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1. 发明授权

US08459956B2 Curved platform turbine blade 有权
标题翻译：弯曲平台涡轮叶片
公开(公告)号：US08459956B2
公开(公告)日：2013-06-11
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。

2. 发明申请

US20100158696A1 CURVED PLATFORM TURBINE BLADE 有权
标题翻译：弯曲平台涡轮叶片
公开(公告)号：US20100158696A1
公开(公告)日：2010-06-24
申请号：US12344058
申请日：2008-12-24
申请人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
发明人： Vidhu Shekhar Pandey , Ching-Pang Lee , Jan Christopher Schilling , Aspi Rustom Wadia , Brian David Keith , Jeffrey Donald Clements
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F01D5/3007 , F05D2240/80 , F05D2270/17 , Y02T50/673
摘要： A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a ridge to a trough, and is curved axially to complement the next adjacent curved platform.
摘要翻译：涡轮机叶片包括在其根部处的翼型件和整体式平台。该平台的立面从脊到波纹形状，并且轴向弯曲以补充下一个相邻的弯曲平台。

3. 发明授权

US06672829B1 Turbine blade having angled squealer tip 有权
标题翻译：涡轮叶片具有倾斜的尖叫尖端
公开(公告)号：US06672829B1
公开(公告)日：2004-01-06
申请号：US10196623
申请日：2002-07-16
申请人： David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
发明人： David Glenn Cherry , Ching-Pang Lee , Chander Prakash , Aspi Rustom Wadia , Brian David Keith , Steven Robert Brassfield
IPC分类号： F01D518
CPC分类号： F01D5/141 , F01D5/145 , F01D5/20 , F05D2250/292
摘要： A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.
摘要翻译：一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。这种角度在指定部分可以是基本相同的，或者可以在其上变化。因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。

4. 发明授权

US08500396B2 Cascade tip baffle airfoil 有权
公开(公告)号：US08500396B2
公开(公告)日：2013-08-06
申请号：US11507120
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

5. 发明授权

US08425183B2 Triforial tip cavity airfoil 失效
标题翻译：尖端腔翼型
公开(公告)号：US08425183B2
公开(公告)日：2013-04-23
申请号：US11602421
申请日：2006-11-20
申请人： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
发明人： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.
摘要翻译：涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。末端肋在翼型件的前缘和后缘之间间隔开，以包括限定三腔尖端腔的三尖头挡板。

6. 发明授权

US07686578B2 Conformal tip baffle airfoil 有权
标题翻译：保形挡板翼型
公开(公告)号：US07686578B2
公开(公告)日：2010-03-30
申请号：US11507121
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.
摘要翻译：涡轮机叶片包括具有从尖端底板延伸的第一和第二末端肋的翼面末端。肋沿刀片的相对的压力和吸力侧延伸并且在相对的前缘和后缘连接在一起。尖端挡板横向嵌套在肋之间，并且与第二肋条一致，以使翼型件尖端分叉成沿相应的压力侧和吸力侧延伸的第一和第二尖端口袋。

7. 发明申请

US20090324422A1 Cascade tip baffle airfoil 有权
标题翻译：级联顶端挡板翼型
公开(公告)号：US20090324422A1
公开(公告)日：2009-12-31
申请号：US11507120
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
摘要翻译：涡轮叶片包括具有沿相对的压力和吸力侧延伸的第一和第二肋的翼型端。肋从尖端底部向外延伸并且在相对的前缘和后缘处连接在一起。级联顶端挡板将尖端底部上方的两个肋横向地桥接在尖端的最大宽度的前方，以将端部弦状地分隔成挡板相对侧上的相应的尖端口。

8. 发明授权

US08512003B2 Tip ramp turbine blade 有权
标题翻译：尖端坡道涡轮叶片
公开(公告)号：US08512003B2
公开(公告)日：2013-08-20
申请号：US11507116
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/14
CPC分类号： F01D5/20 , F05D2240/307 , F05D2250/292 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/20 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.
摘要翻译：涡轮叶片包括从尖端底板延伸以限定尖端腔的第一和第二尖端肋。出口斜坡桥接肋骨，并从地板上抬高。

9. 发明申请

US20100221122A1 Flared tip turbine blade 有权
标题翻译：扩口尖端涡轮叶片
公开(公告)号：US20100221122A1
公开(公告)日：2010-09-02
申请号：US11507119
申请日：2006-08-21
申请人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
发明人： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/18 , B64C27/46
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/673
摘要： A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.
摘要翻译：涡轮机叶片包括终止于尖端的翼型件。尖端包括符合翼型件的凹入压力侧的第一肋条和与翼型件的凸形吸入侧相一致的第二肋条。第二肋从吸力侧向外张开。

10. 发明授权

US07607893B2 Counter tip baffle airfoil 有权
标题翻译：台顶挡板翼型
公开(公告)号：US07607893B2
公开(公告)日：2009-10-27
申请号：US11507132
申请日：2006-08-21
申请人： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
发明人： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F01D5/145 , F05D2250/70 , Y02T50/671 , Y02T50/673
摘要： A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a tip baffle. The baffle extends chordally in counter profile with the first rib to define a first pocket, and in counter profile with the second rib to define a second pocket.
摘要翻译：涡轮叶片包括具有沿其相对的压力和吸力侧延伸的第一和第二末端肋的翼型件。末端肋在翼型件的前缘和后缘之间间隔开，以包括顶端挡板。所述挡板以第一肋条与第一肋条相反地延伸，以相反轮廓延伸，以限定第一凹槽，并且与第二肋条对置形成第二凹槽。

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