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1. 发明专利

JP2013199927A Scalloped surface turbine stage 有权
标题翻译： SCALLOPED SURFACE TURBINE STAGE
公开(公告)号：JP2013199927A
公开(公告)日：2013-10-03
申请号：JP2013050195
申请日：2013-03-13
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： BARR BRIAN CHANDLER , KEITH BRIAN DAVID , KAJFASZ GREGORY JOHN
IPC分类号： F01D5/14 , F01D9/02
CPC分类号： F01D5/143 , F01D5/141 , F01D5/145 , F05D2240/304 , F05D2250/611 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a turbine stage including a row of airfoils joined to corresponding platforms to define flow passages therebetween.SOLUTION: Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured to have a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.
摘要翻译：要解决的问题：提供一种涡轮级，其包括连接到相应平台的一排翼型件，以在其间限定流动通道。解决方案：每个翼型件包括相对的压力和吸力侧面，并且在相对的前缘和后缘之间以和弦延伸。至少一些平台具有扇形流动表面，其包括邻近压力侧的凸起和邻接相应翼型件的前缘的吸力侧的碗。凸起构造成具有位于其各自的流动通道内的最大高度，并且其中凸起在前后方向上的高度减小，并且横向朝向翼型的压力侧朝向与翼的压力侧相邻的碗的高度减小下一个相邻的翼型。

2. 发明专利

JP2008051102A Conformal tip baffle aerofoil 有权
标题翻译：一致提示AEROFOIL
公开(公告)号：JP2008051102A
公开(公告)日：2008-03-06
申请号：JP2007213051
申请日：2007-08-17
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： KLASING KEVIN SAMUEL , LEE CHING-PANG , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/20 , F02C7/28
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To reduce turbine blade tipflow leakage. SOLUTION: A turbine blade 10 includes an aerofoil tip 30 having first and second ribs 36, 38 extending from a tip floor 40. The ribs 36, 38 extend along the opposite pressure and suction sides 20, 22 of the blade 10 and are joined together at opposite leading and trailing edges 24, 26. A tip baffle 42 is nested transversely between the ribs 36, 38, and conforms with the second rib 38 to bifurcate the aerofoil tip 30 into first and second tip pockets 44, 46 extending along the corresponding pressure and suction sides 20, 22. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：减少涡轮叶片尖端流量泄漏。解决方案：涡轮机叶片10包括具有从尖端底板40延伸的第一和第二肋36,38的翼面30。肋36,38沿着叶片10的相对的压力和吸力侧面20,22延伸，并且在相对的前缘和后缘24,26处连接在一起。尖端挡板42横向地嵌套在肋36,38之间，并且与第二肋38一致，以将翼面30分叉成第一和第二尖端口袋44,46延伸沿着相应的压力和吸力侧20,22。版权所有（C）2008，JPO＆INPIT

3. 发明专利

JP2012163103A Cascade tip baffle airfoil 有权
标题翻译： CASCADE TIP BAFFLE AIRFOIL
公开(公告)号：JP2012163103A
公开(公告)日：2012-08-30
申请号：JP2012059563
申请日：2012-03-16
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイ
发明人： KLASING KEVIN SAMUEL , LEE CHING-PANG , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/20 , F01D11/08 , F01D25/00 , F02C7/28
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade that reduces tip flow leakage and improves turbine efficiency.SOLUTION: The turbine blade 10 includes an airfoil tip 30 with first and second ribs 36 and 38 extending along the opposite pressure and suction sides 20 and 22. The ribs 36 and 38 extend outwardly from a tip floor 40 and are joined together at opposite leading and trailing edges 24 and 26. A cascade tip baffle 42 transversely bridges the two ribs 36 and 38 above the tip floor 40 forward of the maximum width of the tip 30 to partition the tip 30 chordally into corresponding tip pockets 44 on opposite sides of the baffle 42.
摘要翻译：要解决的问题：提供减少尖端泄漏并提高涡轮机效率的涡轮叶片。涡轮叶片10包括具有沿着相对的压力和吸力侧面20和22延伸的第一和第二肋36和38的翼型件末端30.肋36和38从尖端底板40向外延伸并连接在一起在相反的前缘和后缘24和26处。级联顶端挡板42将尖端底部40上方的两个肋36和38横向地桥接在尖端30的最大宽度的前方，以将尖端30弦状地分隔成相对的尖端口袋44 挡板42的侧面。版权所有（C）2012，JPO＆INPIT

