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公开(公告)号：US20100050651A1
公开(公告)日：2010-03-04
申请号：US12198959
申请日：2008-08-27
IPC分类号： F02K1/00
CPC分类号： F02K3/06 , B64D33/04 , F02K1/08 , F02K1/52 , F02K3/02 , F02K3/04 , F02K9/86 , F05D2250/14 , F05D2250/231
摘要： A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.
摘要翻译： 涡轮机排气喷嘴包括同轴地设置在外壳内的内壳，以限定终止在外壳的后缘处的出口中的流动管道。 内壳是非轴对称的，并且围绕管道周向地以轴向倾斜角度变化。
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公开(公告)号：US09181899B2
公开(公告)日：2015-11-10
申请号：US12198959
申请日：2008-08-27
CPC分类号： F02K3/06 , B64D33/04 , F02K1/08 , F02K1/52 , F02K3/02 , F02K3/04 , F02K9/86 , F05D2250/14 , F05D2250/231
摘要： A turbine exhaust nozzle includes an inner shell disposed coaxially inside an outer shell to define a flow duct terminating in an outlet at a trailing edge of the outer shell. The inner shell is non-axisymmetric and varies in axial slope angle circumferentially around the duct.
摘要翻译： 涡轮机排气喷嘴包括同轴地设置在外壳内的内壳，以限定终止在外壳的后缘处的出口中的流动管道。 内壳是非轴对称的，并且围绕管道周向地以轴向倾斜角度变化。
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3.发明授权Turbine assembly for a gas turbine engine and method of manufacturing the same 有权用于燃气涡轮发动机的涡轮组件及其制造方法公开(公告)号：US07758306B2
公开(公告)日：2010-07-20
申请号：US11615514
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49236
摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.
摘要翻译： 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。
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4.发明申请GAS TURBINE ENGINES INCLUDING MULTI-CURVE STATOR VANES AND METHODS OF ASSEMBLING THE SAME 有权气体涡轮发动机，其中包括多级定子风扇及其组装方法公开(公告)号：US20080152505A1
公开(公告)日：2008-06-26
申请号：US11615556
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F01D5/145 , F01D9/041 , F05D2240/301 , F05D2250/611 , F05D2250/71 , Y02T50/673
摘要： A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.
摘要翻译： 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。
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5.发明授权Gas turbine engines including lean stator vanes and methods of assembling the same 有权包括精密定子叶片的燃气涡轮发动机及其组装方法公开(公告)号：US07794201B2
公开(公告)日：2010-09-14
申请号：US11615541
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.
摘要翻译： 提供可用于发动机组件中的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接到第一侧壁。 翼型件还包括根部部分和尖端部分。 第一和第二侧壁都从根部延伸到尖端部分。 翼面根部形成为负的倾斜，并且翼型前端部形成为正的倾斜。
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6.发明申请GAS TURBINE ENGINES INCLUDING LEAN STATOR VANES AND METHODS OF ASSEMBLING THE SAME 有权气体涡轮发动机，包括精密定子风扇及其组装方法公开(公告)号：US20080152504A1
公开(公告)日：2008-06-26
申请号：US11615541
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
IPC分类号： F01D9/00
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.
摘要翻译： 提供可用于发动机组件中的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接到第一侧壁。 翼型件还包括根部部分和尖端部分。 第一和第二侧壁都从根部延伸到尖端部分。 翼面根部形成为负的倾斜，并且翼型前端部形成为正的倾斜。
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7.发明授权Gas turbine engines including multi-curve stator vanes and methods of assembling the same 有权包括多曲线定子叶片的燃气涡轮发动机及其组装方法公开(公告)号：US07806653B2
公开(公告)日：2010-10-05
申请号：US11615556
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F01D5/145 , F01D9/041 , F05D2240/301 , F05D2250/611 , F05D2250/71 , Y02T50/673
摘要： A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.
摘要翻译： 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。
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8.发明申请TURBINE ASSEMBLY FOR A GAS TURBINE ENGINE AND METHOD OF MANUFACTURING THE SAME 有权用于气体涡轮发动机的涡轮组件及其制造方法公开(公告)号：US20080148564A1
公开(公告)日：2008-06-26
申请号：US11615514
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D5/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49236
摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.
摘要翻译： 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。
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