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1.发明申请公开(公告)号：US20140169957A1
公开(公告)日：2014-06-19
申请号：US13719566
申请日：2012-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Natalie Wali , Don Mittendorf , Lorenzo Crosatti
CPC classification number: F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes 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.
Abstract translation: 提供涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，涡轮喷嘴包括支撑环和滑动接头环，其与支撑环基本上同心并且与其径向间隔开。 滑接环在其中具有多个狭槽。 多个叶片固定地联接到支撑环并且从其径向延伸到多个狭槽中。 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移动。
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2.发明申请TURBINE NOZZLES WITH SLIP JOINTS IMPREGNATED BY OXIDATION-RESISTANT SEALING MATERIAL AND METHODS FOR THE PRODUCTION THEREOF 有权具有耐氧化密封材料浸渍的滑动接头的涡轮喷嘴及其生产方法公开(公告)号：US20150267550A1
公开(公告)日：2015-09-24
申请号：US14219622
申请日：2014-03-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Bradley Reed Tucker , Natalie Wali , Daniel Hicks , Bill Macelroy
CPC classification number: F01D11/005 , B23K1/0018 , B23K2101/001 , B23P15/04 , F01D5/28 , F01D9/041 , F01D9/042 , F01D11/00 , F01D17/162 , F05D2300/182 , Y02T50/673 , Y10T29/49321
Abstract: Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.
Abstract translation: 提供了具有由耐氧化密封材料浸渍的滑动接头的涡轮喷嘴的实施例，如制造涡轮喷嘴的方法的实施例。 在一个实施例中，该方法包括提供支撑环，与支撑环基本上同心且与其径向间隔开的滑动关节环以及固定地联接到支撑环的多个叶片。 多个叶片从支撑环径向地延伸到设置在滑动接合环中的多个周向间隔开的槽中，以与其形成多个滑动接头。 多个滑动接头用硅改性的铝化物密封材料浸渍。 硅改性的铝化物密封材料在涡轮喷嘴操作期间阻止气体流入径向滑动接头，同时还可以断裂以允许沿着多个滑动接头在多个叶片和滑动接头环之间的相对径向运动。
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Patent Agency Ranking
3.发明申请PROTECTIVE COATING SYSTEMS FOR GAS TURBINE ENGINE APPLICATIONS AND METHODS FOR FABRICATING THE SAME 审中-公开气体涡轮发动机用保护涂层系统及其制造方法公开(公告)号：US20150247245A1
公开(公告)日：2015-09-03
申请号：US14042323
申请日：2013-09-30
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Natalie Wali
Abstract: Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary method of manufacturing a turbine engine component includes providing a substrate in the form of the turbine engine component and forming a bond coating on and over the substrate. The method further includes forming a thermal barrier coating or an environmental barrier coating on and over the bond coating and forming a magnetoplumbite structure ceramic top coating on an over the thermal barrier coating or the environmental barrier coating.
Abstract translation: 提供了用于燃气涡轮发动机应用的保护涂层系统以及用于制造这种保护涂层系统的方法。 制造涡轮发动机部件的示例性方法包括以涡轮发动机部件的形式提供基板，并在基板上和上方形成接合涂层。 该方法还包括在粘结涂层之上和之上形成热障涂层或环境阻挡涂层，并在热障涂层或环境屏障涂层上形成磁铅笔结构陶瓷顶涂层。
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公开(公告)号：US09702252B2
公开(公告)日：2017-07-11
申请号：US13719566
申请日：2012-12-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Natalie Wali , Don Mittendorf , Lorenzo Crosatti
CPC classification number: F01D1/04 , B23P11/00 , F01D9/041 , F01D9/042 , F05D2230/60 , F05D2260/941 , Y02T50/671 , Y10T29/49245
Abstract: Embodiments of a turbine nozzle are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the turbine nozzle includes a support ring and a slip joint ring, which is substantially concentric with the support ring and radially spaced apart therefrom. The slip joint ring has a plurality of slots therein. A plurality of vanes 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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5.发明申请STATIONARY AIRFOILS CONFIGURED TO FORM IMPROVED SLIP JOINTS IN BI-CAST TURBINE ENGINE COMPONENTS AND THE TURBINE ENGINE COMPONENTS INCLUDING THE SAME 有权配置用于形成改进的双缸涡轮发动机部件中的滑动接头和包括其的涡轮发动机部件的固定式空气公开(公告)号：US20150159495A1
公开(公告)日：2015-06-11
申请号：US14099218
申请日：2013-12-06
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Harry Lester Kington , Shezan Kanjiyani , Natalie Wali , John Gintert , Bradley R. Tucker
IPC: F01D9/04
CPC classification number: F01D9/042 , B22C9/04 , B22C9/22 , F01D9/041 , F01D25/26 , F05D2230/21 , F05D2300/50212
Abstract: Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.
Abstract translation: 提供了构造成在双流型涡轮发动机部件中形成改进的滑动关节的固定翼型件以及包括其的涡轮发动机部件。 用于双流型涡轮发动机部件的固定翼片包括通过压力侧壁和吸力侧壁互连的前缘和后缘。 端部形成有一对相对的凸缘，以在双流型涡轮发动机部件中形成具有护罩环的滑动接头并且限定互锁特征。 滑动接头允许固定翼型件相对于护罩环由于热差膨胀和收缩而径向移动。
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公开(公告)号：US09970307B2
公开(公告)日：2018-05-15
申请号：US14219622
申请日：2014-03-19
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Shezan Kanjiyani , Bradley Reed Tucker , Natalie Wali , Daniel Hicks , Bill Macelroy
CPC classification number: F01D11/005 , B23K1/0018 , B23K2101/001 , B23P15/04 , F01D5/28 , F01D9/041 , F01D9/042 , F01D11/00 , F01D17/162 , F05D2300/182 , Y02T50/673 , Y10T29/49321
Abstract: Embodiments of a turbine nozzle having slip joints impregnated by an oxidation-resistant sealing material are provided, as are embodiments of methods for the manufacture of turbine nozzles. In one embodiment, the method includes providing a support ring, a slip joint ring substantially concentric with the support ring and radially spaced apart therefrom, and a plurality of vanes fixedly coupled to the support ring. The plurality of vanes extends radially from the support ring into a plurality of circumferentially-spaced slots provided in the slip joint ring to form a plurality of slip joints therewith. The plurality of slip joints are impregnated with a silicon-modified aluminide sealing material. The silicon-modified aluminide sealing material impedes gas flow into the radial slip joints during operation of the turbine nozzle, while also fracturing to permit relative radial movement between the plurality of vanes and the slip joint ring along the plurality of slip joints.
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公开(公告)号：US09611748B2
公开(公告)日：2017-04-04
申请号：US14099218
申请日：2013-12-06
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Harry Lester Kington , Shezan Kanjiyani , Natalie Wali , John Gintert , Bradley R. Tucker
CPC classification number: F01D9/042 , B22C9/04 , B22C9/22 , F01D9/041 , F01D25/26 , F05D2230/21 , F05D2300/50212
Abstract: Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.
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