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公开(公告)号：US06345955B1
公开(公告)日：2002-02-12
申请号：US09466296
申请日：1999-12-17
IPC分类号： F01D514
CPC分类号： F01D5/288 , F01D5/145 , F01D5/186 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes outer and inner bands between which extend a plurality of vanes for channeling combustion gases. Each of the vanes includes leading and trailing edges, and pressure and suction sides extending therebetween, and also a bow along the trailing edge to increase pressure in the gases adjacent the inner band. The vanes also include a thermal barrier coating (TBC) selectively disposed solely along the suction side between the leading and trailing edges.
摘要翻译： 涡轮喷嘴包括外部和内部带，在其之间延伸多个叶片以引导燃烧气体。 每个叶片包括前缘和后缘，以及在它们之间延伸的压力和吸力侧，以及沿着后缘的弓形，以增加邻近内带的气体中的压力。 叶片还包括仅沿着前缘和后缘之间的吸力侧选择性地设置的隔热涂层（TBC）。
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公开(公告)号：US6077036A
公开(公告)日：2000-06-20
申请号：US136834
申请日：1998-08-20
CPC分类号： F01D5/145 , F01D5/186 , F01D5/288 , Y02T50/67 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes outer and inner bands between which extend a plurality of vanes for channeling combustion gases. Each of the vanes includes leading and trailing edges, and pressure and suction sides extending therebetween, and also a bow along the trailing edge to increase pressure in the gases adjacent the inner band. The vanes also include a thermal barrier coating (TBC) selectively disposed solely along the suction side between the leading and trailing edges.
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3.发明授权公开(公告)号：US06527165B1
公开(公告)日：2003-03-04
申请号：US09535915
申请日：2000-03-24
申请人： David E. Budinger , Todd S. Heffron , John P. Heyward , Roger D. Wustman , Gregory A. White , Thomas F. Broderick , Joshua L. Miller
发明人： David E. Budinger , Todd S. Heffron , John P. Heyward , Roger D. Wustman , Gregory A. White , Thomas F. Broderick , Joshua L. Miller
IPC分类号： B23K3112
CPC分类号： B23K1/0018 , B23K2101/001 , F05B2220/30 , F05B2230/237 , F05B2230/30
摘要： A method is provided for making, from a plurality of members brazed together, an article including an environmental resistant surface coating and a wear resistant surface portion. Prior to brazing, the members are assembled with at least one preform including the wear resistant material in a matrix including a first brazing alloy having a brazing temperature in a brazing temperature range. The assembly of members includes a second brazing alloy having a brazing temperature in the brazing temperature range. The assembly of members and wear resistant preform is heated in the brazing temperature range to provide a brazed article preform. Then the article preform is machined to a selected geometry and can be coated with the environmental coating.
摘要翻译： 提供一种从钎焊在一起的多个构件制造包括耐环境表面涂层和耐磨表面部分的制品的方法。 在钎焊之前，将构件与至少一个包含耐磨材料的预制件组装在包括钎焊温度范围内的钎焊温度的第一钎焊合金的基体中。 构件的组件包括在钎焊温度范围内具有钎焊温度的第二钎焊合金。 在钎焊温度范围内加热构件和耐磨预制件的组件以提供钎焊制品预制件。 然后将制品预制件加工成所选择的几何形状并且可以用环境涂层涂覆。
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4.发明授权Method and apparatus for fabricating a nozzle segment for use with turbine engines 有权用于制造用于涡轮发动机的喷嘴段的方法和装置公开(公告)号：US07806650B2
公开(公告)日：2010-10-05
申请号：US11511963
申请日：2006-08-29
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , F05D2240/81 , F05D2250/314
摘要： A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.
摘要翻译： 提供了一种用于定向用于涡轮发动机的喷嘴单体的冷却孔的方法。 该方法包括提供具有内带，外带和在其间延伸的至少一个翼型的喷嘴单线。 该方法还包括将至少一排第一排冷却孔相对于至少一排第二排冷却孔定向成一定角度。 所述至少一个第一排和至少一个第二排的取向提供了容纳翼面角度变化而不重新定向冷却孔图案的冷却孔图案。
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5.发明申请Method and apparatus for fabricating a nozzle segment for use with turbine engines 有权用于制造用于涡轮发动机的喷嘴段的方法和装置公开(公告)号：US20080056907A1
公开(公告)日：2008-03-06
申请号：US11511963
申请日：2006-08-29
IPC分类号： F01D5/18
CPC分类号： F01D9/041 , F05D2240/81 , F05D2250/314
摘要： A method for orienting cooling holes of a nozzle singlet for a turbine engine is provided. The method includes providing a nozzle singlet having an inner band, an outer band, and at least one airfoil extending therebetween. The method also includes orienting at least one first row of cooling holes an angle with respect to at least one second row of cooling holes. The orientation of the at least one first row and the at least one second row provides a cooling hole pattern that accommodates a change in the airfoil angle without reorienting the cooling hole pattern.
