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公开(公告)号：EP2947280B1
公开(公告)日：2018-10-17
申请号：EP15158094.1
申请日：2015-03-06
CPC分类号： F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： Turbine nozzles (110) and cooling systems for cooling slip joints (206) therein are provided. The turbine nozzle has an endwall (103), a vane (102) coupled to the endwall, a slip joint (206), and a plurality of airfoil quenching holes (160) that cooperate with a plurality of endwall cooling holes (150). The vane comprises a leading edge (126) and a trailing edge (128) interconnected by a pressure sidewall (122) and a suction sidewall (128) and an end portion (140). The slip joint (206) is between the end portion(140) and the endwall (103). The airfoil quenching holes (160) are defined through the pressure sidewall (122) in the end portion. The endwall cooling holes (150) are defined through the endwall along the pressure sidewall (122) and in proximity to the leading edge (126). The airfoil quenching holes (160) and endwall cooling holes (150) are disposed adjacent the slip joint (150).
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3.发明公开
公开(公告)号：EP2787174A2
公开(公告)日：2014-10-08
申请号：EP14161162.4
申请日：2014-03-21
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil (310) for a gas turbine engine is provided. The airfoil includes a body (311) with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall (402) disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber (424) and a leading edge chamber (422). The interior wall defines a cooling hole (450) with a base portion (470) and a locally extended portion (480) to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译： 提供了一种用于燃气涡轮发动机的翼型件（310）。 翼型件包括具有前缘的主体（311），后缘，在前缘和后缘之间延伸的第一侧壁，以及在前缘和后缘之间延伸的第二侧壁。 身体定义一个内腔。 所述翼型件包括设置在所述主体的内部空腔内并在所述第一壁和所述第二壁之间延伸以限定供应室（424）和前缘室（422）的内壁（402）。 内壁限定具有基部（470）和局部延伸部分（480）的冷却孔（450），以将冷却空气从供应室引导到前缘室，使得冷却空气撞击前缘。
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公开(公告)号：EP2787174A3
公开(公告)日：2018-03-07
申请号：EP14161162.4
申请日：2014-03-21
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/186 , F05D2220/32 , F05D2240/121 , F05D2250/231 , F05D2250/232 , F05D2260/201 , Y02T50/671 , Y02T50/676
摘要： An airfoil (310) for a gas turbine engine is provided. The airfoil includes a body (311) with a leading edge, a trailing edge, a first side wall extending between the leading edge and the trailing edge, and a second side wall extending between the leading edge and the trailing edge. The body defines an interior cavity. The airfoil includes an interior wall (402) disposed within the interior cavity of the body and extending between the first wall and the second wall to define a supply chamber (424) and a leading edge chamber (422). The interior wall defines a cooling hole (450) with a base portion (470) and a locally extended portion (480) to direct cooling air from the supply chamber to the leading edge chamber such that the cooling air impinges upon the leading edge.
摘要翻译： 提供了用于燃气涡轮发动机的翼型件（310）。 翼型件包括具有前缘，后缘，在前缘和后缘之间延伸的第一侧壁以及在前缘和后缘之间延伸的第二侧壁的主体（311）。 身体确定了一个内腔。 翼型件包括布置在本体的内部空腔内并且在第一壁和第二壁之间延伸以限定供应室（424）和前缘室（422）的内壁（402）。 内壁限定具有底座部分（470）和局部延伸部分（480）的冷却孔（450），以将冷却空气从供应室引导至前缘室，使得冷却空气冲击前缘。
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5.发明公开Turbine sections of gas turbine engines with dual use of cooling air 审中-公开Turbinenabschnitte von Gasturbinenmotoren mit Doppelter Verwendung derKühlluft
公开(公告)号：EP2924238A1
公开(公告)日：2015-09-30
申请号：EP15151704.2
申请日：2015-01-19
发明人： Kanjiyani, Shezan , Gintert, John , Rana, Rajiv , Crosatti, Lorenzo , Tucker, Bradley Reed , Zurmehly, Ed
CPC分类号： F02C7/18 , F01D5/187 , F01D11/08 , F01D25/12 , F01D25/14 , F02C3/10 , F05D2240/81 , F05D2260/201 , F05D2260/205 , Y02T50/673 , Y02T50/676
摘要： A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud. The first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity.
