发明的另一实施例中，旋转器包括用于减小入口管道面积的旋转器轮廓表面。 在其他实施例中，机舱和/或旋转器包括可充气气囊，SMA致动器，流体致动器或其组合，其被选择性地激活以增加在飞行器的某些条件下的声衰减。

公开(公告)号：US20100215479A1

公开(公告)日：2010-08-26

申请号：US12775649

申请日：2010-05-07

申请人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

发明人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

IPC分类号： F01D25/04

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  Y10T137/0536

摘要： A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

摘要翻译： 包括风扇部分，压缩机，燃烧器和涡轮机的燃气涡轮发动机包括具有限定入口管道的内部机舱表面的机舱，其设计成减小入口管道的入口管道面积以增加声学衰减。 燃气涡轮发动机还包括设置在风扇部分的前方的旋转器，其包括增加声衰减的特征。 在本发明的一个实施例中，机舱包括从内部机舱表面径向向内突出以缩小入口管道面积的机舱轮廓表面。 在本发明的另一实施例中，旋转器包括用于减小入口管道面积的旋转器轮廓表面。 在其他实施例中，机舱和/或旋转器包括可充气气囊，SMA致动器，流体致动器或其组合，其被选择性地激活以增加在飞行器的某些条件下的声衰减。

公开(公告)号：US08286654B2

公开(公告)日：2012-10-16

申请号：US12775649

申请日：2010-05-07

申请人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

发明人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

IPC分类号： F02B27/00

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  Y10T137/0536

摘要： A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

摘要翻译： 包括风扇部分，压缩机，燃烧器和涡轮机的燃气涡轮发动机包括具有限定入口管道的内部机舱表面的机舱，其设计成减小入口管道的入口管道面积以增加声学衰减。 燃气涡轮发动机还包括设置在风扇部分的前方的旋转器，其包括增加声衰减的特征。 在本发明的一个实施例中，机舱包括从内部机舱表面径向向内突出以缩小入口管道面积的机舱轮廓表面。 在本发明的另一实施例中，旋转器包括用于减小入口管道面积的旋转器轮廓表面。 在其他实施例中，机舱和/或旋转器包括可充气气囊，SMA致动器，流体致动器或其组合，其被选择性地激活以增加在飞行器的某些条件下的声衰减。

公开(公告)号：US07739865B2

公开(公告)日：2010-06-22

申请号：US11588544

申请日：2006-10-27

申请人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

发明人： Dilip Prasad ,  Jinzhang Feng ,  Jayant S. Sabnis

IPC分类号： F02K3/02

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  Y10T137/0536

摘要： A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

摘要翻译： 包括风扇部分，压缩机，燃烧器和涡轮机的燃气涡轮发动机包括具有限定入口管道的内部机舱表面的机舱，其设计成减小入口管道的入口管道面积以增加声学衰减。 燃气涡轮发动机还包括设置在风扇部分的前方的旋转器，其包括增加声衰减的特征。 在本发明的一个实施例中，机舱包括从内部机舱表面径向向内突出以缩小入口管道面积的机舱轮廓表面。 在本发明的另一实施例中，旋转器包括用于减小入口管道面积的旋转器轮廓表面。 在其他实施例中，机舱和/或旋转器包括可充气气囊，SMA致动器，流体致动器或其组合，其被选择性地激活以增加在飞行器的某些条件下的声衰减。

公开(公告)号：US20050274103A1

公开(公告)日：2005-12-15

申请号：US10865025

申请日：2004-06-10

申请人： Dilip Prasad ,  Jinzhang Feng ,  Jayant Sabnis

发明人： Dilip Prasad ,  Jinzhang Feng ,  Jayant Sabnis

IPC分类号： F02C7/042 ,  F02C7/045 ,  F02C7/24 ,  F02K1/10 ,  F02K1/15 ,  F02K3/04

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F02C7/045 ,  Y10T137/0536

摘要： A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

摘要翻译： 包括风扇部分，压缩机，燃烧器和涡轮机的燃气涡轮发动机包括具有限定入口管道的内部机舱表面的机舱，其设计成减小入口管道的入口管道面积以增加声学衰减。 燃气涡轮发动机还包括设置在风扇部分的前方的旋转器，其包括增加声衰减的特征。 在本发明的一个实施例中，机舱包括从内部机舱表面径向向内突出以缩小入口管道面积的机舱轮廓表面。 在本发明的另一实施例中，旋转器包括用于减小入口管道面积的旋转器轮廓表面。 在其他实施例中，机舱和/或旋转器包括可充气气囊，SMA致动器，流体致动器或其组合，其被选择性地激活以增加在飞行器的某些条件下的声衰减。