-
公开(公告)号：EP1323897B1
公开(公告)日：2007-08-22
申请号：EP02258883.4
申请日：2002-12-23
发明人： Mohammed-Fakir, Abdul-Azeez , Safi, Ahmad , Fang, Ning , Aksit, Mahmut Faruk , Vedantam, Srikanth
CPC分类号： F01D11/005 , F02C7/28 , F16J15/0887
-
公开(公告)号：EP1503045A2
公开(公告)日：2005-02-02
申请号：EP04254576.4
申请日：2004-07-30
发明人： Turnquist, Norman Arnold , Dinc, Osman Saim , Demiroglu, Mehmet , Fang, Biao , Sarshar, Hamid Reza , Burnett, Mark Edward , Baily, Frederick George , Safi, Ahmad , Aksit, Mahmut Faruk , Larsen, Richard Robert
IPC分类号： F01D25/16
CPC分类号： F16J15/445 , F01D11/025 , F04D27/0292 , F04D29/102 , F05D2240/55 , F05D2240/56 , F05D2250/182 , F05D2250/183 , F05D2270/62 , F16J15/3288 , F16J15/442
摘要： A seal assembly (24) includes an annular hanger (42) having a supporting ledge (44). An arcuate seal segment (46) includes an outer rail (50) mounted on the ledge and supporting an inner seal (54). An arcuate carrier (56) is mounted between the hanger (42) and the rail (50), and includes a piston (58) mounted in a bore (60). The bore (60) is selectively pressurized to deploy the piston (58) between the hanger and rail for temporarily retracting the seal segment from an adjacent rotor component (14).
摘要翻译： 密封组件（24）包括具有支撑凸缘（44）的环形悬挂器（42）。 弓形密封段（46）包括安装在凸缘上并支撑内密封件（54）的外轨（50）。 弓形托架（56）安装在悬挂器（42）和导轨（50）之间，并且包括安装在孔（60）中的活塞（58）。 孔（60）被选择性地加压以将活塞（58）展开在悬挂架和轨道之间，以便临时从相邻的转子部件（14）缩回密封部分。
-
公开(公告)号：EP1323891A3
公开(公告)日：2004-05-26
申请号：EP02258830.5
申请日：2002-12-23
发明人： Mohammed-Fakir, Abdul-Azeez , Aksit, Mahmut Faruk , Safi, Ahmad , Vedantam, Srikanth , Fang, Ning
IPC分类号： F01D11/00
CPC分类号： F16J15/0887 , F01D11/005
摘要： In a gas turbine having a chordal hinge seal (46) between an inner rail (52) of each nozzle segment and an annular axially facing sealing surface (54) of a nozzle support ring (44), a flexible supplemental seal (70) is disposed between the support ring and inner band (52) of the nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the flexible seal extends between the inner rail and the sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin (74) of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin (78) extends arcuately in sealing engagement with the nozzle support ring.
-
公开(公告)号：EP1323899A3
公开(公告)日：2004-03-31
申请号：EP02258886.7
申请日：2002-12-23
发明人： Aksit, Mahmut Faruk , Safi, Ahmad , Mohammed-Fakir, Abdul-Azeez , Dean, Gilbert Joseph , Martin, Thomas Paul
CPC分类号： F16J15/0887 , F01D11/005 , F02C7/28
摘要： In a gas turbine having a chordal hinge seal between an inner rail (52) of each nozzle segment and an annular axially facing sealing surface (54) of a nozzle support ring (44), a supplemental seal (70) is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a sheet metal seal supported by a bracket secured to the back side and radial inner surfaces (79, 80) of the inner rail. The sheet metal seal has a flexible margin (86) which is preloaded and bears against the annular sealing surface of the nozzle support ring. The bracket is bolted (96) or welded to the inner rail with the sheet metal seal therebetween inhibiting or precluding leakage past the back side of the supplemental seal.
