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1. 发明授权

US09945484B2 Turbine seals 有权
公开(公告)号：US09945484B2
公开(公告)日：2018-04-17
申请号：US13276481
申请日：2011-10-19
申请人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F02C7/28 , F16J15/02 , F16J15/08 , F01D11/00
CPC分类号： F16J15/0887 , F01D11/003 , F01D11/005
摘要： A seal strip (60A, 60B, 60C, 60F, 60G, 60H, 60J) with an imperforate width-spanning portion (64) first and second rounded edges (65, 66) and one or more strip-thickening elements (67, 68, 74, 76, 82, 84, 90, 91) between the rounded edges. The strip-thickening elements may have transverse slots (80, 86, 88, 93L, 93R, 72, 78) for increased flexibility of the strip. The strip-thickening elements may also have perforations (92) or gaps (69) to admit coolant and/or to reduce weight. Folded embodiments (60A, 60B) may have dimples (70) on the width-spanning portion (64) to limit bending of the folded portions (67, 68, 74, 76). The seal may be slidably mounted in opposed slots (58A, 58B) in respective adjacent turbine components (54A, 54B), filling a width (W) of the slots, and a side of the seal may be cooled by compressed air (48).

2. 发明授权

US08562000B2 Turbine combustion system transition piece side seals 有权
标题翻译：涡轮燃烧系统过渡片侧封
公开(公告)号：US08562000B2
公开(公告)日：2013-10-22
申请号：US13276439
申请日：2011-10-19
申请人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F16J15/02
CPC分类号： F01D9/023 , F01D11/005 , F05D2240/55 , F05D2250/292
摘要： A seal strip (54) with a central relatively thin portion (68) and first and second thicker side portions (70, 72) that may be wedge-shaped adjacent the central portion. Each side portion may be formed of a linear array of base-in prisms (56), where each prism includes a base adjacent and normal to the central portion, and a thickness tapering distally toward an adjacent edge of the seal strip. The base-in prisms of each side portion may be separated by transverse slots (55) along the length of the strip. The transverse slots of the first side portion may be unaligned with the transverse slots of the second side portion along the length of the strip. A retention pin (58) may extend normally from an end of the seal strip. The seal strip may be mounted in tapered slots (49) of a gas turbine transition exit frame (48).
摘要翻译：具有中心相对较薄部分（68）的密封条（54）和与中心部分相邻可以楔形的第一和第二较厚侧部（70,72）。每个侧部可以由基底棱镜（56）的线性阵列形成，其中每个棱镜包括与中心部分相邻并垂直于中心部分的基部，以及朝向密封条的相邻边缘向远侧渐缩的厚度。每个侧部分的基底棱镜可以沿着带的长度被横向狭槽（55）分开。第一侧部分的横向狭槽可以沿着条的长度与第二侧部的横向槽不对齐。保持销（58）可以从密封条的端部正常延伸。密封条可以安装在燃气轮机过渡出口框架（48）的锥形槽（49）中。

3. 发明授权

US09879555B2 Turbine combustion system transition seals 有权
公开(公告)号：US09879555B2
公开(公告)日：2018-01-30
申请号：US13279396
申请日：2011-10-24
申请人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F02C7/28 , F01D11/00 , F01D9/02
CPC分类号： F01D11/005 , F01D9/023 , F05D2230/21 , F05D2230/232 , F05D2240/55 , F05D2260/37 , F05D2260/38
摘要： Respective seals (54, 78) for the upper and lower spans (48A, 48B) of an exit frame (48) of a turbine combustion system transition piece (28). Each seal has a first strip (55, 79) and a second strip (66, 88) of a sealing material. The two strips of each seal are attached together along a common edge. The second strip is flexible, generally parallel to the first strip, and has a bead (72, 90) along its free edge. This forms a spring clamp that clamps a rail (68, 86) of the exit frame between the bead and the first strip of each seal. A tab extends axially aft from the first strip of each seal for insertion into a circumferential slot (58, 82) in a turbine inlet support structure (52, 76), thus sealing the transition piece (46) to the turbine inlet for efficient turbine operation.

