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1.发明申请Transition support system for combustion transition ducts for turbine engines 有权用于涡轮发动机燃烧过渡管道的过渡支撑系统公开(公告)号：US20080202124A1
公开(公告)日：2008-08-28
申请号：US11711823
申请日：2007-02-27
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F01D11/005 , F01D25/12 , F02C7/28
摘要： A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.
摘要翻译： 用于过渡管道的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 过渡管道支撑系统包括过渡支撑框架，该过渡支撑框架由位于出口过渡部分处的过渡管道主体周围的主体形成。 过渡支撑框架可以包括与出口过渡部分的一部分对准并定位成靠近过渡管体本体的外壁的倾斜角度的第一内表面，以限制过渡管体的线性移动 第一个方向 过渡支撑框架还可以包括以倾斜角度定位的第二内表面，以限制过渡管体在与第一方向相反的第二方向上的线性运动。
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2.发明授权Transition support system for combustion transition ducts for turbine engines 有权用于涡轮发动机燃烧过渡管道的过渡支撑系统公开(公告)号：US08001787B2
公开(公告)日：2011-08-23
申请号：US11711823
申请日：2007-02-27
CPC分类号： F01D9/023 , F01D11/005 , F01D25/12 , F02C7/28
摘要： A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.
摘要翻译： 用于过渡管道的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 过渡管道支撑系统包括过渡支撑框架，该过渡支撑框架由位于出口过渡部分处的过渡管道主体周围的主体形成。 过渡支撑框架可以包括与出口过渡部分的一部分对准并定位成靠近过渡管体本体的外壁的倾斜角度的第一内表面，以限制过渡管体的线性移动 第一个方向 过渡支撑框架还可以包括以倾斜角度定位的第二内表面，以限制过渡管体在与第一方向相反的第二方向上的线性运动。
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3.发明授权Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine 有权用于燃气涡轮发动机的过渡/涡轮联结的过渡到涡轮机密封装置和套件公开(公告)号：US07527469B2
公开(公告)日：2009-05-05
申请号：US11298320
申请日：2005-12-08
IPC分类号： F01D25/00
CPC分类号： F01D11/005 , F01D9/041 , F05D2240/55 , F16J15/062 , F16J15/0887
摘要： One embodiment of a transition-to-turbine seal (300) comprises a transition exit seal (302) adapted for fixed attachment to an exit rail (350) of a transition (109), and a stage-1 seal (340). The stage-1 seal (340) comprises an axial seal slot (348) comprising parallel walls (346, 347) adapted to slidingly engage a first male member (310) of the transition exit seal (302). The stage-1 seal (340) also comprises a radial seal slot (354) comprising parallel walls (351, 353) adapted to slidingly engage a plate (338) of a row 1 vane segment (330). The transition-to-turbine seal (300) thus provides both axial and radial freedom of movement. Materials and coatings for the transition exit seal (302) and the stage-1 seal (340) are selected to promote preferential wear of these components relative to wear of the surface of the row 1 vane segment (330). Wear of the exit rail (350) is reduced or eliminated due to the noted fixed attachment.
摘要翻译： 过渡到涡轮机密封件（300）的一个实施例包括适于固定连接到过渡件（109）的出口轨道（350）的过渡出口密封件（302）和阶段1密封件（340）。 阶段1密封件（340）包括轴向密封槽（348），其包括适于滑动地接合过渡出口密封件（302）的第一阳构件（310）的平行壁（346,347）。 阶段1密封件（340）还包括径向密封槽（354），其包括适于滑动地接合排1叶片段（330）的板（338）的平行壁（351,353）。 过渡到涡轮机密封件（300）因此提供轴向和径向的移动自由度。 选择用于转换出口密封件（302）和阶段-1密封件（340）的材料和涂层以促进这些部件相对于第一排叶片段（330）表面的磨损的优先磨损。 由于注意到的固定附件，出口导轨（350）的磨损被减少或消除。
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公开(公告)号：US08142142B2
公开(公告)日：2012-03-27
申请号：US12205278
申请日：2008-09-05
IPC分类号： F01D11/00
CPC分类号： F01D9/023
摘要： A gas turbine transition duct apparatus is provided comprising first and second turbine transition ducts and a strip seal. The strip seal may comprise a sealing element and a spring structure.
