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1. 发明授权

EP1600605B1 Cooled rotor blade 有权转让
标题翻译：冷却转子叶片
公开(公告)号：EP1600605B1
公开(公告)日：2015-01-28
申请号：EP05253262.9
申请日：2005-05-27
申请人： United Technologies Corporation
发明人： Levine, Jeffrey R. , Pietraszkiewicz, Edward , Calderbank, John , Mongillo, Dominic J., Jr.
IPC分类号： F01D5/18 , F01D5/14 , F02C7/18
CPC分类号： F01D5/187 , F05D2250/30 , F05D2250/314 , F05D2260/22141

2. 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

3. 发明公开

EP1547714A3 Hole drilling guide and method 有权
标题翻译：钻孔指导和方法
公开(公告)号：EP1547714A3
公开(公告)日：2005-11-23
申请号：EP04257974.8
申请日：2004-12-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Coons, Todd , Pietraszkiewicz, Edward
IPC分类号： B23H9/14 , B23H9/10 , B23H7/10 , B23H7/26
CPC分类号： B23H9/10 , B23H7/105 , B23H7/265 , B23H9/14
摘要： A hole-drilling guide for directing a flexible hole-drilling instrument (72) includes a body (74) made of electrically insulating material, at least one inlet aperture (76) penetrating a face of the body (74), at least one exit aperture (78) penetrating a face of the body (74) and a hollow, nonlinear raceway linking the inlet and exit apertures.
摘要翻译：用于引导柔性钻孔器械（72）的钻孔引导件包括由电绝缘材料制成的主体（74），至少一个穿透主体（74）的面的入口孔（76），至少一个出口穿过主体（74）的表面的孔（78）以及连接入口和出口孔的中空非线性滚道。

4. 发明公开

EP1605138A3 Cooled rotor blade with leading edge impingement cooling 有权转让
标题翻译：具有冲击冷却转子叶片的前缘的区域冷却
公开(公告)号：EP1605138A3
公开(公告)日：2007-10-03
申请号：EP05253261.1
申请日：2005-05-27
申请人： United Technologies Corporation
发明人： Levine, Jeffrey R. , Pietraszkiewicz, Edward
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202
摘要： A rotor blade (14) is provided having a hollow airfoil (22) and a root (20). The hollow airfoil (22) has a cavity defined by a suction side wall (38), a pressure side wall (36), a leading edge (32), a trailing edge (34), a base (28), and a tip (30). An internal passage configuration (40) is disposed within the cavity. The configuration includes a first radial passage (48), a second radial passage (50), and a rib (53) disposed between and separating the first radial passage (48) and second radial passage (50). A plurality of crossover apertures (52) are disposed within the rib (53). A portion of the plurality of crossover apertures (52) are oblong having a length (70) extending through the rib (53), and a height (74) and a width (72). The height (74) of each oblong aperture (52) is greater than the width (72). In some embodiments, the oblong crossover apertures (52) are aligned heightwise along the rib (53). The root (20) includes a conduit (42) that is operable to permit airflow through the root (20) and into the first radial passage (48).

5. 发明公开

EP1728970A2 Turbine blade cooling system 有权转让
标题翻译： KühlsystemfürTurbinenschaufel
公开(公告)号：EP1728970A2
公开(公告)日：2006-12-06
申请号：EP06252809.6
申请日：2006-05-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Downs, James P. , Roeloffs, Norman F. , Pietraszkiewicz, Edward
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202
摘要： A turbine blade cooling system for a gas turbine engine includes a turbine blade (100) having a trailing edge, a concave side (104), and a convex side (102). The trailing edge defines at least one set of impingement holes (106, 112) each having a central longitudinal axis which is closer to a nearest portion of an edge of the blade at one of the concave (104) and convex (102) sides relative to a nearest portion of an edge of the blade at the other of the concave (104) and convex (102) sides. Alternatively or in addition to the foregoing, the trailing edge can define at least one set of impingement holes (206, 212) each having a central longitudinal axis which is angled in a direction of a flow of cooling medium toward one of the concave (204) and convex (202) sides relative to the other of the concave (204) and convex (202) sides.
摘要翻译：用于燃气涡轮发动机的涡轮叶片冷却系统包括具有后缘的涡轮叶片（100），凹侧（104）和凸侧（102）。后缘限定至少一组冲击孔（106,112），每个冲击孔具有中心纵向轴线，该中心纵向轴线在凹（104）和凸（102）侧中的一个相对较靠近叶片的边缘的最近部分相对到另一个凹（104）和凸（102）侧的叶片的边缘的最近部分。替代地或除了上述之外，后缘可以限定至少一组冲击孔（206,212），每个冲击孔具有中心纵向轴线，该中心纵向轴线在冷却介质的流动方向上朝着凹部（204 ）和相对于凹（204）和凸（202）侧中的另一个的凸（202）侧。

6. 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.

7. 发明授权

EP1547714B1 Hole drilling guide and method 有权
标题翻译：跳汰机和钻孔
公开(公告)号：EP1547714B1
公开(公告)日：2008-07-30
申请号：EP04257974.8
申请日：2004-12-20
申请人： United Technologies Corporation
发明人： Coons, Todd , Pietraszkiewicz, Edward
IPC分类号： B23H9/14 , B23H9/10 , B23H7/10 , B23H7/26
CPC分类号： B23H9/10 , B23H7/105 , B23H7/265 , B23H9/14

8. 发明公开

EP1547714A2 Hole drilling guide and method 有权
标题翻译： Bohrlehre und Bohrverfahren
公开(公告)号：EP1547714A2
公开(公告)日：2005-06-29
申请号：EP04257974.8
申请日：2004-12-20
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Coons, Todd , Pietraszkiewicz, Edward
IPC分类号： B23H9/14 , B23H9/10 , B23H7/10 , B23H7/26
CPC分类号： B23H9/10 , B23H7/105 , B23H7/265 , B23H9/14
摘要： A hole-drilling guide for directing a flexible hole-drilling instrument (72) includes a body (74) made of electrically insulating material, at least one inlet aperture (76) penetrating a face of the body (74), at least one exit aperture (78) penetrating a face of the body (74) and a hollow, nonlinear raceway linking the inlet and exit apertures.
摘要翻译：用于引导柔性钻孔仪器（72）的钻孔引导件包括由电绝缘材料制成的主体（74），穿过主体（74）的表面的至少一个入口孔（76），至少一个出口穿过主体（74）的表面的孔（78）和连接入口孔和出口孔的中空的非线性滚道。

9. 发明授权

EP1728970B1 Turbine blade cooling system 有权转让
标题翻译：冷却系统用于涡轮机叶片
公开(公告)号：EP1728970B1
公开(公告)日：2013-12-11
申请号：EP06252809.6
申请日：2006-05-31
申请人： United Technologies Corporation
发明人： Downs, James P. , Roeloffs, Norman F. , Pietraszkiewicz, Edward
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/711 , F05D2250/712 , F05D2260/201 , F05D2260/202

10. 发明授权

EP1605138B1 Cooled rotor blade with leading edge impingement cooling 有权转让
标题翻译：具有冲击冷却转子叶片的前缘的区域冷却
公开(公告)号：EP1605138B1
公开(公告)日：2010-06-30
申请号：EP05253261.1
申请日：2005-05-27
申请人： United Technologies Corporation
发明人： Levine, Jeffrey R. , Pietraszkiewicz, Edward
IPC分类号： F01D5/18 , F02C7/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202

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