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1.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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2.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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3.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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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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7.发明授权Airfoil for a turbine nozzle of a gas turbine engine and method of making same 有权用于燃气涡轮发动机的涡轮喷嘴的翼型及其制造方法公开(公告)号：US06612811B2
公开(公告)日：2003-09-02
申请号：US10015313
申请日：2001-12-12
申请人： Clive A. Morgan , Todd S. Heffron
发明人： Clive A. Morgan , Todd S. Heffron
IPC分类号： F04D2958
CPC分类号： F01D5/187 , F05D2230/21 , Y10T29/49341
摘要： An airfoil for a turbine nozzle assembly of a gas turbine engine includes an outer side wall, an inner side wall, a leading edge extending from the outer side wall to the inner side wall, a trailing edge extending from the outer side wall to the inner side wall, a concave surface extending from the leading edge to the trailing edge on a pressure side of the airfoil, a convex surface extending from the leading edge to the trailing edge on a suction side of the airfoil, an outer cooling slot, an inner cooling slot, and at least one middle cooling slot formed in the concave side of the airfoil adjacent the trailing edge. Each of the cooling slots further includes a recessed wall, an inner slot side wall, an outer slot side wall, an inner corner fillet located between the inner slot side wall and the recessed wall, and an outer corner fillet located between the outer slot side wall and the recessed wall, wherein one of the inner and outer corner fillets for at least one of the inner and outer cooling slots forms a variable contour from an opening in the concave surface to an exit plane of the trailing edge cooling slots.
摘要翻译： 用于燃气涡轮发动机的涡轮喷嘴组件的翼型件包括外侧壁，内侧壁，从外侧壁延伸到内侧壁的前缘，从外侧壁延伸到内侧壁的后缘 侧壁，在所述翼型件的压力侧从所述前缘延伸到所述后缘的凹面;在所述翼型的吸力侧从所述前缘延伸到所述后缘的凸形表面，外部冷却槽，内部 冷却槽，以及形成在靠近后缘的翼型件的凹面中的至少一个中间冷却槽。 每个冷却槽还包括凹壁，内槽侧壁，外槽侧壁，位于内槽侧壁和凹壁之间的内拐角圆角，以及位于外槽侧 壁和凹入壁，其中用于内部和外部冷却槽中的至少一个的内部和外部角形圆角之一形成从凹入表面中的开口到后缘冷却槽的出口平面的可变轮廓。
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