公开(公告)号：US07008185B2

公开(公告)日：2006-03-07

申请号：US10375415

申请日：2003-02-27

申请人： Jonathan Jordan Peterman ,  Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

发明人： Jonathan Jordan Peterman ,  Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

IPC分类号： F01D9/02 ,  F01D5/18

CPC分类号： F01D5/189 ,  F01D9/041 ,  F05D2240/81 ,  F05D2250/70 ,  F05D2260/201 ,  F05D2260/30 ,  Y02T50/67 ,  Y02T50/676

摘要： 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.

摘要翻译： 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。

公开(公告)号：US06969233B2

公开(公告)日：2005-11-29

申请号：US10375585

申请日：2003-02-27

申请人： Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Jonathan Jordan Peterman ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

发明人： Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Jonathan Jordan Peterman ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

IPC分类号： F01D9/02 ,  F01D5/18 ,  F01D25/12 ,  F02C7/00 ,  F02C7/16 ,  F02C7/18 ,  F01D9/04

CPC分类号： F01D5/189 ,  B22C21/14 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/22141 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/676

摘要： 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.

摘要翻译： 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。

公开(公告)号：US06397604B2

公开(公告)日：2002-06-04

申请号：US09773369

申请日：2001-02-01

申请人： Sacheverel Quentin Eldrid ,  James Lee Burns ,  Gene David Palmer ,  Sal Albert Leone ,  Gary Joseph Drlik ,  Edward Eugene Gibler

发明人： Sacheverel Quentin Eldrid ,  James Lee Burns ,  Gene David Palmer ,  Sal Albert Leone ,  Gary Joseph Drlik ,  Edward Eugene Gibler

IPC分类号： F02C718

CPC分类号： F01D9/065 ,  F01D5/088 ,  Y02T50/673 ,  Y02T50/676

摘要： In a land based gas turbine including a compressor, a combustor and turbine section including at least three stages, an improvement comprising an inlet into a third stage nozzle from the compressor for feeding cooling air from the compressor to the third stage nozzle; at least one passageway running substantially radially through each airfoil of the third stage nozzle and an associated diaphragm, into an annular space between the rotor and the diaphragm; and passageways communicating between the annular space and individual buckets of the third stage.

摘要翻译： 在包括压缩机，燃烧器和包括至少三个级的涡轮机部分的陆基燃气轮机中，改进包括从压缩机进入到第三级喷嘴的入口，用于将冷却空气从压缩机供给到第三级喷嘴; 至少一个通道，其基本上径向地穿过第三级喷嘴的每个翼片和相关联的隔膜，进入转子和隔膜之间的环形空间; 以及在第三阶段的环形空间和各个桶之间连通的通路。

公开(公告)号：US06321447B1

公开(公告)日：2001-11-27

申请号：US09523964

申请日：2000-03-13

申请人： Kurt Neal Laurer ,  Gary Joseph Drlik ,  Edward Eugene Gibler

发明人： Kurt Neal Laurer ,  Gary Joseph Drlik ,  Edward Eugene Gibler

IPC分类号： B23P600

CPC分类号： B25B13/481 ,  B25B13/48 ,  Y10T29/49318 ,  Y10T29/49963

摘要： The concentric wrench includes an outer tube having flats at one end and a gripping surface at an opposite end. An inner tube has interior flats at one end and a gripping surface at its opposite end. With the inner and outer tubes disposed about a pressure transmitting conduit, the tubes may be inserted into a blind access opening in the outer turbine casing to engage the flats of the tubes against hex nuts of an internal fitting. By relatively rotating the tubes using the externally exposed gripping surfaces, the threaded connection between the parts of the fitting bearing the respective hex nuts can be tightened or loosened.

摘要翻译： 同心扳手包括在一端具有平面的外管和在相对端的抓握表面。 内管在一端具有内部平面，在其相对端具有夹紧表面。 在内管和外管围绕压力传递管道设置的情况下，管可插入外涡轮机壳体中的盲进入开口中，以将管道的平面与内部配件的六角螺母接合。 通过使用外部暴露的夹持表面相对旋转管，可以拧紧或拧松轴承相应的六角螺母的配件的螺纹连接。

公开(公告)号：US06932568B2

公开(公告)日：2005-08-23

申请号：US10375441

申请日：2003-02-27

申请人： Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Jonathan Jordan Peterman ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

发明人： Andrew Charles Powis ,  Ronald Eugene McRae, Jr. ,  Jonathan Philip Clarke ,  Jonathan Jordan Peterman ,  Robert Alan Frederick ,  Edward Eugene Gibler ,  Brian David Keith

IPC分类号： F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F01D25/24 ,  F02C7/18

CPC分类号： F01D9/041 ,  B22C21/14 ,  E05Y2900/402 ,  F01D5/189 ,  F01D25/246 ,  F05D2240/12 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/22141 ,  F05D2260/30 ,  Y02T50/67 ,  Y02T50/676

摘要： A turbine nozzle segment includes at least one hollow airfoil extending radially between radially outer and inner band segments, a clockwise open hook on a clockwise end at an aft end of the outer band segment, and counter-clockwise open hook on a counter-clockwise end at the aft end of the outer band segments. An exemplary embodiment of the turbine nozzle segment includes a load stop extending radially outwardly from the outer band segment. At least one aftwardly facing load face is at the aft end of the nozzle segment at the outer band segment. The clockwise open hook is C-shaped and the counter-clockwise open hook is a shiplap hook. Another embodiment of the turbine nozzle segment has only one hollow airfoil with an airfoil wall surrounding a bifurcated cavity divided into forward and aft cavities by a bifurcating rib extending between pressure and suction sides of the airfoil wall.

摘要翻译： 涡轮喷嘴段包括至少一个在径向外带段和内带段之间径向延伸的中空翼型件，在外带段的后端处的顺时针端部上的顺时针打开的钩子，以及逆时针方向的逆时针方向的开口钩 在外带段的后端。 涡轮喷嘴段的示例性实施例包括从外带段径向向外延伸的负载停止。 至少一个面向前的负载面处于外带段处的喷嘴段的后端。 顺时针打开的钩子是C形的，逆时针打开的钩子是一个shiplap钩子。 涡轮喷嘴段的另一个实施例仅具有一个中空翼型件，其翼型壁围绕通过在翼型件壁的压力侧和抽吸侧之间延伸的分叉肋分成前部和后部空腔的分叉空腔。