摘要翻译： 在每个喷嘴段的内轨道（52）与喷嘴支撑环（44）的环形轴向面对密封表面（54）之间具有弦状铰链密封件的燃气涡轮机中，辅助密封件（70）设置在支撑件 在所述弦铰链密封件的高压侧上的所述喷嘴段的环形和内轨道。 辅助密封件包括由固定到内侧轨道的后侧和径向内表面（79,80）的托架支撑的金属片密封件。 金属板密封件具有预加载的柔性边缘（86）并抵靠喷嘴支撑环的环形密封表面。 支架用螺栓（96）或焊接到内轨道，其间的金属片密封件阻止或阻止泄漏通过补充密封件的背面。
-
公开(公告)号：EP1327801A3
公开(公告)日：2004-01-28
申请号：EP03250134.8
申请日：2003-01-09
发明人： Vedantam, Srikanth , Safi, Ahmad , Ning, Fang , Aksit, Mahmut Faruk , Mohammed-Fakir, Abdul Azeez
CPC分类号： F16J15/128 , F04D29/083 , F16J15/0812 , F16J15/121
摘要： Upper and lower halves (28, 30) of the inner barrel (22) of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves (36) are provided in the margin (34) of one of the barrel halves. Elongated composite tubular woven seals (36) are provided in the grooves, the seals having a diameter in excess of the depth of the grooves. The seals comprise an inner woven metal core (42) surrounded by an annular silica fiber layer (44), in turn surrounded by a metal foil (46) with an outer protective covering of a braided stainless steel (48). Upon joining the upper and lower halves, the compliant seal is crushed within the groove, maintaining a seal between the barrel halves in the event of warpage of the compressor casing during turbine operation.
-
6.发明公开A composite tubular woven seal for an inner compressor discharge case 有权RohrförmigeVerbundgewebedichtungfürdasAuslassgehäuseeines Innenverdichters
公开(公告)号：EP1327801A2
公开(公告)日：2003-07-16
申请号：EP03250134.8
申请日：2003-01-09
发明人： Vedantam, Srikanth , Safi, Ahmad , Ning, Fang , Aksit, Mahmut Faruk , Mohammed-Fakir, Abdul Azeez
IPC分类号： F16J15/12
CPC分类号： F16J15/128 , F04D29/083 , F16J15/0812 , F16J15/121
摘要： Upper and lower halves (28, 30) of the inner barrel (22) of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves (36) are provided in the margin (34) of one of the barrel halves. Elongated composite tubular woven seals (36) are provided in the grooves, the seals having a diameter in excess of the depth of the grooves. The seals comprise an inner woven metal core (42) surrounded by an annular silica fiber layer (44), in turn surrounded by a metal foil (46) with an outer protective covering of a braided stainless steel (48). Upon joining the upper and lower halves, the compliant seal is crushed within the groove, maintaining a seal between the barrel halves in the event of warpage of the compressor casing during turbine operation.
摘要翻译： 用于涡轮的压缩机的内筒（22）的上下半部（28,30）沿着具有金属对金属表面接触的水平中线接头彼此螺栓连接。 细长的槽（36）设置在其中一个镜筒半部的边缘（34）中。 细长的复合管状编织密封件（36）设置在凹槽中，密封件的直径超过凹槽的深度。 密封件包括由环形二氧化硅纤维层（44）包围的内部编织金属芯（42），然后被金属箔（46）包围，并具有编织不锈钢（48）的外部保护层。 在接合上半部和下半部时，柔性密封件在凹槽内被破碎，在涡轮机操作期间在压缩机壳体翘曲的情况下保持两半之间的密封。
-
7.发明公开Supplemental seal for the chordal hinge seals in a gas turbine 有权ZusatzdichtungfürStatorelemente einer Gurburbine
公开(公告)号：EP1323894A2
公开(公告)日：2003-07-02
申请号：EP02258863.6
申请日：2002-12-23
发明人： Mohammed-Fakir, Abdul-Azeez , Safi, Ahmad , Fang, Ning , Aksit, Mahmut Faruk , Vedantam, Srikanth
CPC分类号： F16J15/0887 , F01D11/005 , F02C7/28
摘要： In a gas turbine having a chordal hinge seal between an inner rail (52) of each nozzle segment and an annular axially facing sealing surface (54) of a nozzle support ring (44), a supplemental seal (70) is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal (70) having reversely folded U-shaped marginal portions (74) is received in a cavity formed in the axially extending sealing surface of the inner rail (52) of the nozzle segment. At operating conditions, the marginal portions (74) seal against the base of the cavity and the annular sealing surface (54) of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path. To install the supplemental seal, the seal is first compressed and maintained in a compressed state by applying one or more wraps about the supplemental seal or an epoxy to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions against opposite sealing surfaces of the nozzle segment and support ring.
