专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

US20150153726A1 METHOD FOR INSPECTING A MANUFACTURING DEVICE 审中-公开
标题翻译：检查制造设备的方法
公开(公告)号：US20150153726A1
公开(公告)日：2015-06-04
申请号：US14574865
申请日：2014-12-18
申请人： James Romanelli, IV , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
发明人： James Romanelli, IV , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
IPC分类号： G05B19/418 , G06F17/50
CPC分类号： G05B19/4187 , G05B19/401 , G05B2219/37205 , G05B2219/37555 , G06F17/50 , Y02P90/265
摘要： A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.
摘要翻译：提供了一种利用电子测量装置和处理系统检查多个部件的方法。该方法包括使用电子测量装置创建部件的表面几何图形的步骤，其中每个部件利用制造装置制造。部件的几何零件模型是从表面几何图生成的。随后可以分析零件模型以确定制造多个零件的制造装置是否制造符合零件设计规范的零件。

2. 发明授权

US08942837B2 Method for inspecting a manufacturing device 有权
标题翻译：检查制造装置的方法
公开(公告)号：US08942837B2
公开(公告)日：2015-01-27
申请号：US13417990
申请日：2012-03-12
申请人： James Romanelli , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
发明人： James Romanelli , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
IPC分类号： G06F19/00
CPC分类号： G05B19/4187 , G05B19/401 , G05B2219/37205 , G05B2219/37555 , G06F17/50 , Y02P90/265
摘要： A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.
摘要翻译：提供了一种利用电子测量装置和处理系统检查多个部件的方法。该方法包括使用电子测量装置创建部件的表面几何图形的步骤，其中每个部件利用制造装置制造。部件的几何零件模型是从表面几何图生成的。随后可以分析零件模型以确定制造多个零件的制造装置是否制造符合零件设计规范的零件。

3. 发明申请

US20130238109A1 METHOD FOR INSPECTING A MANUFACTURING DEVICE 有权
公开(公告)号：US20130238109A1
公开(公告)日：2013-09-12
申请号：US13417990
申请日：2012-03-12
申请人： James Romanelli , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
发明人： James Romanelli , Jeffrey S. Beattie , Jesse R. Boyer , Robert E. Erickson , Randall W. Joyner , Daniel A. Snyder , David A. Krause , Kun Tong
IPC分类号： G06F19/00
CPC分类号： G05B19/4187 , G05B19/401 , G05B2219/37205 , G05B2219/37555 , G06F17/50 , Y02P90/265
摘要： A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.

4. 发明申请

US20140003950A1 MISTAKE PROOF DAMPER POCKET SEALS 有权
标题翻译：防伪防尘口袋密封件
公开(公告)号：US20140003950A1
公开(公告)日：2014-01-02
申请号：US13537127
申请日：2012-06-29
申请人： Jeffrey S. Beattie , Jeffrey Michael Jacques
发明人： Jeffrey S. Beattie , Jeffrey Michael Jacques
IPC分类号： F01D5/30 , B21D53/78 , F01D5/10
CPC分类号： F01D5/22 , F01D11/006 , F05D2230/64 , F05D2260/30 , Y10T29/49316
摘要： A method of assembling a blade array includes the step of inserting a blade having a platform into a rotor. The blade includes a pocket radially beneath the platform that includes an interference feature. The blade corresponds to one of first and second blades that are scaled versions of one another. The method includes the step of selecting a damper seal, and inserting the damper seal into the pocket. The damper seal corresponds to one of first and second damper seals. The first damper seal cooperates with the interference feature thereby permitting the first damper seal to fully seat within the pocket. The second damper seal is obstructed by the interference feature thereby preventing the second damper seal from fully seating within the pocket.
摘要翻译：组装叶片阵列的方法包括将具有平台的叶片插入转子的步骤。刀片包括径向在平台下方的口袋，其包括干涉特征。叶片对应于第一和第二叶片之一，其是彼此缩放的版本。该方法包括选择阻尼器密封件并将阻尼器密封件插入袋中的步骤。阻尼器密封件对应于第一和第二阻尼器密封件之一。第一阻尼器密封件与干涉特征协调，从而允许第一阻尼器密封件完全位于口袋内。第二阻尼器密封件受到干涉特征的阻碍，从而防止第二阻尼器密封件完全位于口袋内。

