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1. 发明公开

EP1205634A3 Cooling of a gas turbine blade 有权
标题翻译： Gasturbinenschaufelkühlung
公开(公告)号：EP1205634A3
公开(公告)日：2003-10-29
申请号：EP01309235.8
申请日：2001-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Demers, Daniel Edward , Acquaviva, Paul Joseph , Manning, Robert Francis
IPC分类号： F01D5/18
CPC分类号： F01D11/04 , F01D5/081 , F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/22141 , Y02T50/676
摘要： A turbine blade (30) includes a platform (40) having an internal cavity (108) formed therein and an airfoil (42) extending radially from the platform (40). An internal cooling circuit (88,90) is formed in the airfoil (42) for circulating a coolant therethrough, and at least one supply passage (110) extends between the internal cooling circuit (88,90) and the internal platform (40) cavity (108) for diverting coolant to the internal platform (40) cavity (108). The coolant is expelled from holes (112) located in the forward and aft edges of the platform (40) for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.
摘要翻译：涡轮叶片（30）包括其中形成有内腔（108）的平台（40）和从平台（40）径向延伸的翼型件（42）。内部冷却回路（88,90）形成在翼片（42）中，用于使冷却剂循环通过，至少一个供应通道（110）在内部冷却回路（88,90）和内部平台（40）之间延伸，用于将冷却剂转向内部平台（40）腔（108）的腔（108）。冷却剂从位于平台（40）的前后边缘的孔（112）排出，用于清除前后的盘轮空间并冲击相邻的喷嘴带。

2. 发明授权

EP1001136B1 Airfoil with isolated leading edge cooling 有权
标题翻译：涡轮机叶片与前缘Aparter的冷却
公开(公告)号：EP1001136B1
公开(公告)日：2005-03-02
申请号：EP99309108.1
申请日：1999-11-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Manning, Robert Francis , Demers, Daniel Edward , Acquaviva, Paul Joseph
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202

3. 发明公开

EP1001136A2 Airfoil isolated leading edge cooling 有权
标题翻译： Strömungsmaschinenschaufelmit aparterKühlungderAnströmkante
公开(公告)号：EP1001136A2
公开(公告)日：2000-05-17
申请号：EP99309108.1
申请日：1999-11-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Manning, Robert Francis , Demers, Daniel Edward , Acquaviva, Paul Joseph
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil (14) includes first and second sidewalls (22,24) joined together at opposite leading and trailing edges (26,28), and spaced apart from each other therebetween to define a leading edge channel (34) extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes (36) extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum 38 extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition (40) having a plurality of inlet holes (42). A plurality of film cooling gill holes (44) extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.
摘要翻译：燃气涡轮发动机翼型件（14）包括在相对的前缘和后缘（26,28）处接合在一起的第一和第二侧壁（22,24），并且彼此间隔开，以限定纵向延伸的前缘通道（34）从根部到翼型的尖端。多个薄膜冷却孔（36）延伸穿过前缘并与前缘通道流通。隔离通风室38沿着第一侧壁延伸并且邻近前缘通道，并且通过具有多个入口孔（42）的隔板（40）与其隔开。多个薄膜冷却鳃孔（44）延伸穿过第一侧壁，并且与隔离气室成流动连通地设置。冷却空气从前缘通道引导到隔离气室，用于用减压空气供给鳃孔。

4. 发明授权

EP1001137B1 Gas turbine airfoil with axial serpentine cooling circuits 有权
标题翻译：燃气轮机叶片的蛇形冷却通道
公开(公告)号：EP1001137B1
公开(公告)日：2005-02-16
申请号：EP99309110.7
申请日：1999-11-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Manning, Robert Francis , Acquaviva, Paul Joseph , Demers, Daniel Edward
IPC分类号： F01D5/18
CPC分类号： F01D5/187

5. 发明公开

EP1001135A3 Airfoil with serial impingement cooling 审中-公开
标题翻译：涡轮叶片串行影响冷却
公开(公告)号：EP1001135A3
公开(公告)日：2001-12-05
申请号：EP99309107.3
申请日：1999-11-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Manning, Robert Francis , Acquaviva, Paul Joseph , Demers, Daniel Edward
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil (14) includes first and second sidewalls (22,24) joined together at opposite leading and trailing edges (26,28), and extending longitudinally from a root to a tip. The sidewalls are spaced apart from each other to define in part first and second adjoining flow chambers (34-38) extending longitudinally therein, and defined in additional part by corresponding first and second partitions (40-44) disposed between the sidewalls. The second partition (42) is common to both chambers, and both partitions include respective pluralities of first and second inlet holes (46-50) sized to meter cooling air therethrough in series between the chambers.

