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公开(公告)号：US08500396B2
公开(公告)日：2013-08-06
申请号：US11507120
申请日：2006-08-21
Applicant: Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
Inventor： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC: F01D5/20
CPC classification number: F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: 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.
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公开(公告)号：US08425183B2
公开(公告)日：2013-04-23
申请号：US11602421
申请日：2006-11-20
Applicant: Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
Inventor： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
IPC: F01D5/20
CPC classification number: F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20130224027A1
公开(公告)日：2013-08-29
申请号：US13407905
申请日：2012-02-29
Applicant: Brian Chandler Barr , Brian David Keith , Gregory John Kajfasz , Prem Venugopal
Inventor： Brian Chandler Barr , Brian David Keith , Gregory John Kajfasz , Prem Venugopal
CPC classification number: F01D5/145 , F01D5/143 , F05D2240/80 , F05D2250/20 , Y02T50/673
Abstract: A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.
Abstract translation: 涡轮级包括连接到相应平台的一排翼型件，以限定它们之间的流动通道。 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延伸成弦。 每个平台具有扇形流动表面，包括在平台的混合区域中切向开始的净化槽。 清洗槽轴向延伸到翼型的吸入侧，前缘的后部，以引导吹扫流。
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公开(公告)号：US20090324422A1
公开(公告)日：2009-12-31
申请号：US11507120
申请日：2006-08-21
Applicant: Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
Inventor： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC: F01D5/18
CPC classification number: F01D5/20 , F01D5/187 , F05D2250/70 , F05D2260/202 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20080101959A1
公开(公告)日：2008-05-01
申请号：US11586952
申请日：2006-10-26
Applicant: Ronald Eugene McRae , Brian David Keith , Andrew Edward Obermeyer , Leslie Eugene Leeke
IPC: B64C27/46
CPC classification number: F01D5/141 , F05D2250/74 , Y10S416/02
Abstract: An airfoil for a rotor blade including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y and Z to facilitate balancing performance and durability of the rotor blade and to facilitate improving an operating efficiency of a high-pressure turbine is provided. The profile is carried only to four decimal places, wherein Y represents a distance from a platform on which the airfoil is mounted, and X and Z are coordinates defining the profile at each distance Y from the platform.
Abstract translation: 提供了一种用于转子叶片的翼型件，其包括基本上根据X，Y和Z的笛卡尔坐标值的未涂覆轮廓，以便于平衡转子叶片的性能和耐久性，并且有助于提高高压涡轮机的操作效率。 配置文件仅承载四位小数，其中Y表示与安装有翼型件的平台的距离，X和Z是从平台每个距离Y定义轮廓的坐标。
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Patent Agency Ranking
公开(公告)号：US07008185B2
公开(公告)日：2006-03-07
申请号：US10375415
申请日：2003-02-27
Applicant: Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
Inventor： Jonathan Jordan Peterman , Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC classification number: F01D5/189 , F01D9/041 , F05D2240/81 , F05D2250/70 , F05D2260/201 , F05D2260/30 , Y02T50/67 , Y02T50/676
Abstract: A turbine nozzle bifurcated impingement baffle includes axially forward and aft chambers with a gap therebetween, impingement holes through forward and aft baffle walls of the forward and aft chambers respectively, and a plenum chamber in fluid flow communication with the forward and aft chambers. An exemplary embodiment of the bifurcated impingement baffle further includes a single cooling air inlet to the plenum chamber enclosed within a plenum chamber enclosure the plenum chamber. A sealing plate is mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers. The sealing plate has forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively. Forward and aft end plates cap radially inner ends of the forward and aft chambers. An outlet aperture in the forward end plate has an interstage seal cavity feed tube disposed therethrough.
Abstract translation: 涡轮喷嘴分叉冲击挡板包括轴向前后空间，其间具有间隙，冲击孔分别通过前后舱的前后挡板壁和与前室和后室流体连通的增压室。 分叉式冲击挡板的示例性实施例还包括一个单独的冷却空气入口，该冷却空气入口封闭在包围增压室的增压室内。 密封板安装在密封室之间并密封到增压室外壳和前后室。 密封板具有分别设置在增压室和前后室之间的前后入口孔。 前端和后端板盖住前后室的径向内端。 前端板中的出口孔具有穿过其设置的级间密封腔供给管。
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7.发明授权Gas turbine engine turbine nozzle segment with a single hollow vane having a bifurcated cavity 有权燃气涡轮发动机涡轮喷嘴段具有单个空心叶片，其具有分叉腔公开(公告)号：US06969233B2
公开(公告)日：2005-11-29
申请号：US10375585
申请日：2003-02-27
Applicant: Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
Inventor： Andrew Charles Powis , Ronald Eugene McRae, Jr. , Jonathan Philip Clarke , Jonathan Jordan Peterman , Robert Alan Frederick , Edward Eugene Gibler , Brian David Keith
CPC classification number: F01D5/189 , B22C21/14 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
Abstract: A turbine nozzle segment includes a single hollow airfoil extending radially between radially outer and inner band segments. The airfoil has an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil. The airfoil wall surrounds a bifurcated cavity and a bifurcating rib extends through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities. A stiffening rib extends radially outwardly from and along a radially outer surface of the outer band segment and axially and circumferentially from a pressure side forward corner of the outer band segment to the bifurcating rib. The outer and inner band segments, the bifurcating rib, and the stiffening rib are integral and made from a unitary one-piece casting.
Abstract translation: 涡轮喷嘴段包括在径向外部段和内部带段之间径向延伸的单个中空翼型件。 翼型件具有翼型壁，其压力和吸力侧面在翼型的前缘和后缘之间轴向延伸。 翼型壁围绕分叉的空腔并且分叉肋延伸穿过分叉的空腔，并且在翼型壁的压力和吸力侧之间延伸，将分叉腔分成前后空腔。 加强筋从外带段的径向外表面径向向外延伸，并且从外带段的压力侧前角轴向和周向延伸到分叉肋。 外带和内带段，分叉肋和加强筋是整体的，由一体式单件铸件制成。
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公开(公告)号：US08632311B2
公开(公告)日：2014-01-21
申请号：US11507119
申请日：2006-08-21
Applicant: Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
Inventor： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC: F01D5/14
CPC classification number: F01D5/20 , F05D2250/712 , Y02T50/673
Abstract: 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.
Abstract translation: 涡轮叶片包括终止在尖端中的翼型件。 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。
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公开(公告)号：US20080044291A1
公开(公告)日：2008-02-21
申请号：US11507132
申请日：2006-08-21
Applicant: Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
Inventor： Ching-Pang Lee , Kevin Samuel Klasing , Paul Hadley Vitt , Brian David Keith
IPC: B64C11/16
CPC classification number: F01D5/20 , F01D5/145 , F05D2250/70 , Y02T50/671 , Y02T50/673
Abstract: 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.
Abstract translation: 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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公开(公告)号：US20080044290A1
公开(公告)日：2008-02-21
申请号：US11507121
申请日：2006-08-21
Applicant: Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
Inventor： Kevin Samuel Klasing , Ching-Pang Lee , Paul Hadley Vitt , Brian David Keith
IPC: B64C11/16
CPC classification number: F01D5/20 , F01D5/187 , F05D2250/185 , F05D2250/70 , Y02T50/673 , Y02T50/676
Abstract: 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.
Abstract translation: 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。
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