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1. 发明公开

EP0887514A2 Coolable airfoil 失效
标题翻译：叶片冷却
公开(公告)号：EP0887514A2
公开(公告)日：1998-12-30
申请号：EP98305052.7
申请日：1998-06-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Fukuda, Takao , Price, Francis R. , Cook, Conan P. , Hoff, Richard W. , Singer, Irwin D.
IPC分类号： F01D5/18
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/2212 , Y02T50/673 , Y02T50/676
摘要： A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

2. 发明授权

EP0887514B1 Coolable airfoil 失效
标题翻译：可冷却翼型
公开(公告)号：EP0887514B1
公开(公告)日：2004-09-22
申请号：EP98305052.7
申请日：1998-06-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Fukuda, Takao , Price, Francis R. , Cook, Conan P. , Hoff, Richard W. , Singer, Irwin D.
IPC分类号： F01D5/18 , F01D25/32
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/2212 , Y02T50/673 , Y02T50/676

3. 发明公开

EP1621729A3 An airfoil profile with optimized aerodynamic shape 审中-公开
标题翻译：档案具有优化的空气动力学形状的涡轮叶片
公开(公告)号：EP1621729A3
公开(公告)日：2008-11-26
申请号：EP05254743.7
申请日：2005-07-28
申请人： United Technologies Corporation
发明人： Fukuda, Takao , Magge, Shankar S. , Price, Francis R.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/74 , Y10S416/02 , Y10S416/05
摘要： Provided is an aerodynamic profile for use in gas turbine airfoil (28) and a turbine blade (12) comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections (42) forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line (44) extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line (44) with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.

4. 发明公开

EP1726782A2 Turbine blade trailing edge construction 有权转让
标题翻译： Konfiguration derAbströmkanteeiner Turbinenschaufel
公开(公告)号：EP1726782A2
公开(公告)日：2006-11-29
申请号：EP06252766.8
申请日：2006-05-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Downs, James P. , Roeloffs, Normal F. , Pietraszkiewicz, Edward , Fukuda, Takao
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/711 , F05D2250/712
摘要： A turbine blade system for a gas turbine engine includes a turbine blade 100,200 having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface 110;210 to a trailing edge 112;212. The trailing edge region includes a plurality of riblets 104;204 extending in the lengthwise direction from the pressure side surface 110;210 toward the trailing edge 112;212. The trailing edge region defines a plurality of ejection slots 106;206 each laterally disposed between two of the riblets 104;204. The plurality of riblets 104;204 each define an upper surface 108;208 having at least a portion in the lengthwise direction being curved relative to the pressure side surface 110;210 so as to generally shield the upper surface 108;208 from a high heat load propagating from the pressure side surface 110;210 and to facilitate cooling air flowing from the ejection slots 106;206 to flow over the upper surface 108;208.
摘要翻译：一种用于燃气涡轮发动机的涡轮叶片系统包括涡轮叶片100,200，其具有在侧向方向上延伸的后缘区域，并且在长度方向上从压力侧表面110; 210延伸到后缘112; 212。后缘区域包括从压力侧表面110; 210向后缘112; 212沿长度方向延伸的多个肋条104; 204。后缘区域限定多个喷射狭槽106; 206，其各自横向设置在两个肋条104; 204之间。多个肋条104; 204各自限定上表面108; 208，其具有在长度方向上的至少一部分相对于压力侧表面110; 210弯曲，以便大体上将上表面108; 208从高热屏蔽从压力侧表面110; 210传播的负载，并且便于从喷射槽106; 206流出的冷却空气流过上表面108; 208。

