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1. 发明授权

US08257045B2 Platforms with curved side edges and gas turbine engine systems involving such platforms 有权
标题翻译：具有弯曲侧边的平台和涉及这种平台的燃气涡轮发动机系统
公开(公告)号：US08257045B2
公开(公告)日：2012-09-04
申请号：US12192271
申请日：2008-08-15
申请人： Brandon W. Spangler , Jeffrey S. Beattie , Scott D. Hjelm
发明人： Brandon W. Spangler , Jeffrey S. Beattie , Scott D. Hjelm
IPC分类号： F01D5/30 , F01D11/00
CPC分类号： F01D5/147 , F05D2240/80
摘要： Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform.
摘要翻译：提供了具有弯曲侧边缘的平台和涉及这种平台的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性翼型组件包括：平台，其具有气体通路侧，非气体通路侧，前缘，后缘，在前缘和后缘之间延伸的第一侧边缘沿着其长度呈现第一曲线，以及在前缘和后缘之间延伸并且沿其长度呈现第二曲线的第二侧边缘; 以及从平台的气体路径侧延伸的翼型件; 平台和翼型件呈现出一体的结构，使得连续的外表面从翼型混合到平台。

2. 发明申请

US20100040460A1 Platforms with Curved Side Edges and Gas Turbine Engine Systems Involving Such Platforms 有权
标题翻译：具有弯曲边缘的平台和涉及这种平台的燃气轮机发动机系统
公开(公告)号：US20100040460A1
公开(公告)日：2010-02-18
申请号：US12192271
申请日：2008-08-15
申请人： Brandon W. Spangler , Jeffrey S. Beattie , Scott D. Hjelm
发明人： Brandon W. Spangler , Jeffrey S. Beattie , Scott D. Hjelm
IPC分类号： F01D9/00
CPC分类号： F01D5/147 , F05D2240/80
摘要： Platforms with curved side edges and gas turbine engine systems involving such platforms are provided. In this regard, a representative airfoil assembly for a gas turbine engine includes: a platform having a gas path side, a non-gas path side, a leading edge, a trailing edge, a first side edge extending between the leading edge and the trailing edge and exhibiting a first curve along a length thereof, and a second side edge extending between the leading edge and the trailing edge and exhibiting a second curve along a length thereof; and an airfoil extending from the gas path side of the platform; the platform and the airfoil exhibiting a unitary construction such that a continuous exterior surface blends from the airfoil to the platform.
摘要翻译：提供了具有弯曲侧边缘的平台和涉及这种平台的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性翼型组件包括：平台，其具有气体通路侧，非气体通路侧，前缘，后缘，在前缘和后缘之间延伸的第一侧边缘沿着其长度呈现第一曲线，以及在前缘和后缘之间延伸并且沿其长度呈现第二曲线的第二侧边缘; 以及从平台的气体路径侧延伸的翼型件; 平台和翼型件呈现出一体的结构，使得连续的外表面从翼型混合到平台。

3. 发明申请

US20090116953A1 Turbine airfoil with platform cooling 有权
标题翻译：涡轮机翼与平台冷却
公开(公告)号：US20090116953A1
公开(公告)日：2009-05-07
申请号：US11982578
申请日：2007-11-02
申请人： Brandon W. Spangler , Corneil S. Paauwe , Christopher J. Lehane , Anita L. Tracy , John D. Wiedemer , Scott D. Hjelm
发明人： Brandon W. Spangler , Corneil S. Paauwe , Christopher J. Lehane , Anita L. Tracy , John D. Wiedemer , Scott D. Hjelm
IPC分类号： F02C7/18 , F02C7/28
CPC分类号： F01D11/008 , F01D5/081 , F01D5/187 , F05D2240/57 , F05D2240/81 , Y02T50/676
摘要： Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.
摘要翻译：通过将平台的界面与对应的平台对平台密封件切开，从而加速平台表面上的冷却气流，增强了燃气涡轮发动机翼型平台的对流冷却。

4. 发明授权

US08240981B2 Turbine airfoil with platform cooling 有权
标题翻译：涡轮机翼与平台冷却
公开(公告)号：US08240981B2
公开(公告)日：2012-08-14
申请号：US11982578
申请日：2007-11-02
申请人： Brandon W. Spangler , Corneil S. Paauwe , Christopher J. Lehane , Anita L. Tracy , John D. Wiedemer , Scott D. Hjelm
发明人： Brandon W. Spangler , Corneil S. Paauwe , Christopher J. Lehane , Anita L. Tracy , John D. Wiedemer , Scott D. Hjelm
IPC分类号： F01D25/12
CPC分类号： F01D11/008 , F01D5/081 , F01D5/187 , F05D2240/57 , F05D2240/81 , Y02T50/676
摘要： Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.
摘要翻译：通过将平台的界面与对应的平台对平台密封件切开，从而加速平台表面上的冷却气流，增强了燃气涡轮发动机翼型平台的对流冷却。