5. 发明申请

US20140000282A1 TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES 有权
标题翻译：涡轮叶片平台与U型通道冷却孔
公开(公告)号：US20140000282A1
公开(公告)日：2014-01-02
申请号：US13537258
申请日：2012-06-29
申请人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
IPC分类号： F01D5/18 , F02C7/18 , F02C3/04
CPC分类号： F01D5/085 , F01D5/081 , F01D5/18 , F05D2240/81 , Y02T50/676
摘要： A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧面连接的前缘和后缘，以提供在径向方向上延伸的外部翼面。后缘设置在涡轮叶片的后侧。根部支撑翼型件延伸的平台，并且冷却通道在根部内在径向方向上延伸到翼型件。下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。冲击孔从U形通道延伸到冷却通道。

6. 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。

7. 发明授权

US09243500B2 Turbine blade platform with U-channel cooling holes 有权
标题翻译：涡轮叶片平台配有U形通道冷却孔
公开(公告)号：US09243500B2
公开(公告)日：2016-01-26
申请号：US13537258
申请日：2012-06-29
申请人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Scott D. Lewis , Jeffrey S. Beattie , Jeffrey Michael Jacques , Brandon M. Rapp
IPC分类号： F01D5/18 , F01D5/08
CPC分类号： F01D5/085 , F01D5/081 , F01D5/18 , F05D2240/81 , Y02T50/676
摘要： A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.
摘要翻译：用于燃气涡轮发动机的涡轮机叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧面连接的前缘和后缘，以提供在径向方向上延伸的外部翼面。后缘设置在涡轮叶片的后侧。根部支撑翼型件延伸的平台，并且冷却通道在根部内在径向方向上延伸到翼型件。下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。冲击孔从U形通道延伸到冷却通道。

8. 发明授权

US09279331B2 Gas turbine engine airfoil with dirt purge feature and core for making same 有权
标题翻译：带有污垢清除功能的燃气涡轮发动机翼型和制造相同的核心
公开(公告)号：US09279331B2
公开(公告)日：2016-03-08
申请号：US13453137
申请日：2012-04-23
申请人： Jeffrey R. Levine , Jeffrey S. Beattie
发明人： Jeffrey R. Levine , Jeffrey S. Beattie
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
摘要： An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.
摘要翻译：机翼包括一个机身。主体包括邻近压力和吸力侧的前缘和后缘，以提供外部翼型表面。第一和第二冷却通道在径向方向上从根部延伸到尖端。第一冷却通道包括从顶端径向插入的尖端标记通道，并且沿着弦向延伸到穿过后缘的第一端。第二冷却通道包括邻近末端标记通道终止的第二端，并且污物清除通道将第二端与尖端标记通道相互连接。还公开了制造翼型的核心。

9. 发明授权

US08356978B2 Turbine airfoil platform cooling core 有权
标题翻译：涡轮机翼平台冷却芯
公开(公告)号：US08356978B2
公开(公告)日：2013-01-22
申请号：US12623666
申请日：2009-11-23
申请人： Jeffrey S. Beattie , Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
发明人： Jeffrey S. Beattie , Matthew A. Devore , Matthew S. Gleiner , Douglas C. Jenne
IPC分类号： F01D5/00
CPC分类号： F01D5/18 , B22C9/10 , F01D9/02 , F05D2240/81 , F05D2260/20
摘要： A gas turbine engine component has a platform and an airfoil extending from the platform. The platform has a pressure side and a suction side. A cooling passage is formed within the platform, and extends along a pressure side of the platform. Air leaves the passage through an air outlet on a suction side of the platform.
摘要翻译：燃气涡轮发动机部件具有从平台延伸的平台和翼型件。该平台具有压力侧和吸力侧。在平台内形成冷却通道，并沿平台的压力侧延伸。空气通过平台的吸入侧的出气口离开通道。

10. 发明授权

US10180067B2 Mate face cooling holes for gas turbine engine component 有权
公开(公告)号：US10180067B2
公开(公告)日：2019-01-15
申请号：US13485588
申请日：2012-05-31
申请人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
发明人： Jeffrey S. Beattie , Scott D. Lewis , Mark F. Zelesky , Ricardo Trindade , Bret M. Teller , Jeffrey Michael Jacques , Brandon M. Rapp
IPC分类号： F01D5/08 , F01D25/12 , F01D5/18
摘要： A gas turbine engine component comprises a shroud, a U-channel, an internal cooling air passage and a U-channel cooling hole. The shroud comprises a forward face, an aft face, a first side face and a second side face. The U-channel is disposed in the aft face of the shroud. A gas path surface connects the forward face, aft face, first side face and second side face. A cooled surface connects the forward face, aft face, first side face and second side face opposite the gas path face. The internal cooling air passage extends through the shroud. The U-channel cooling hole extends into the first side face of the shroud adjacent the U-channel to intersect the internal cooling passage.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式