5. 发明公开

EP1726782A3 Turbine blade trailing edge construction 有权转让
标题翻译：一个涡轮机叶片的后缘的结构
公开(公告)号：EP1726782A3
公开(公告)日：2010-05-05
申请号：EP06252766.8
申请日：2006-05-26
申请人： United Technologies Corporation
发明人： Downs, James P. , Roeloffs, Normal F. , Pietraszkiewicz, Edward , Fukuda, Takao
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/711 , F05D2250/712
摘要： A turbine blade system for a gas turbine engine includes a turbine blade 100,200 having a trailing edge region extending in a lateral direction and in a lengthwise direction from a pressure side surface 110;210 to a trailing edge 112;212. The trailing edge region includes a plurality of riblets 104;204 extending in the lengthwise direction from the pressure side surface 110;210 toward the trailing edge 112;212. The trailing edge region defines a plurality of ejection slots 106;206 each laterally disposed between two of the riblets 104;204. The plurality of riblets 104;204 each define an upper surface 108;208 having at least a portion in the lengthwise direction being curved relative to the pressure side surface 110;210 so as to generally shield the upper surface 108;208 from a high heat load propagating from the pressure side surface 110;210 and to facilitate cooling air flowing from the ejection slots 106;206 to flow over the upper surface 108;208.

6. 发明授权

EP1726782B1 Turbine blade trailing edge construction 有权转让
标题翻译：一个涡轮机叶片的后缘的结构
公开(公告)号：EP1726782B1
公开(公告)日：2012-10-17
申请号：EP06252766.8
申请日：2006-05-26
申请人： United Technologies Corporation
发明人： Downs, James P. , Roeloffs, Normal F. , Pietraszkiewicz, Edward , Fukuda, Takao
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/126 , F05D2240/304 , F05D2250/711 , F05D2250/712

7. 发明公开

EP1621729A2 An airfoil profile with optimized aerodynamic shape 审中-公开
标题翻译： Profilfüreine Turbinenschaufel mit optimierter aerodynamischer Form
公开(公告)号：EP1621729A2
公开(公告)日：2006-02-01
申请号：EP05254743.7
申请日：2005-07-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Fukuda, Takao , Magge, Shankar S. , Price, Francis R.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/74 , Y10S416/02 , Y10S416/05
摘要： Provided is an aerodynamic profile for use in gas turbine airfoil (28) and a turbine blade (12) comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections (42) forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured in any direction perpendicular to an airfoil stacking line (44) extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches. The R values are measured perpendicular to a plane normal to the airfoil stacking line (44) with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.
摘要翻译：提供用于燃气涡轮机翼型件（28）和包括这种型材的涡轮叶片（12）的空气动力学特性。轮廓由于涂层厚度的增加而抵消相邻翼面之间的面积减小。多个径向部分（42）形成翼型件的涂覆和未涂覆的标称轮廓。这些部分位于垂直于从中心轴线径向延伸并由X，Y和R笛卡尔坐标值以英寸限定的翼型堆叠线（44）的任何方向上测量的公差内。 R值垂直于垂直于翼型堆叠线（44）的平面测量，在最低径向截面处的R值为零，并且在径向方向上增加。 X和Y值垂直于翼型堆叠线测量。

8. 发明公开

EP0887514A3 Coolable airfoil 失效
标题翻译：叶片冷却
公开(公告)号：EP0887514A3
公开(公告)日：2000-03-15
申请号：EP98305052.7
申请日：1998-06-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Fukuda, Takao , Price, Francis R. , Cook, Conan P. , Hoff, Richard W. , Singer, Irwin D.
IPC分类号： F01D5/18 , F01D25/32
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/2212 , Y02T50/673 , Y02T50/676
摘要： A coolable airfoil has a passage 94 for discharging particulates entrained in cooling air to provide clean cooling air to the leading edge 60 of the airfoil. A chordwise duct 100 extends past a spanwisely extending supply passage 92 to the inlet of a spanwisely extending rear passage 94 such that momentum effects direct the flow of a portion of cooling air and particulates from the duct, past the entrance of the supply passage 92 and into the rear passage 94. The rear passage 94 has a purge hole 96 through which the particulates may be removed.

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