5. 发明授权

US08240987B2 Gas turbine engine systems involving baffle assemblies 有权
标题翻译：包括挡板组件的燃气涡轮发动机系统
公开(公告)号：US08240987B2
公开(公告)日：2012-08-14
申请号：US12192362
申请日：2008-08-15
申请人： Brandon W. Spangler , Jeffrey S. Beattie
发明人： Brandon W. Spangler , Jeffrey S. Beattie
IPC分类号： F01D25/08
CPC分类号： F01D11/006 , F01D11/08 , F05D2240/11 , F05D2240/126 , F05D2240/57 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section.
摘要翻译：提供了涉及挡板组件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性挡板组件包括：限定冷却空气路径的冷却气室; 以及挡板，其尺寸和形状设置成在所述冷却气室的表面之间延伸，使得在所述挡板和所述表面之间形成具有减小的横截面的冷却空气路径，所述挡板可操作以增加所述冷却空气的流速被引导到冷却空气路径被重新定向通过减小的横截面的冷却空气路径。

6. 发明申请

US20100040479A1 Gas Turbine Engine Systems Involving Baffle Assemblies 有权
标题翻译：燃气轮机发动机系统涉及挡板组件
公开(公告)号：US20100040479A1
公开(公告)日：2010-02-18
申请号：US12192362
申请日：2008-08-15
申请人： Brandon W. Spangler , Jeffrey S. Beattie
发明人： Brandon W. Spangler , Jeffrey S. Beattie
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D11/006 , F01D11/08 , F05D2240/11 , F05D2240/126 , F05D2240/57 , F05D2240/81 , F05D2260/202 , F05D2260/22141
摘要： Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section.
摘要翻译：提供了涉及挡板组件的燃气涡轮发动机系统。在这方面，用于燃气涡轮发动机的代表性挡板组件包括：限定冷却空气路径的冷却气室; 以及挡板，其尺寸和形状设置成在所述冷却气室的表面之间延伸，使得在所述挡板和所述表面之间形成具有减小的横截面的冷却空气路径，所述挡板可操作以增加所述冷却空气的流速被引导到冷却空气路径被重新定向通过减小的横截面的冷却空气路径。

7. 发明授权

US09322279B2 Airfoil cooling arrangement 有权
标题翻译：翼型冷却装置
公开(公告)号：US09322279B2
公开(公告)日：2016-04-26
申请号：US13539838
申请日：2012-07-02
申请人： Brandon W. Spangler , Russell J. Bergman
发明人： Brandon W. Spangler , Russell J. Bergman
IPC分类号： F01D5/18 , F01D9/06
CPC分类号： F01D5/186 , F01D9/065 , Y02T50/676
摘要： An airfoil according to an exemplary embodiment of the present disclosure can include an airfoil body having a plurality of film cooling holes that extend through an exterior surface of the airfoil body. Each of the plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the airfoil.
摘要翻译：根据本公开的示例性实施例的翼型件可以包括具有延伸穿过翼型件主体的外表面的多个膜冷却孔的翼型件主体。多个膜冷却孔中的每一个根据如表1所示的X，Y和Z的笛卡尔坐标值以几何坐标突破外表面。每个几何坐标是从前缘上的参考点机翼平台的轨道。

8. 发明授权

US09115597B2 Gas turbine engine turbine vane airfoil profile 有权
标题翻译：燃气轮机发动机涡轮叶片翼型
公开(公告)号：US09115597B2
公开(公告)日：2015-08-25
申请号：US13539917
申请日：2012-07-02
申请人： Brandon W. Spangler , Russell J. Bergman
发明人： Brandon W. Spangler , Russell J. Bergman
IPC分类号： F01D25/12 , F01D9/02
CPC分类号： F01D25/12 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes, wherein one of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。内部和外部平台分别包括内部和外部薄膜冷却孔组，其中内部和外部薄膜冷却孔组中的一个基本上与基于以下的笛卡尔坐标系中的一组所描述的平台冷却孔位置形成：表1和2.相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供。表1和表2中笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。

9. 发明授权

US09021816B2 Gas turbine engine turbine vane platform core 有权
标题翻译：燃气轮机涡轮叶片平台核心
公开(公告)号：US09021816B2
公开(公告)日：2015-05-05
申请号：US13539842
申请日：2012-07-02
申请人： Russell J. Bergman , Leonard A. Bach , Brandon W. Spangler
发明人： Russell J. Bergman , Leonard A. Bach , Brandon W. Spangler
IPC分类号： F02C3/04 , F04D29/30 , F01D9/02 , F01D9/04 , F01D25/12
CPC分类号： F01D9/02 , B22C9/04 , B22C9/10 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2230/21 , F05D2230/211 , F05D2240/81 , F05D2250/185 , F05D2260/2214 , Y02T50/672 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。翼型件包括翼型件冷却通道。平台冷却通道布置在内平台和外平台中的至少一个中。平台冷却通道包括多个冷却区域，其中一个冷却区域布置在翼型冷却通道下方。

10. 发明授权

US08707712B2 Gas turbine engine turbine vane airfoil profile 有权
标题翻译：燃气轮机发动机涡轮叶片翼型
公开(公告)号：US08707712B2
公开(公告)日：2014-04-29
申请号：US13539873
申请日：2012-07-02
申请人： Brandon W. Spangler , Russell J. Bergman
发明人： Brandon W. Spangler , Russell J. Bergman
IPC分类号： F02C7/12
CPC分类号： F01D25/12 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes. One of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).
摘要翻译：用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。内平台和外平台分别包括内套和外套薄膜冷却孔。内外套膜冷却孔中的一个基本上符合由表1和表2中所示的笛卡尔坐标系中的一组描述的平台冷却孔位置。笛卡尔坐标由轴向坐标，圆周方向坐标和径向坐标，相对于零坐标。表1和表2中笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。

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