4. 发明专利

JP2008128247A Triforial front end cavity airfoil 有权
标题翻译：四边形前端空气流
公开(公告)号：JP2008128247A
公开(公告)日：2008-06-05
申请号：JP2007299080
申请日：2007-11-19
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： LEE CHING-PANG , KLASING KEVIN SAMUEL , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/18 , F01D11/08 , F02C7/18 , F02C7/28
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade for a gas turbine engine. SOLUTION: The turbine blade 10 comprises an airfoil 12, a platform 14, and an integrated dovetail 16. The airfoil 12 has opposed positive and negative pressure side faces 20, 22 extending between opposed leading edge and trailing edge 24, 26 over a blade chord and extending over a span from a root 28 to a front end 30, and the front end 30 includes first and second ribs 36, 38 extending from a front end floor 40 along the positive and negative side faces 20, 22. The first and second ribs 36, 38 are joined at their leading edge and trailing edge 24, 26 to each other and arranged at a space in a blade cross direction, and it includes trifurcate front end baffles 42, 44, 46 having triple front end pockets 48, 50, 52 formed as counter contours extending from the second rib 38 toward the blade chord and located adjacent to one another. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于燃气涡轮发动机的涡轮机叶片。涡轮叶片10包括翼型件12，平台14和集成的燕尾16.翼型件12具有相对的正和负压侧面20,22，其在相对的前缘和后缘24,26之间延伸叶片弦，并且从根部28延伸到前端30，并且前端30包括从前端底板40沿着正和负侧面20,22延伸的第一和第二肋36,38。第一和第二肋36,38在它们的前缘和后缘24,26彼此连接并布置在叶片横向的空间处，并且它包括具有三个前端口袋的三叉形前端挡板42,44,46 48,50,52形成为从第二肋38朝向叶片弦并且彼此相邻定位的相对轮廓。版权所有（C）2008，JPO＆INPIT

5. 发明专利

JP2008051098A Reverse tip baffle type blade profile part 有权
标题翻译：反向提示纸型刀片型材零件
公开(公告)号：JP2008051098A
公开(公告)日：2008-03-06
申请号：JP2007211197
申请日：2007-08-14
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： LEE CHING-PANG , KLASING KEVIN SAMUEL , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/20 , F01D5/18 , F01D11/08 , F02C7/28
CPC分类号： F01D5/20 , F01D5/145 , F05D2250/70 , Y02T50/671 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a reverse tip baffle type turbine blade. SOLUTION: This turbine blade 10 includes a blade profile part 12 having the first and second tip ribs 36, 38 extended along positive pressure and negative pressure side faces 20, 22 thereof opposed each other. The tip ribs 36, 38 are arranged with a space between a front edge 24 and a rear edge 26 of the blade profile part 12, and includes the tip baffle 42. The baffle 42 is extended along a blade chord direction with a profile reverse to that of the first rib 36 to form the first pocket 44, and is also extended along the blade chord direction with a profile reverse to that of the second rib 38 to form the second pocket 46. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种反向顶端挡板型涡轮叶片。解决方案：该涡轮叶片10包括叶片轮廓部分12，叶片轮廓部分12具有沿着正压力延伸的第一和第二末端肋36,38和彼此相对的负压侧面20,22。末端肋36,38布置有在叶片轮廓部分12的前边缘24和后边缘26之间的空间，并且包括末端挡板42.挡板42沿叶片弦方向延伸，其轮廓与第一肋36的形状形成第一袋44，并且还沿着叶片弦弦方向延伸，具有与第二肋38的轮廓相反的轮廓，以形成第二袋46.权利要求：（C）2008， JPO＆INPIT

6. 发明专利

JP2008051097A Flared tip type turbine blade 有权
标题翻译：膨化式涡轮叶片
公开(公告)号：JP2008051097A
公开(公告)日：2008-03-06
申请号：JP2007211196
申请日：2007-08-14
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： KLASING KEVIN SAMUEL , LEE CHING-PANG , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/20 , F01D11/08 , F02C7/28 , F16J15/44
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade with reduced tipflow leakage, improved turbine efficiently, and improved tip cooling, in a gas turbine engine. SOLUTION: This turbine blade (10) includes an airfoil (12), a platform (14) on a root of the airfoil, and a support dovetail (16). The airfoil (12) has opposite positive pressure and negative pressure side surfaces (20, 22) extending chordally between leading and trailing edges (24, 26) and extending in span from the root (28) to a tip (30). The tip (30) includes first and second ribs (36, 38) conforming with the positive pressure and negative pressure side surfaces (20, 22), arranged interspecially in a blade thickness direction between the leading and tailing edges (24, 26), and forming a tip cavity (40) having a tip floor (42) surrounding the airfoil (12). The second rib (38) includes an outer surface flare (44) enlarging laterally outwardly from the negative pressure side surface (22). COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提供一种在燃气涡轮发动机中提供具有减小的尖端流量泄漏，有效改进的涡轮机和改进的尖端冷却的涡轮机叶片。解决方案：该涡轮叶片（10）包括翼型件（12），在翼型件的根部上的平台（14）和支撑燕尾榫（16）。机翼（12）具有相反的正压力和负压侧表面（20,22），其在前缘和后缘（24,26）之间弦状延伸并且在跨度上从根部（28）延伸到尖端（30）。尖端（30）包括与正压和负压侧表面（20,22）相符合的第一和第二肋（36,38），特别是在前缘和后缘（24,26）之间的叶片厚度方向上，以及形成具有围绕所述翼型件（12）的尖端底部（42）的尖端腔（40）。第二肋（38）包括从负压侧表面（22）横向向外扩大的外表面火炬（44）。版权所有（C）2008，JPO＆INPIT