6. 发明公开

EP0990771A1 Trapped insert turbine airfoil 审中-公开
标题翻译： Turbinenschaufel mitKühleinsatz
公开(公告)号：EP0990771A1
公开(公告)日：2000-04-05
申请号：EP99307225.5
申请日：1999-09-13
申请人： GENERAL ELECTRIC COMPANY
发明人： Acquaviva, Paul Joseph , Liotta, Gary Charles , Fleck, James Norwood
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： B23P15/04 , F01D5/189 , F01D5/20 , Y10T29/49343
摘要： A gas turbine engine airfoil (10) is manufactured by forming an internal retention seat in two complementary airfoil parts (26, 28). An insert is fabricated for retention in the seat. The two parts (26, 28) are assembled with the insert disposed in the seat therebetween. The parts are then bonded together to trap the insert therein to collectively define the airfoil (10), The insert and seat may be precisely fabricated for improving the efficiency of the airfoil.
摘要翻译：燃气涡轮发动机翼型件（10）通过在两个互补翼型件（26,28）中形成内部保持座来制造。制造用于保持在座中的插入件。这两个部件（26,28）组装在插入件之间的插入件中。然后将这些部件结合在一起以将其中的插入物收集在一起以共同限定翼型件（10）。可以精确地制造插入件和座椅以提高翼型件的效率。

7. 发明授权

EP1205636B1 Turbine blade for a gas turbine and method of cooling said blade 有权
标题翻译：一个燃气涡轮机的涡轮机叶片和过程叶片的冷却
公开(公告)号：EP1205636B1
公开(公告)日：2012-08-22
申请号：EP01309237.4
申请日：2001-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Demers, Daniel Edward , Manning, Robert Francis , Acquaviva, Paul Joseph
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81 , F05D2260/202 , Y02T50/676

8. 发明公开

EP1205636A2 Cooling a turbine blade for gas turbine engine 有权
标题翻译： Turbinenschaufel einer Gasturbine sowie Verfahren zurKühlungder Schaufel
公开(公告)号：EP1205636A2
公开(公告)日：2002-05-15
申请号：EP01309237.4
申请日：2001-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Demers, Daniel Edward , Manning, Robert Francis , Acquaviva, Paul Joseph
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2240/81 , F05D2260/202 , Y02T50/676
摘要： A turbine blade (30) includes a platform (40) and an airfoil (42) extending radially from the platform (40). An internal cooling circuit is formed in the airfoil (42) for circulating a coolant therethrough to cool the airfoil (42). At least one supply passage (110) is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform (40) for cooling the platform (40).
摘要翻译：涡轮叶片（30）包括平台（40）和从平台（40）径向延伸的翼型件（42）。在翼型件（42）中形成内部冷却回路，用于使冷却剂循环通过以冷却翼型件（42）。提供至少一个供应通道（110）以将已经至少部分地通过内部冷却回路的一些冷却剂引导到平台（40）上以冷却平台（40）。

9. 发明公开

EP1205634A2 Cooling of a gas turbine blade 有权
标题翻译： Turbinenschaufel sowie deren Verwendung
公开(公告)号：EP1205634A2
公开(公告)日：2002-05-15
申请号：EP01309235.8
申请日：2001-10-31
申请人： GENERAL ELECTRIC COMPANY
发明人： Demers, Daniel Edward , Acquaviva, Paul Joseph , Manning, Robert Francis
IPC分类号： F01D5/18
CPC分类号： F01D11/04 , F01D5/081 , F01D5/187 , F05D2240/81 , F05D2260/202 , F05D2260/22141 , Y02T50/676
摘要： A turbine blade (30) includes a platform (40) having an internal cavity (108) formed therein and an airfoil (42) extending radially from the platform (40). An internal cooling circuit (88,90) is formed in the airfoil (42) for circulating a coolant therethrough, and at least one supply passage (110) extends between the internal cooling circuit (88,90) and the internal platform (40) cavity (108) for diverting coolant to the internal platform (40) cavity (108). The coolant is expelled from holes (112) located in the forward and aft edges of the platform (40) for purging the forward and aft disk wheel spaces and impingement cooling adjacent nozzle bands.
摘要翻译：涡轮叶片（30）包括其中形成有内腔（108）的平台（40）和从平台（40）径向延伸的翼型件（42）。内部冷却回路（88,90）形成在翼片（42）中，用于使冷却剂循环通过，至少一个供应通道（110）在内部冷却回路（88,90）和内部平台（40）之间延伸，用于将冷却剂转向内部平台（40）腔（108）的腔（108）。冷却剂从位于平台（40）的前后边缘的孔（112）排出，用于清除前后的盘轮空间并冲击相邻的喷嘴带。

10. 发明公开

EP1001136A3 Airfoil isolated leading edge cooling 有权
标题翻译：涡轮机叶片与前缘Aparter的冷却
公开(公告)号：EP1001136A3
公开(公告)日：2001-11-28
申请号：EP99309108.1
申请日：1999-11-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Manning, Robert Francis , Demers, Daniel Edward , Acquaviva, Paul Joseph
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2260/201 , F05D2260/202
摘要： A gas turbine engine airfoil (14) includes first and second sidewalls (22,24) joined together at opposite leading and trailing edges (26,28), and spaced apart from each other therebetween to define a leading edge channel (34) extending longitudinally from a root to a tip of the airfoil. A plurality of film cooling holes (36) extend through the leading edge and are disposed in flow communication with the leading edge channel. An isolation plenum 38 extends along the first sidewall and adjacent the leading edge channel, and is separated therefrom by a partition (40) having a plurality of inlet holes (42). A plurality of film cooling gill holes (44) extend through the first sidewall, and are disposed in flow communication with the isolation plenum. Cooling air is channeled from the leading edge channel to the isolation plenum for feeding the gill holes with reduced pressure air.

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