摘要翻译： 提供了一种用于定向用于涡轮发动机的喷嘴单体的冷却孔的方法。 该方法包括提供具有内带，外带和在其间延伸的至少一个翼型的喷嘴单线。 该方法还包括将至少一排第一排冷却孔相对于至少一排第二排冷却孔定向成一定角度。 所述至少一个第一排和至少一个第二排的取向提供了容纳翼面角度变化而不重新定向冷却孔图案的冷却孔图案。
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公开(公告)号：US06464457B1
公开(公告)日：2002-10-15
申请号：US09886820
申请日：2001-06-21
IPC分类号： F01D1100
CPC分类号： F16J15/0887 , F01D11/005 , F05B2260/301 , F05D2240/55 , F05D2240/57
摘要： A gas turbine engine arcuate segment has an arcuate band segment, at least one tab and an arcuate rail segment spaced axially apart from the tab and located along an axial end of the band segment. The tab and the arcuate rail segment extend radially away from the band segment and a space is located between the tab and the rail segment. A tab aperture extends entirely through the tab. The rail segment has a rail aperture entirely therethrough. A leaf seal and a spring are disposed within the space to bias the leaf seal against the aft rail. In an exemplary embodiment, a spring aperture extends entirely through the spring, a seal aperture extends entirely through the leaf seal, and a headless pin is disposed in the apertures such that the leaf seal and the spring are radially restrained by the pin.
摘要翻译： 燃气涡轮发动机弓形段具有弧形带段，至少一个翼片和弓形轨道段，其与翼片轴向隔开并且沿着带段的轴向端部定位。 突片和弧形轨道段从带段径向延伸，并且空间位于突片和轨道段之间。 突片孔完全延伸穿过舌片。 轨道段具有完全穿过其中的轨道孔。 叶片密封件和弹簧设置在该空间内以将叶片密封件抵靠在后导轨上。 在示例性实施例中，弹簧孔完全延伸穿过弹簧，密封孔完全延伸穿过叶片密封件，并且无孔销设置在孔中，使得叶片密封件和弹簧由销径向地限制。
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7.发明授权Adhesion of a ceramic layer deposited on an article by casting features in the article surface 有权通过在制品表面铸造特征，沉积在制品上的陶瓷层的粘合性
公开(公告)号：US6074706A
公开(公告)日：2000-06-13
申请号：US210829
申请日：1998-12-15
CPC分类号： C23C28/00 , F01D5/288 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339 , Y10T29/49341 , Y10T29/49984
摘要： A method of forming a thermal barrier coating system on an article subjected to a hostile thermal environment, such as the hot gas path components of a gas turbine engine. The coating system is generally composed of a ceramic layer and preferably a bond coat that adheres the ceramic layer to the component surface. Surface features such as grooves are cast directly into the surface of the component. If the bond coat is present, the grooves in the component surface cause the bond coat to also have grooves that generally correspond to the grooves in the component surface.
摘要翻译： 在经受恶劣热环境的制品（例如燃气涡轮发动机的热气路径部件）上形成热障涂层系统的方法。 涂层系统通常由陶瓷层组成，优选粘结涂层将陶瓷层粘附到组件表面。 诸如凹槽的表面特征直接浇注到部件的表面中。 如果粘合涂层存在，则部件表面中的凹槽使得粘合涂层还具有通常对应于部件表面中的凹槽的凹槽。
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公开(公告)号：US5813832A
公开(公告)日：1998-09-29
申请号：US759544
申请日：1996-12-05
CPC分类号： F01D5/005 , F01D9/041 , F05D2300/606
摘要： A turbine engine vane segment, including spaced apart band or platform members and at least one airfoil member carried at metallic bonds between the platform members, is improved by providing at least one, but not necessarily all, of the segment members as an improved member having a directionally oriented Ni base superalloy microstructure with a stress rupture strength greater than the stress rupture strength of the balance of the segment members, which have a conventional generally equiaxed microstructure. For example, the balance of the members are conventionally cast from a Co base alloy. The coefficient of thermal expansion of the improved member is different from that of the balance of the members. A metallic bond including a brazed structure is provided between the improved member and the balance of the members, possessing strength sufficient to carry the stresses caused by differences in coefficients of thermal expansion of the dissimilar materials.
摘要翻译： 包括间隔开的带或平台构件的涡轮发动机叶片节段以及在平台构件之间以金属接合的方式承载的至少一个翼型构件通过提供至少一个但不一定全部的分段构件来改进， 一种定向取向的Ni基超合金显微组织，其应力断裂强度大于具有常规大致等轴显微组织的段构件平衡的应力断裂强度。 例如，构件的平衡通常由Co基合金铸造。 改进的构件的热膨胀系数与构件的平衡的不同。 在改进的构件和构件的平衡之间设置包括钎焊结构的金属结合体，其具有足以承受由不同材料的热膨胀系数差异引起的应力的强度。
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