7. 发明专利

JP2008051094A Tip inclined face turbine blade 有权
标题翻译： TIP INCLINED FACE涡轮叶片
公开(公告)号：JP2008051094A
公开(公告)日：2008-03-06
申请号：JP2007204372
申请日：2007-08-06
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： KLASING KEVIN SAMUEL , LEE CHING-PANG , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/18 , F01D5/20
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/292 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To reduce flow leakage in a tip, to enhance turbine efficiency, to enhance tip cooling, and to improve design of a turbine blade tip. SOLUTION: An aerofoil 12 of a turbine blade 10 has an orthogonally opposed pressure side 20 and suction side 22 extended along a blade chord direction between a front edge 24 and a rear edge 26 opposed each other, and extended longitudinally in a range from a root 28 up to the tip 30, the tip 30 forms a tip cavity 42, including the first and second tip ribs 36, 38 extended along the pressure side 20 and the suction side 22 from a tip floor 40 toward an outer direction, between the front edge 24 and the rear edge 26, and an outlet inclined face 44 is bridged to the first and second tip ribs 36, 38 in a rear junction part in the vicinity of the rear edge 26 to increase a height from the tip floor 40 toward a rear side. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：为了减少尖端中的泄漏，提高涡轮效率，增强喷嘴冷却，并改进涡轮叶片尖端的设计。解决方案：涡轮机叶片10的机翼12具有正交相对的压力侧20和吸入侧22，其沿着叶片弦方向延伸，在前边缘24和彼此相对的后边缘26之间，并且在一定范围内纵向延伸从根部28直到尖端30，尖端30形成尖端腔42，其包括沿着压力侧20延伸的第一和第二末端肋36,38，以及从尖端底面40向外侧延伸的吸力侧22，在前边缘24和后边缘26之间，并且出口倾斜面44桥接到后边缘26附近的后连接部分中的第一和第二末端肋36,38以增加与顶部底部 40朝向后方。版权所有（C）2008，JPO＆INPIT

8. 发明专利

JP2008051096A Cascade tip baffle aerofoil 有权
标题翻译： CASCADE TIP BAFFLE AEROFOIL
公开(公告)号：JP2008051096A
公开(公告)日：2008-03-06
申请号：JP2007211195
申请日：2007-08-14
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： KLASING KEVIN SAMUEL , LEE CHING-PANG , VITT PAUL HADLEY , KEITH BRIAN DAVID
IPC分类号： F01D5/20 , F01D5/18 , F01D11/08 , F02C7/28
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To improve sealing performance and cooling performance of a blade tip. SOLUTION: A turbine blade 10 includes an aerofoil tip 30 having first and second ribs 36, 38 extending along the opposite pressure and suction sides 20, 22. The ribs 36, 38 extend outwardly from a tip floor 40 and are joined together at opposite leading and trailing edges 24, 26. A cascade tip baffle 42 transversely bridges the two ribs 36, 38 above the tip floor 40 forward of the maximum width of the tip 30 to partition the tip 30 chordally into corresponding tip pockets 44 on both sides of the baffle 42. COPYRIGHT: (C)2008,JPO&INPIT
摘要翻译：要解决的问题：提高叶片尖端的密封性能和冷却性能。解决方案：涡轮机叶片10包括具有沿着相对的压力和吸力侧面20,22延伸的第一和第二肋36,38的机翼尖端30.肋36,38从尖端底板40向外延伸并连接在一起在相对的前缘和后缘24,26处。级联顶端挡板42横向地将尖端底部40上方的两个肋36,38横向地桥接在尖端30的最大宽度的前方，以将尖端30弦状地分成相应的尖端口袋44 挡板42的侧面。版权所有（C）2008，JPO＆INPIT

9. 发明专利

JP2004003471A Turbine blade with root notch 有权
公开(公告)号：JP2004003471A
公开(公告)日：2004-01-08
申请号：JP2003127032
申请日：2003-05-02
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： HERMAN WILLIAM CHARLES , NORTON BRAIN ALAN , KEITH BRIAN DAVID
IPC分类号： F01D5/14 , F01D5/30
CPC分类号： F01D5/3007 , F01D5/147 , Y02E10/721 , Y02T50/671 , Y02T50/673
摘要： PROBLEM TO BE SOLVED: To provide a turbine blade of a gas turbine engine.
SOLUTION: A turbine blade (10) includes a blade-shaped part (16) and a dovetail (18). The dovetail includes a pair of support tongues (26). A rectangular root block (26) is astride the tongues over most portions of root ends of the tongues. The block is terminated before one end face (40) of the dovetail, and a root notch (42) to selectively reduce the weight is formed there. The root block (36) is coupled with the lower tongue (26) in a first fillet (44), and the root notch (42) is connected to the block in a second fillet (46).
COPYRIGHT: (C)2004,JPO

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