4. 发明申请

US20120292862A1 TURBINE SEALS 有权
标题翻译：涡轮密封
公开(公告)号：US20120292862A1
公开(公告)日：2012-11-22
申请号：US13276481
申请日：2011-10-19
申请人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： Frank Moehrle , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F02C7/28 , F16J15/02
CPC分类号： F16J15/0887 , F01D11/003 , F01D11/005
摘要： A seal strip (60A, 60B, 60C, 60F, 60G, 60H, 60J) with an imperforate width-spanning portion (64) first and second rounded edges (65, 66) and one or more strip-thickening elements (67, 68, 74, 76, 82, 84, 90, 91) between the rounded edges. The strip-thickening elements may have transverse slots (80, 86, 88, 93, 93R, 72, 78) for increased flexibility of the strip. The strip-thickening elements may also have perforations (92) or gaps (69) to admit coolant and/or to reduce weight. Folded embodiments (60A, 60B) may have dimples (70) on the width-spanning portion (64) to limit bending of the folded portions (67, 68, 74, 76). The seal may be slidably mounted in opposed slots (58A, 58B) in respective adjacent turbine components (54A, 54B), filling a width (W) of the slots, and a side of the seal may be cooled by compressed air (48).
摘要翻译：具有无孔宽度跨度部分（64）的密封条（60A，60B，60C，60F，60G，60H，60J）第一和第二圆形边缘（65,66）和一个或多个带状增厚元件（67,68 ，74,76,82,84,90,91）之间。条带增厚元件可以具有横向狭槽（80,86,88,93,93R，72,78），用于增加带材的柔性。带状增厚元件还可以具有允许冷却剂和/或减轻重量的穿孔（92）或间隙（69）。折叠实施例（60A，60B）可以在宽度跨越部分（64）上具有凹坑（70）以限制折叠部分（67,68,74,76）的弯曲。密封件可以可滑动地安装在相应的相邻涡轮机部件（54A，54B）中的相对的狭槽（58A，58B）中，填充狭槽的宽度（W），密封件的侧面可以被压缩空气（48）冷却，。

5. 发明申请

US20120292861A1 TURBINE COMBUSTION SYSTEM TRANSITION PIECE SIDE SEALS 有权
标题翻译：涡轮燃烧系统过渡边密封
公开(公告)号：US20120292861A1
公开(公告)日：2012-11-22
申请号：US13276439
申请日：2011-10-19
申请人： FRANK MOEHRLE , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： FRANK MOEHRLE , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F02C7/28
CPC分类号： F01D9/023 , F01D11/005 , F05D2240/55 , F05D2250/292
摘要： A seal strip (54) with a central relatively thin portion (68) and first and second thicker side portions (70, 72) that may be wedge-shaped adjacent the central portion. Each side portion may be formed of a linear array of base-in prisms (56), where each prism includes a base adjacent and normal to the central portion, and a thickness tapering distally toward an adjacent edge of the seal strip. The base-in prisms of each side portion may be separated by transverse slots (55) along the length of the strip. The transverse slots of the first side portion may be unaligned with the transverse slots of the second side portion along the length of the strip. A retention pin (58) may extend normally from an end of the seal strip. The seal strip may be mounted in tapered slots (49) of a gas turbine transition exit frame (48).
摘要翻译：具有中心相对较薄部分（68）的密封条（54）和与中心部分相邻可以楔形的第一和第二较厚侧部（70,72）。每个侧部可以由基底棱镜（56）的线性阵列形成，其中每个棱镜包括与中心部分相邻并垂直于中心部分的基部，以及朝向密封条的相邻边缘向远侧渐缩的厚度。每个侧部分的基底棱镜可以沿着带的长度被横向狭槽（55）分开。第一侧部分的横向狭缝可以沿着条带的长度与第二侧部分的横向槽不对齐。保持销（58）可以从密封条的端部正常延伸。密封条可以安装在燃气轮机过渡出口框架（48）的锥形槽（49）中。

6. 发明申请

US20120292860A1 TURBINE COMBUSTION SYSTEM TRANSITION SEALS 有权
标题翻译：涡轮燃烧系统过渡密封
公开(公告)号：US20120292860A1
公开(公告)日：2012-11-22
申请号：US13279396
申请日：2011-10-24
申请人： FRANK MOEHRLE , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
发明人： FRANK MOEHRLE , Andrew R. Narcus , John Carella , Jean-Max Millon Sainte-Claire
IPC分类号： F02C7/28
CPC分类号： F01D11/005 , F01D9/023 , F05D2230/21 , F05D2230/232 , F05D2240/55 , F05D2260/37 , F05D2260/38
摘要： Respective seals (54, 78) for the upper and lower spans (48A, 48B) of an exit frame (48) of a turbine combustion system transition piece (28). Each seal has a first strip (55, 79) and a second strip (66, 88) of a sealing material. The two strips of each seal are attached together along a common edge. The second strip is flexible, generally parallel to the first strip, and has a bead (72, 90) along its free edge. This forms a spring clamp that clamps a rail (68, 86) of the exit frame between the bead and the first strip of each seal. A tab extends axially aft from the first strip of each seal for insertion into a circumferential slot (58, 82) in a turbine inlet support structure (52, 76), thus sealing the transition piece (46) to the turbine inlet for efficient turbine operation.
摘要翻译：用于涡轮燃烧系统过渡件（28）的出口框架（48）的上跨和下跨（48A，48B）的相应密封件（54,78）。每个密封件具有密封材料的第一条带（55,79）和第二条带（66,88）。每个密封件的两个条带沿着共同的边缘连接在一起。第二条带是柔性的，大致平行于第一条带，并且沿着其自由边缘具有凸缘（72,90）。这形成弹簧夹，其夹紧出口框架的轨道（68,86）在胎圈和每个密封件的第一条带之间。翼片从每个密封件的第一条带轴向延伸，用于插入到涡轮机入口支撑结构（52,76）中的周向狭槽（58,82）中，从而将过渡件（46）密封到涡轮机入口以用于有效的涡轮机操作。

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