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1. 发明申请

US20150300192A1 GAS TURBINE ENGINE COMPONENTS HAVING SEALED STRESS RELIEF SLOTS AND METHODS FOR THE FABRICATION THEREOF 有权
标题翻译：具有密封应力消除槽的气体涡轮发动机部件及其制造方法
公开(公告)号：US20150300192A1
公开(公告)日：2015-10-22
申请号：US14257485
申请日：2014-04-21
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Jason Smoke , Bradley Reed Tucker , Ardeshir Riahi , Ed Zurmehly , Alexander MirzaMoghadam
IPC分类号： F01D11/00 , F01D9/04 , B22D19/00 , B22D25/02 , B22D25/06 , F01D1/06 , F01D25/12
CPC分类号： F01D11/005 , B22D19/00 , B22D25/02 , B22D25/06 , F01D1/06 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/30 , F05D2240/55 , F05D2260/20 , F05D2260/941
摘要： Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.
摘要翻译：提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽壁。应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。

2. 发明申请

US20160305004A1 COATED SUBSTRATES AND METHODS OF PRODUCING THE SAME 审中-公开
标题翻译：涂覆基板及其制造方法
公开(公告)号：US20160305004A1
公开(公告)日：2016-10-20
申请号：US14690835
申请日：2015-04-20
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Don Olson , Reza Oboodi , Natalie Kruk , Bradley Reed Tucker
IPC分类号： C23C4/134 , C23C4/10 , F01D25/00
CPC分类号： C23C4/134 , B23K35/001 , C04B41/009 , C04B41/52 , C04B41/89 , C23C4/02 , C23C4/10 , C23C4/18 , C23C28/042 , F01D5/284 , F01D5/288 , F01D25/005 , F05D2230/237 , F05D2230/312 , F05D2300/177 , F05D2300/21 , C04B35/565 , C04B35/806 , C04B35/584 , C04B35/597 , C04B41/0072 , C04B41/4501 , C04B41/5071 , C04B41/5096 , C04B41/4527 , C04B41/5027
摘要： Coated substrates and methods of producing the same are provided. In an exemplary embodiment, a method of coating a substrate includes brazing a first bond coat layer to the substrate, where the substrate includes a ceramic material. A second bond coat layer is plasma sprayed overlying the first bond coat layer to form a composite bond coat with the first bond coat layer positioned between the second bond coat layer and the substrate. An environmental barrier coating layer is applied overlying the second bond coat layer such that the first and second bond coat layers are positioned between the substrate and the environmental barrier coating layer.
摘要翻译：提供涂布的基材及其制备方法。在示例性实施例中，涂覆基板的方法包括将第一粘结涂层钎焊到基底上，其中基底包括陶瓷材料。将第二粘合涂层等离子体喷涂在第一粘合涂层上以形成复合粘合涂层，其中第一粘合涂层位于第二粘结涂层和基底之间。施加环境屏障涂层覆盖在第二粘合涂层上，使得第一和第二粘合涂层位于基底和环境阻挡涂层之间。

3. 发明申请

US20150275763A1 TURBINE SECTIONS OF GAS TURBINE ENGINES WITH DUAL USE OF COOLING AIR 有权
标题翻译：具有双重冷却空气使用的涡轮发动机涡轮段
公开(公告)号：US20150275763A1
公开(公告)日：2015-10-01
申请号：US14227924
申请日：2014-03-27
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
IPC分类号： F02C7/18 , F02C3/10
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; 涡轮转子组件，其包括延伸到主流气流路径中的转子叶片; 壳体，其包括环绕所述转子叶片并且至少部分地限定所述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。第一腔体流体地联接到第二腔体，而第二腔室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，并从第二腔体流到第三空腔。

4. 发明申请

US20140321965A1 TURBINE NOZZLES AND METHODS OF MANUFACTURING THE SAME 有权
标题翻译：涡轮喷嘴及其制造方法
公开(公告)号：US20140321965A1
公开(公告)日：2014-10-30
申请号：US13869085
申请日：2013-04-24
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Rajiv Rana , Ardeshir Riahi , Bradley Reed Tucker , David Chou
IPC分类号： F01D9/02
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.
摘要翻译：涡轮喷嘴组件包括内周支撑平台，外周支撑平台以及设置在内圆周支撑平台和外圆周支撑平台之间的多个翼型叶片。涡轮喷嘴组件还包括沿着外周支撑平台的径向外表面或内周支撑平台的径向内表面设置的多个冲击板，以及多个间隙保持特征，其设置在多个外周或内圆周支撑平台和多个冲击板。多个间隙保持特征的每个间隙保持特征都设置在使多个外周或内周支撑平台与多个冲击板之间保持冷却空气流动空间的高度。

5. 发明申请

US20190022781A1 METHODS FOR MANUFACTURING A TURBINE NOZZLE WITH SINGLE CRYSTAL ALLOY NOZZLE SEGMENTS 审中-公开
公开(公告)号：US20190022781A1
公开(公告)日：2019-01-24
申请号：US15811862
申请日：2017-11-14
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Bradley Reed Tucker , Ardeshir Riahi , Jason Smoke , Ed Zurmehly
IPC分类号： B23K1/00 , F01D9/04 , B23P15/00 , B22D19/04 , B22D19/00
摘要： Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.