摘要翻译： 在具有在每个喷嘴段的内部轨道（52）和喷嘴支撑环（44）的环形轴向面对的密封表面（54）之间的弦状铰链密封件的燃气轮机中，辅助密封件（70）设置在支撑件 弦和铰链密封件的下压侧上的喷嘴段的环和内带。 为了最小化或防止跨弦铰链密封件的泄漏流动，具有反向折叠的U形边缘部分（74）的大致U形补充密封件（70）被容纳在形成在内轨道的轴向延伸的密封表面中的空腔中 52）。 在操作条件下，边缘部分（74）密封空腔的基部和喷嘴支撑环的环形密封表面（54），以防止经过铰链密封件的泄漏流进入热气路径。 为了安装补充密封件，首先将密封件压缩并保持在压缩状态，通过在补充密封件或环氧树脂周围施加一个或多个包装件以在压缩在腔体中时固定密封件。 在操作温度下，保持装置释放密封件以将边缘部分接合在喷嘴段和支撑环的相对的密封表面上。
-
8.发明公开Supplemental seal for the chordal hinge seals in a gas turbine 有权ErgänzungsdichtungfürVerdichtung einer SehnenscharnierbefestigungfürGasturbinen
公开(公告)号：EP1323891A2
公开(公告)日：2003-07-02
申请号：EP02258830.5
申请日：2002-12-23
发明人： Mohammed-Fakir, Abdul-Azeez , Aksit, Mahmut Faruk , Safi, Ahmad , Vedantam, Srikanth , Fang, Ning
IPC分类号： F01D11/00
CPC分类号： F16J15/0887 , F01D11/005
摘要： In a gas turbine having a chordal hinge seal (46) between an inner rail (52) of each nozzle segment and an annular axially facing sealing surface (54) of a nozzle support ring (44), a flexible supplemental seal (70) is disposed between the support ring and inner band (52) of the nozzle segment radially inwardly of the chordal hinge seal. To minimize or prevent leakage flow across the chordal hinge seal, the flexible seal extends between the inner rail and the sealing surface of the support ring radially inwardly of the chordal hinge seal. A first margin (74) of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin (78) extends arcuately in sealing engagement with the nozzle support ring.
摘要翻译： 在具有在每个喷嘴段的内部轨道（52）和喷嘴支撑环（44）的环形轴向面对的密封表面（54）之间的弦状铰链密封件（46）的燃气轮机中，柔性补充密封件（70）是 设置在所述支撑环和所述喷嘴段的内带（52）之间，所述内带（52）在所述弦铰链密封件的径向内侧。 为了最小化或防止跨过铰链密封件的泄漏流动，柔性密封件在内侧轨道和支撑环的密封表面之间在弦向铰链密封件的径向向内延伸。 柔性密封件的第一边缘（74）接合由内轨道承载的直线槽。 相对的边缘（78）与喷嘴支撑环的密封接合弓形延伸。
-
公开(公告)号：EP1323890A3
公开(公告)日：2004-05-19
申请号：EP02258829.7
申请日：2002-12-23
CPC分类号： F02C7/28 , F01D11/005 , F16J15/0812
摘要： In a gas turbine having a chordal hinge seal between an inner rail (52) of each nozzle segment and an annular axially facing sealing surface (54) of a nozzle support ring (44), a supplemental seal (70) is disposed between the support ring and inner rail of the nozzle segment on a high pressure side of the chordal hinge seal. The supplemental seal includes a pair of sheet metal shims (72, 74) overlaid by a woven metallic cloth (76) supported by a bracket (80) secured to a back side surface of the inner rail. The radially inner end of the cloth seal bears against the annular sealing surface of the nozzle support ring. The shims of the legs of the supplemental seal are slit (104, 108) along their distal margin (100) and staggered in a chord-wise direction relative to one another to provide flexibility and effective sealing engagement with the nozzle support ring.
-
公开(公告)号：EP1323893A3
公开(公告)日：2004-04-21
申请号：EP02258862.8
申请日：2002-12-23
CPC分类号： F16J15/0887 , F01D11/005 , F02C7/28 , Y10S277/931
摘要： In a gas turbine including a nozzle retaining ring (42) having a first annular axially facing sealing surface (48) and a shroud segment (41) having an axial registering second surface (46). To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal ((70) having reversely folded U-shaped marginal portions is received in a cavity (80) formed in the second surface. At operating conditions, the marginal portions seal against the base (82) of the cavity and the first surface (48) of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body (71) is first compressed and maintained in a compressed state by applying one or more wraps about the seal body and an epoxy is used to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions (74) \against opposite sealing surfaces of the shroud segments and retaining ring.
-
-
-
-
-
-
-
-
-
搜索结果
47 条记录 (耗时 0.013 秒)
