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1. 发明授权

US06752592B2 Supplemental seal for the chordal hinge seals in a gas turbine 失效
标题翻译：燃气轮机中的弦铰链密封的补充密封
公开(公告)号：US06752592B2
公开(公告)日：2004-06-22
申请号：US10029003
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F01D904
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 of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal 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 having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface 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轨道和喷嘴支撑环的环形轴向面对的密封表面之间具有弦状铰链密封件的燃气涡轮机中，在较低压力下在支撑环和喷嘴段的内带之间设置补充密封侧面铰链密封。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形边缘部分的大致U形补充密封件容纳在形成在喷嘴段的内轨道的轴向延伸的密封表面中的空腔中。在操作条件下，边缘部分密封在空腔的底部和喷嘴支撑环的环形密封表面上，以防止通过弦状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空腔中时固定密封件。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。

2. 发明授权

US06609886B2 Composite tubular woven seal for gas turbine nozzle and shroud interface 失效
公开(公告)号：US06609886B2
公开(公告)日：2003-08-26
申请号：US10029216
申请日：2001-12-28
申请人： Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Srikanth Vedantam , Ning Fang , Gayle Hobbs Goetze , Brian Peter Arness , John Ellington Greene , Wei-Ming Chi
发明人： Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Srikanth Vedantam , Ning Fang , Gayle Hobbs Goetze , Brian Peter Arness , John Ellington Greene , Wei-Ming Chi
IPC分类号： F01D902
CPC分类号： F16J15/0887 , F01D11/005 , F16J15/0812
摘要： A compliant woven tubular seal is provided in an arcuate cavity opening through an axial face of a plurality of shroud segments in opposition to a nozzle retaining ring. The annular composite tubular woven compliant seal includes a stainless steel inner metal core surrounded by an annular layer of silica fiber. Surrounding the silica fiber is a metal foil which prevents flow past the supplemental seal. An outer wear-resistant braiding serves as a protective covering and wear surface.

3. 发明授权

US06719295B2 Supplemental seal for the chordal hinge seals in a gas turbine 有权
标题翻译：燃气轮机中的弦铰链密封的补充密封
公开(公告)号：US06719295B2
公开(公告)日：2004-04-13
申请号：US10029226
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F16J1544
CPC分类号： F01D11/005
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment on a lower pressure side of the chordal hinge seal. The supplemental seal comprises a segmented annular composite tubular woven compliant seal disposed in a cavity along a sealing surface of the inner rail of the segment. The seal bears against the annular sealing surface of the nozzle support ring, which compresses the seal. Because of the compliant nature of the seal, a supplemental seal is formed on the low pressure side of the chordal hinge seal.
摘要翻译：在具有在每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气轮机中，在较低压力下在辅助密封件之间设置在喷嘴段的支撑环和内轨道之间侧面铰链密封。补充密封件包括沿着该段的内轨道的密封表面设置在空腔中的分段环形复合管状编织柔性密封件。密封件抵靠喷嘴支撑环的环形密封表面，压缩密封件。由于密封的顺从性，在弦铰链密封件的低压侧形成补充密封。

4. 发明授权

US06595745B1 Supplemental seal for the chordal hinge seals in a gas turbine 失效
标题翻译：燃气轮机中的弦铰链密封的补充密封
公开(公告)号：US06595745B1
公开(公告)日：2003-07-22
申请号：US10029004
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F01D904
CPC分类号： F01D11/005 , F02C7/28 , F16J15/0887
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner band of the nozzle segment on a lower pressure side of the chordal hinge seal. The supplemental seal includes a flexible sheet metal seal having a margin secured in a groove of the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Leakage flow past the chordal hinge seal exerts sealing pressure against the preloaded flexible seal to maintain the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends circumferentially and spans the joint between adjacent nozzle segments.
摘要翻译：在具有在每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气涡轮机中，在较低压力下的辅助密封件之间设置在喷嘴段的支撑环和内带之间侧面铰链密封。辅助密封件包括柔性金属片密封件，其具有固定在喷嘴段的内轨道的凹槽中的边缘，具有弯曲边缘以与其形成密封。相对的边缘具有抵靠喷嘴支撑环的轴向相对的密封表面的边缘。通过弦杆铰链密封件的泄漏流动对预加载的柔性密封件施加密封压力，以保持支撑环和段的密封表面之间的密封。辅助密封件周向延伸并跨过相邻喷嘴段之间的接头。