摘要翻译： 涡轮部分包括具有内径端壁，外径端壁和定子叶片的定子组件; 包括延伸到主流气流路径中的转子叶片的涡轮转子组件; 壳体，其包括环绕转子叶片并且至少部分地限定主流热气体流动路径的环形护罩; 第一挡板，布置成限定具有定子组件的外径端壁的第一腔; 第二挡板 以及第三挡板，其布置成限定具有第二挡板的第二空腔和具有护罩的第三空腔。 第一空腔流体耦合到第二空腔，第二空腔流体耦合到第三空腔，使得冷却空气从第一空腔流到第二空腔，并从第二空腔流到第三空腔。
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公开(公告)号：EP2746539B1
公开(公告)日：2017-03-15
申请号：EP13193392.1
申请日：2013-11-18
CPC分类号： F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
摘要： Embodiments of a turbine nozzle (20) are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring (60) and a slip joint ring (62), which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots (78) therein. A plurality of vanes (64) is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
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7.发明公开TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN 审中-公开TURBINENDÜSENUNDKÜHLSYSTEMEZUMKÜHLENVON GLEITGELENKEN DARIN
公开(公告)号：EP2947280A1
公开(公告)日：2015-11-25
申请号：EP15158094.1
申请日：2015-03-06
CPC分类号： F01D9/02 , F01D9/04 , F01D9/042 , F01D9/065 , F01D25/12 , F01D25/246 , F05D2220/32 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： Turbine nozzles (110) and cooling systems for cooling slip joints (206) therein are provided. The turbine nozzle has an endwall (103), a vane (102) coupled to the endwall, a slip joint (206), and a plurality of airfoil quenching holes (160) that cooperate with a plurality of endwall cooling holes (150). The vane comprises a leading edge (126) and a trailing edge (128) interconnected by a pressure sidewall (122) and a suction sidewall (128) and an end portion (140). The slip joint (206) is between the end portion(140) and the endwall (103). The airfoil quenching holes (160) are defined through the pressure sidewall (122) in the end portion. The endwall cooling holes (150) are defined through the endwall along the pressure sidewall (122) and in proximity to the leading edge (126). The airfoil quenching holes (160) and endwall cooling holes (150) are disposed adjacent the slip joint (150).
摘要翻译： 提供了用于冷却滑动接头（206）的涡轮喷嘴（110）和冷却系统。 涡轮喷嘴具有端壁（103），联接到端壁的叶片（102），滑动接头（206）和与多个端壁冷却孔（150）协作的多个翼型骤冷孔（160）。 叶片包括通过压力侧壁（122）和吸力侧壁（128）和端部（140）互连的前缘（126）和后缘（128）。 滑动接头（206）位于端部（140）和端壁（103）之间。 翅片淬火孔（160）通过端部中的压力侧壁（122）限定。 端壁冷却孔（150）沿着压力侧壁（122）通过端壁限定并且靠近前缘（126）。 翼片淬火孔（160）和端壁冷却孔（150）邻近滑动接头（150）设置。
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公开(公告)号：EP2924238B1
公开(公告)日：2019-05-15
申请号：EP15151704.2
申请日：2015-01-19
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9.发明公开Turbine nozzles with slip joints and method for the production thereof 有权Turbinendüsenmit Gleitverbindungen und Verfahren zu ihrer Herstellung
公开(公告)号：EP2746539A3
公开(公告)日：2015-10-28
申请号：EP13193392.1
申请日：2013-11-18
CPC分类号： F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
摘要： Embodiments of a turbine nozzle (20) are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring (60) and a slip joint ring (62), which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots (78) therein. A plurality of vanes (64) is fixedly coupled to the support ring and extends radially therefrom into the plurality of slots. A plurality of radial slip joints is formed between the plurality of vanes and the plurality slots. Each slip joint extends around a different one of the plurality of vanes to permit relative radial movement between the plurality of vanes and the slip joint ring during operation of the turbine nozzle.
摘要翻译： 如同制造涡轮喷嘴的方法的实施例一样，提供涡轮喷嘴（20）的实施例。 在一个实施例中，涡轮喷嘴包括支撑环（60）和滑动接头环（62），其与支撑环基本上同心并且与其径向间隔开。 滑动接头环在其中具有多个狭槽（78）。 多个叶片（64）固定地联接到支撑环并且从其径向延伸到多个槽中。 在多个叶片和多个槽之间形成多个径向滑动接头。 每个滑动接头围绕多个叶片中的不同的叶片延伸，以允许在涡轮喷嘴的操作期间在多个叶片和滑动接头环之间的相对径向运动。
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10.发明公开Bi-cast turbine nozzles and methods for cooling slip joints therein 审中-公开Zweifach gegosseneTurbinendüsenund Verfahren zurKühlungder Gleitgelenke darin
公开(公告)号：EP2881542A1
公开(公告)日：2015-06-10
申请号：EP14185022.2
申请日：2014-09-16
发明人： Riahi, Ardeshir , Crosatti, Lorenzo
CPC分类号： F01D25/12 , F01D5/14 , F01D5/145 , F01D5/18 , F01D5/186 , F01D5/22 , F01D9/00 , F01D9/041 , F01D9/042 , Y02T50/673 , Y02T50/676
摘要： Bi-cast turbine nozzles and methods for cooling the same are provided. The bi-cast turbine nozzle comprises an endwall. A vane is coupled to the endwall. The vane comprises an end portion and a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. A slip joint is provided between the end portion and the endwall. A plurality of cooling holes is defined through the endwall. The plurality of cooling holes is disposed adjacent the periphery of the slip joint along the pressure sidewall of the vane and in proximity to the leading edge of the vane.
摘要翻译： 提供双流透平喷嘴及其冷却方法。 双浇注涡轮喷嘴包括端壁。 叶片联接到端壁。 叶片包括端部和前缘以及通过压力侧壁和吸力侧壁相互连接的后缘。 在端部和端壁之间设置滑动接头。 通过端壁限定多个冷却孔。 多个冷却孔沿着叶片的压力侧壁并且靠近叶片的前缘设置在滑动接头的周边附近。
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