摘要翻译： 提供了一种燃气轮机过渡管道装置，其包括第一和第二涡轮机过渡管道和带状密封件。 带状密封件可以包括密封元件和弹簧结构。
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5.发明申请TRANSITION SUPPORT SYSTEM FOR COMBUSTION TRANSITION DUCTS FOR TURBINE ENGINES 审中-公开用于涡轮发动机燃烧过渡管的过渡支撑系统公开(公告)号：US20110192171A1
公开(公告)日：2011-08-11
申请号：US13087534
申请日：2011-04-15
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F01D11/005 , F01D25/12 , F02C7/28
摘要： A transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The transition duct support system includes a transition support frame formed from a body positioned around a transition duct body at an outlet transition section. The transition support frame may include a first inner surface aligned with and positioned proximate to portion of the outlet transition section that is positioned at an oblique angle relative to the outer wall of the transition duct body to limit linear movement of the transition duct body in a first direction. The transition support frame may also include a second inner surface positioned at an oblique angle to limit linear movement of the transition duct body in a second direction opposite the first direction.
摘要翻译： 用于过渡管道的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 过渡管道支撑系统包括过渡支撑框架，该过渡支撑框架由位于出口过渡部分处的过渡管道主体周围的主体形成。 过渡支撑框架可以包括与出口过渡部分的一部分对准并定位成靠近过渡管体本体的外壁的倾斜角度的第一内表面，以限制过渡管体的线性移动 第一个方向 过渡支撑框架还可以包括以倾斜角度定位的第二内表面，以限制过渡管体在与第一方向相反的第二方向上的线性运动。
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公开(公告)号：US07870738B2
公开(公告)日：2011-01-18
申请号：US11540030
申请日：2006-09-29
申请人： James M. Zborovsky , Andreas Heilos
发明人： James M. Zborovsky , Andreas Heilos
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/55 , Y02T50/675
摘要： The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.
摘要翻译： 本发明涉及用于密封涡轮发动机中相邻罐式环形燃烧器的过渡部分之间的间隙的密封件，使得该密封件可用于密封0.5巴或更大的压降。 密封件包括被配置为在相邻过渡部分之间延伸的板，并且板可以具有从板的前表面延伸到板的后表面的至少一个穿孔。 密封件还包括由能够承受涡轮机燃烧气体温度的材料形成的多孔基体，其中一部分多孔基体可以固定地附接到板的表面。
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7.发明申请公开(公告)号：US20100251687A1
公开(公告)日：2010-10-07
申请号：US11540030
申请日：2006-09-29
申请人： James M. Zborovsky , Andreas Heilos
发明人： James M. Zborovsky , Andreas Heilos
CPC分类号： F01D9/023 , F01D11/005 , F02C7/28 , F05D2240/55 , Y02T50/675
摘要： The present invention is directed to a seal for sealing a gap between transition sections of adjacent can annular combustors in a turbine engine such that the seal is usable in applications for sealing pressure drops of 0.5 bar or greater. The seal includes a plate configured to extend between adjacent transition sections and the plate may have at least one perforation extending from the front surface of the plate to the rear surface of plate. The seal further includes a porous matrix formed from materials capable of withstanding turbine combustion gas temperatures, wherein a portion of the porous matrix may be fixedly attached to a surface of the plate.
摘要翻译： 本发明涉及用于密封涡轮发动机中相邻罐式环形燃烧器的过渡部分之间的间隙的密封件，使得该密封件可用于密封0.5巴或更大的压降。 密封件包括被配置为在相邻过渡部分之间延伸的板，并且板可以具有从板的前表面延伸到板的后表面的至少一个穿孔。 密封件还包括由能够承受涡轮机燃烧气体温度的材料形成的多孔基体，其中一部分多孔基体可以固定地附接到板的表面。
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