5. 发明授权

US06655913B2 Composite tubular woven seal for an inner compressor discharge case 有权
公开(公告)号：US06655913B2
公开(公告)日：2003-12-02
申请号：US10045023
申请日：2002-01-15
申请人： Srikanth Vedantam , Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Ning Fang
发明人： Srikanth Vedantam , Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Ning Fang
IPC分类号： F01D2528
CPC分类号： F16J15/128 , F04D29/083 , F16J15/0812 , F16J15/121
摘要： Upper and lower halves of the inner barrel of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves are provided in the margin of one of the barrel halves. Elongated composite tubular woven seals 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 surrounded by an annular silica fiber layer, in turn surrounded by a metal foil with an outer protective covering of a braided stainless steel. 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. 发明授权

US06652231B2 Cloth seal for an inner compressor discharge case and methods of locating the seal in situ 有权
标题翻译：用于内部压缩机排放箱的布密封件和原位置密封件的方法
公开(公告)号：US06652231B2
公开(公告)日：2003-11-25
申请号：US10047988
申请日：2002-01-17
申请人： Srikanth Vedantam , Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Ning Fang
发明人： Srikanth Vedantam , Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Ning Fang
IPC分类号： F01D1100
CPC分类号： F01D11/005 , F02C7/28 , F05D2240/55 , F05D2300/6012 , F16J15/061 , F16J15/0812
摘要： Upper and lower halves of the inner barrel of a compressor for a turbine are bolted to one another along a horizontal midline joint with metal-to-metal surface contact. Elongated grooves are provided in the engaging surfaces, with the upper groove having a depth greater than the depth of the lower groove. Elongated seals are provided in the grooves, including an elongated shim with a metallic woven covering on opposite sides, and margins having sealing edges. The depth of the seal is equal to or less than the depth of the upper groove and an adherent material maintains the seal in the upper groove during installation. In operation, the adherent material dissolves at temperatures above ambient and the seal drops by gravity to bear against the walls of the grooves in response to high pressure air leaking through any gap at the horizontal midline joint.
摘要翻译：用于涡轮机的压缩机的内筒的上半部和下半部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。细长的槽设置在接合表面中，上槽的深度大于下槽的深度。细长的密封件设置在凹槽中，包括细长垫片，金属编织覆盖物在相对的两侧，边缘具有密封边缘。密封件的深度等于或小于上槽的深度，并且粘合材料在安装期间将密封件保持在上槽中。在操作中，粘附材料在高于环境温度的温度下溶解，并且密封件通过重力下降以响应于在水平中线接头处的任何间隙泄漏的高压空气而抵靠在槽的壁上。

7. 发明授权

US06764081B2 Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation 失效
标题翻译：燃气轮机中的弦铰链密封件的补充密封和安装方法
公开(公告)号：US06764081B2
公开(公告)日：2004-07-20
申请号：US10028932
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F16J1502
CPC分类号： F16J15/0887 , F01D11/005
摘要： In a gas turbine, a supplemental seal is provided between an annular axially facing sealing surface of a nozzle support ring and an annular axially opposed sealing surface formed by circumferentially adjacent nozzle segments. Each segment carries an inner rail mounting a chordal hinge seal which engages the sealing surface of the nozzle support ring. That seal is supplemented by a generally arcuate V-shaped seal between the sealing surfaces which opens radially inwardly toward a high pressure leakage path past the chordal hinge seal. The supplemental seal is initially compressed and maintained in a compressed condition during installation by application of a solder. At operating temperature, the solder melts away, releasing the supplemental seal to seal between the nozzle support ring and nozzle segments.
摘要翻译：在燃气轮机中，在喷嘴支撑环的环形轴向面对的密封表面和由周向相邻的喷嘴段形成的环形轴向相对的密封表面之间提供补充密封。每个段都带有一个内轨道，其安装一个与喷嘴支撑环的密封表面接合的弦索铰链密封件。在密封表面之间通过弧形的V形密封件补充该密封件，该密封表面径向向内朝着通过弦杆铰链密封件的高压泄漏路径开口。在安装期间，通过施加焊料，补充密封件被初始压缩并保持在压缩状态。在操作温度下，焊料熔化掉，释放补充密封件以密封喷嘴支撑环和喷嘴段之间。

