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公开(公告)号：US20130205752A1
公开(公告)日：2013-08-15
申请号：US13370750
申请日：2012-02-10
IPC分类号： F02K3/02
CPC分类号： F02C3/145 , F02C7/36 , F02K3/025 , F05D2250/314
摘要： A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.
摘要翻译： 燃气涡轮发动机包括安装成围绕第一轴线旋转的推进单元和安装成围绕第二轴线旋转的核心发动机，并且其中第一和第二轴线是不平行的。 燃气涡轮发动机包括由与推进单元相邻的自由涡轮机驱动的推进单元和相关联的风扇，并且具有包括压缩机，燃烧器和涡轮机部分的气体发生器核心发动机。 还公开了一种方法。
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公开(公告)号：US08789354B2
公开(公告)日：2014-07-29
申请号：US13370750
申请日：2012-02-10
IPC分类号： F02K3/02
CPC分类号： F02C3/145 , F02C7/36 , F02K3/025 , F05D2250/314
摘要： A gas turbine engine includes a propulsion unit mounted to rotate about a first axis, and a core engine mounted to rotate about a second axis, and wherein the first and second axes are non-parallel. A gas turbine engine includes a propulsion unit driven by a free turbine which is adjacent to the propulsion unit and an associated fan, and having a gas generator core engine including a compressor, combustor and turbine section. A method is also disclosed.
摘要翻译： 燃气涡轮发动机包括安装成围绕第一轴线旋转的推进单元和安装成围绕第二轴线旋转的核心发动机，并且其中第一和第二轴线是不平行的。 燃气涡轮发动机包括由与推进单元相邻的自由涡轮机驱动的推进单元和相关联的风扇，并且具有包括压缩机，燃烧器和涡轮机部分的气体发生器核心发动机。 还公开了一种方法。
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公开(公告)号：US09010085B2
公开(公告)日：2015-04-21
申请号：US13599175
申请日：2012-08-30
申请人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
发明人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.
摘要翻译： 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比率低于约170。
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公开(公告)号：US20130223991A1
公开(公告)日：2013-08-29
申请号：US13407836
申请日：2012-02-29
IPC分类号： F01D15/12
CPC分类号： F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
摘要翻译： 燃气涡轮发动机包括具有压缩机部分的核心发动机，燃烧器和涡轮机。 涡轮驱动输出轴，输出轴驱动至少四个齿轮。 所述至少四个齿轮中的每一个延伸穿过驱动轴以驱动相关联的风扇转子。
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公开(公告)号：US20140102076A1
公开(公告)日：2014-04-17
申请号：US13599175
申请日：2012-08-30
申请人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
发明人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170.
摘要翻译： 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比率低于约170。
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公开(公告)号：US20120291449A1
公开(公告)日：2012-11-22
申请号：US13475252
申请日：2012-05-18
申请人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
发明人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
IPC分类号： F02C3/04
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
摘要翻译： 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比低于约170。
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公开(公告)号：US07942632B2
公开(公告)日：2011-05-17
申请号：US11765463
申请日：2007-06-20
IPC分类号： F01D17/16
CPC分类号： F01D5/146 , F01D5/148 , F01D17/162 , F04D29/563 , F05B2240/311 , F05D2240/12 , Y02T50/673
摘要： A variable shape inlet guide vane (IGV) system includes a variable-shape IGV flap with a flexible portion that enables the desired spanwise distribution of Cx, alpha, and beta at a fan rotor inlet. An actuation system that rotates a root section of the variable-shape IGV flap to flex the flexible portion such that the twisted shape of the flap can reverse rather symmetrically during actuation from max open to max closed.
摘要翻译： 可变形入口导叶（IGV）系统包括具有柔性部分的可变形IGV挡板，其能够在风扇转子入口处实现期望的跨度分布Cx，α和β。 驱动系统，其使可变形IGV挡板的根部部分旋转以弯曲柔性部分，使得在从最大开启到最大关闭的致动期间，翼片的扭曲形状可以相对对称地反转。
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8.发明申请VARIABLE-SHAPE VARIABLE-STAGGER INLET GUIDE VANE FLAP 有权VARIABLE-SHAPE VARIABLE-STAGGER入口指南VANE FLAP公开(公告)号：US20080317587A1
公开(公告)日：2008-12-25
申请号：US11765463
申请日：2007-06-20
IPC分类号： F01B25/02
CPC分类号： F01D5/146 , F01D5/148 , F01D17/162 , F04D29/563 , F05B2240/311 , F05D2240/12 , Y02T50/673
摘要： A variable shape inlet guide vane (IGV) system includes a variable-shape IGV flap with a flexible portion that enables the desired spanwise distribution of Cx, alpha, and beta at a fan rotor inlet. An actuation system that rotates a root section of the variable-shape IGV flap to flex the flexible portion such that the twisted shape of the flap can reverse rather symmetrically during actuation from max open to max closed.
摘要翻译： 可变形入口导叶（IGV）系统包括具有柔性部分的可变形IGV挡板，其能够在风扇转子入口处实现期望的跨度分布Cx，α和β。 驱动系统，其使可变形IGV挡板的根部部分旋转以弯曲柔性部分，使得在从最大开启到最大关闭的致动期间，翼片的扭曲形状可以相对对称地反转。
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公开(公告)号：US09297270B2
公开(公告)日：2016-03-29
申请号：US13407836
申请日：2012-02-29
CPC分类号： F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
摘要： A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
摘要翻译： 燃气涡轮发动机包括具有压缩机部分的核心发动机，燃烧器和涡轮机。 涡轮驱动输出轴，输出轴驱动至少四个齿轮。 所述至少四个齿轮中的每一个延伸穿过驱动轴以驱动相关联的风扇转子。
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公开(公告)号：US08844265B2
公开(公告)日：2014-09-30
申请号：US13475252
申请日：2012-05-18
申请人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
发明人： Paul R. Adams , Shankar S. Magge , Joseph B. Staubach , Wesley K. Lord , Frederick M. Schwarz , Gabriel L. Suciu
CPC分类号： F02C9/18 , F01D1/02 , F01D5/02 , F01D9/041 , F01D25/24 , F02C3/04 , F02C3/107 , F02C3/113 , F02C7/20 , F02C7/36 , F02K3/025 , F02K3/06 , F02K3/075 , F02K7/06 , F05D2220/32 , F05D2260/40311 , F05D2260/606 , Y02T50/671
摘要： A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.
摘要翻译： 涡轮风扇发动机具有发动机壳体和通过发动机壳体的气路。 风扇具有圆周阵列的风扇叶片。 发动机还具有压缩机，燃烧器，气体发生涡轮机和低压涡轮部分。 减速机构将低压涡轮部分连接到风扇。 旁路面积比大于约6.0。 低压涡轮机翼型计数到旁路面积比低于约170。
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