6. 发明授权

US09719362B2 Turbine nozzles and methods of manufacturing the same 有权
公开(公告)号：US09719362B2
公开(公告)日：2017-08-01
申请号：US13869085
申请日：2013-04-24
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Rajiv Rana , Ardeshir Riahi , Bradley Reed Tucker , David Chou
IPC分类号： F01D5/14 , F01D9/06 , F01D5/18
CPC分类号： F01D9/065 , F01D5/187 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A turbine nozzle assembly includes an inner circumferential support platform, an outer circumferential support platform, and a plurality of airfoil vanes disposed between the inner circumferential support platform and the outer circumferential support platform. The turbine nozzle assembly further includes a plurality of impingement plates disposed along a radially outer surface of the outer circumferential support platform or a radially inner surface of the inner circumferential support platform, and a plurality of gap-maintaining features disposed between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates. Each gap-maintaining feature of the plurality of gap-maintaining features is provided at a height such that a cooling air flow space is maintained between the plurality of outer or inner circumferential support platforms and the plurality of impingement plates.

7. 发明授权

US09657642B2 Turbine sections of gas turbine engines with dual use of cooling air 有权
公开(公告)号：US09657642B2
公开(公告)日：2017-05-23
申请号：US14227924
申请日：2014-03-27
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Shezan Kanjiyani , John Gintert , Rajiv Rana , Lorenzo Crosatti , Bradley Reed Tucker , Ed Zurmehly
IPC分类号： F02C7/18 , F01D25/12 , F01D25/14 , F01D5/18 , F01D11/08 , F02C3/10
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.

8. 发明授权

US09506365B2 Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof 有权
标题翻译：具有密封应力消除槽的燃气涡轮发动机部件及其制造方法
公开(公告)号：US09506365B2
公开(公告)日：2016-11-29
申请号：US14257485
申请日：2014-04-21
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Jason Smoke , Bradley Reed Tucker , Ardeshir Riahi , Ed Zurmehly , Alexander MirzaMoghadam
IPC分类号： F01D11/00 , B23D19/00 , F01D1/06 , F01D9/04 , F01D25/12 , B22D25/02 , B22D25/06 , B22D19/00
CPC分类号： F01D11/005 , B22D19/00 , B22D25/02 , B22D25/06 , F01D1/06 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/30 , F05D2240/55 , F05D2260/20 , F05D2260/941
摘要： Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.
摘要翻译：提供了具有密封的应力消除槽的燃气涡轮发动机部件的实施例，其中包括含有这种部件的燃气涡轮发动机和用于制造这种部件的方法的实施例的实施例。在一个实施例中，燃气涡轮发动机包括核心气体流动路径，二次冷却流动路径，以及涡轮喷嘴或其它燃气涡轮发动机部件。该组件又包括核心气体流路延伸穿过的组件主体，从组件主体突出并进入二次冷却流动路径的径向延伸的壁，以及一个或多个形成在径向延伸的应力释放槽壁。应力释放槽填充有高温密封材料，其阻止第二冷却和核心气体流动路径之间的泄漏，并且其在燃气涡轮发动机的操作期间破裂以减轻径向延伸的壁内的热机械应力。

9. 发明申请

US20160024948A1 METHODS FOR MANUFACTURING A TURBINE NOZZLE WITH SINGLE CRYSTAL ALLOY NOZZLE SEGMENTS 有权
标题翻译：用单晶合金喷嘴部分制造涡轮喷嘴的方法
公开(公告)号：US20160024948A1
公开(公告)日：2016-01-28
申请号：US14341162
申请日：2014-07-25
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Bradley Reed Tucker , Ardeshir Riahi , Jason Smoke , Ed Zurmehly
IPC分类号： F01D9/02 , B22D19/04 , B23K1/00 , B22D19/00
CPC分类号： B23K1/0018 , B22D19/0081 , B22D19/04 , B23P15/006 , F01D9/044 , F05D2230/21 , F05D2230/237 , F05D2230/90 , F05D2300/607 , Y10T29/49346
摘要： Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.
摘要翻译：提供了制造涡轮喷嘴的方法。形成多个喷嘴段。每个喷嘴段包括具有至少一个叶片的端壁环部分。多个喷嘴段连接到环形端壁，其形成与环形端壁同心的分段环形端壁，每个喷嘴段的至少一个叶片在分段的环形端壁和环形端壁之间延伸。

10. 发明申请

US20150337680A1 TURBINE NOZZLES AND COOLING SYSTEMS FOR COOLING SLIP JOINTS THEREIN 有权
标题翻译：用于冷却SLIP接头的涡轮喷嘴和冷却系统
公开(公告)号：US20150337680A1
公开(公告)日：2015-11-26
申请号：US14283104
申请日：2014-05-20
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Lorenzo Crosatti , Ardeshir Riahi , Bradley Reed Tucker , Shezan Kanjiyani
IPC分类号： F01D25/12 , F01D9/02
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 and cooling systems for cooling slip joints therein are provided. The turbine nozzle has an endwall, a vane coupled to the endwall, a slip joint, and a plurality of airfoil quenching holes that cooperate with a plurality of endwall cooling holes. The vane comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall and an end portion. The slip joint is between the end portion and the endwall. The airfoil quenching holes are defined through the pressure sidewall in the end portion. The endwall cooling holes are defined through the endwall along the pressure sidewall and in proximity to the leading edge. The airfoil quenching holes and endwall cooling holes are disposed adjacent the slip joint.
摘要翻译：提供了用于冷却滑动接头的涡轮喷嘴和冷却系统。涡轮喷嘴具有端壁，联接到端壁的叶片，滑动接头以及与多个端壁冷却孔配合的多个翼型骤冷孔。叶片包括通过压力侧壁和吸力侧壁和端部部分互连的前缘和后缘。滑动接头位于端部和端壁之间。翼型淬火孔通过端部中的压力侧壁限定。端壁冷却孔沿着压力侧壁并且靠近前缘限定通过端壁。翼片淬火孔和端壁冷却孔设置在滑动接头附近。

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