8. 发明授权

US06659472B2 Seal for gas turbine nozzle and shroud interface 失效
公开(公告)号：US06659472B2
公开(公告)日：2003-12-09
申请号：US10028928
申请日：2001-12-28
申请人： Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Srikanth Vedantam , Ning Fang , Gayle Hobbs Goetze , Brian Peter Arness , John Ellington Greene , Wei-Ming Chi
发明人： Mahmut Faruk Aksit , Ahmad Safi , Abdul-Azeez Mohammed-Fakir , Srikanth Vedantam , Ning Fang , Gayle Hobbs Goetze , Brian Peter Arness , John Ellington Greene , Wei-Ming Chi
IPC分类号： F16J1502
CPC分类号： F01D11/003 , F01D11/005 , F02C7/28
摘要： In a gas turbine including a nozzle retaining ring having a first annular axially sealing surface and a shroud segment having an axial registering second surface. To minimize or prevent leakage flow between the retaining ring and shroud segments, a generally U-shaped seal having reversely folded U-shaped marginal portions is received in a cavity formed in the second surface. At operating conditions, the marginal portions seal against the base of the cavity and the first surface of the retaining ring to prevent leakage flow past the retaining ring/shroud segment interface. To install the seal, the seal body 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 against opposite sealing surfaces of the shroud segments and retaining ring.

9. 发明授权

US06641144B2 Supplemental seal for the chordal hinge seals in a gas turbine 失效
标题翻译：燃气轮机中的弦铰链密封的补充密封
公开(公告)号：US06641144B2
公开(公告)日：2003-11-04
申请号：US10028924
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F01D904
CPC分类号： F16J15/0887 , F01D11/005
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a flexible supplemental seal is disposed between the support ring and inner band 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 of the flexible seal engages in a linear groove carried by the inner rail. The opposite margin 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轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气涡轮机中，柔性补充密封件设置在喷嘴段的支撑环和内带之间的径向向内弦铰链密封。为了最小化或防止跨越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延伸，该密封表面在弦向铰链密封件的径向向内。柔性密封件的第一边缘接合由内轨道承载的直线槽。相对的边缘与喷嘴支撑环密封接合地弓形延伸。

10. 发明授权

US06572331B1 Supplemental seal for the chordal hinge seals in a gas turbine 有权
标题翻译：燃气轮机中的弦铰链密封的补充密封
公开(公告)号：US06572331B1
公开(公告)日：2003-06-03
申请号：US10029228
申请日：2001-12-28
申请人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
发明人： Abdul-Azeez Mohammed-Fakir , Mahmut Faruk Aksit , Ahmad Safi , Srikanth Vedantam , Ning Fang
IPC分类号： F01D904
CPC分类号： F01D11/005 , F16J15/0887
摘要： In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner rail of the nozzle segment. The supplemental seal is formed of a preloaded flexible sheet metal seal having a first margin secured in a linear groove extending in a tangential direction along the inner rail of the nozzle segments with a bent-over edge to form a seal therewith. The opposite second margin has an edge which bears against the axially opposed sealing surface of the nozzle support ring. Sealing pressure against the preloaded flexible seal from a high pressure region maintains the seal between the sealing surfaces of the support ring and segments. The supplemental seal extends tangentially and end edges thereof overlap one another to form a seal between adjacent nozzle segments.
摘要翻译：在具有每个喷嘴段的内轨道和喷嘴支撑环的环形轴向相对的密封表面之间具有弦状铰链密封件的燃气轮机中，在喷嘴段的支撑环和内轨道之间设置补充密封。辅助密封件由预加载的柔性金属片密封件形成，该密封件具有固定在沿着沿喷嘴段的内轨道的切线方向延伸的直线槽中的第一边缘，具有弯曲边缘以与其形成密封。相对的第二边缘具有抵靠喷嘴支撑环的轴向相对的密封表面的边缘。从高压区域对预加载的柔性密封件的密封压力保持了支撑环的密封表面和段之间的密封。辅助密封件切向延伸并且其端部边缘彼此重叠以在相邻的喷嘴段之间形成密封。

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