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公开(公告)号：US07976274B2
公开(公告)日：2011-07-12
申请号：US11297699
申请日：2005-12-08
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F01D9/02 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.
摘要翻译： 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，该涡轮喷嘴包括内带，外带，在内带和外带之间延伸的至少一个叶片，以及在至少一个叶片和至少一个叶片之间延伸的至少一个前缘圆角 内部和外部带，其中所述至少一个叶片的前缘在所述内部和外部带的前缘的下游，以及将所述涡轮喷嘴连接在所述燃气涡轮发动机内，使得所述前缘圆角被配置为有助于最小化涡旋 沿着与内带和外带中的至少一个相邻的叶片前缘的形成。
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公开(公告)号：US20070134087A1
公开(公告)日：2007-06-14
申请号：US11297082
申请日：2005-12-08
申请人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles , Douglas Fortuna
发明人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles , Douglas Fortuna
IPC分类号： F01D9/00
CPC分类号： F01D9/023 , F01D9/042 , F01D25/246 , F05D2300/505 , Y02T50/673 , Y02T50/675
摘要： A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, and at least one vane extending between the inner and outer bands, coupling the turbine nozzle within the gas turbine engine, such that the turbine nozzle is downstream from a combustor, and coupling the turbine nozzle to the combustor using at least a first annular ring, wherein the first annular ring substantially seals a gap defined between the turbine nozzle and the combustor.
摘要翻译： 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，其包括内带，外带，以及在内带和外带之间延伸的至少一个叶片，将涡轮喷嘴连接在燃气涡轮发动机内，使得涡轮喷嘴在 燃烧器，并且使用至少第一环形环将涡轮喷嘴耦合到燃烧器，其中第一环形圈基本上密封限定在涡轮喷嘴和燃烧器之间的间隙。
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公开(公告)号：US07195454B2
公开(公告)日：2007-03-27
申请号：US11002570
申请日：2004-12-02
CPC分类号： F01D5/143 , F01D5/145 , F01D9/041 , F01D11/005 , F01D25/246 , F05D2250/19 , Y02T50/673
摘要： A turbine airfoil includes opposite pressure and suction sides extending in span from a flowpath surface. The flowpath surface has chordally opposite forward and aft edges and laterally opposite first and second endfaces corresponding with the airfoil pressure and suction sides. The flowpath surface joins the first endface at the forward edge in a forward bullnose and joins the second endface at the aft edge in an aft bullnose, with the bullnoses varying in radius from the opposite edges.
摘要翻译： 涡轮机翼型包括从流路表面跨越的相对的压力和吸力侧。 流路表面具有弦向相反的前后边缘，并且与翼型压力和吸力侧对应的横向相对的第一和第二端面。 流路表面将前端长嘴的前边缘处的第一端面连接起来，并且在后方长臂处的后边缘处连接第二端面，其中棱镜从相对边缘的半径变化。
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公开(公告)号：US20060062671A1
公开(公告)日：2006-03-23
申请号：US10898835
申请日：2004-07-26
申请人： Ching-Pang Lee , Wenfeng Lu
发明人： Ching-Pang Lee , Wenfeng Lu
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/081 , F01D5/187 , F05D2260/607 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls spaced apart between opposite leading and trailing edges and interconnected by a plurality of partitions to define first and second independent cooling circuits therein. The cooling circuits have corresponding inlets in a dovetail of the blade and extend through a platform of the blade and through the airfoil to its tip. A common discharge chamber is disposed below the airfoil tip and includes a plurality of outlet holes for discharging cooling air from the circuits.
摘要翻译： 涡轮机叶片包括具有在相对的前缘和后缘间隔开的压力和吸力侧壁的翼型件，并通过多个隔板互连以在其中限定第一和第二独立冷却回路。 冷却回路在叶片的燕尾形中具有相应的入口，并延伸穿过叶片的平台并且通过翼型件到其顶端。 公共排放室设置在翼型件末端的下方，并且包括用于从电路排出冷却空气的多个出口孔。
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公开(公告)号：US20070134089A1
公开(公告)日：2007-06-14
申请号：US11297699
申请日：2005-12-08
申请人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles
发明人： Ching-Pang Lee , Joseph Guentert , Wenfeng Lu , Mitchell Iles
IPC分类号： F01D9/00
CPC分类号： F01D9/041 , F01D5/143 , F01D5/145 , F01D9/02 , F05D2240/81 , Y02T50/673 , Y02T50/676
摘要： A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.
摘要翻译： 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，该涡轮喷嘴包括内带，外带，在内带和外带之间延伸的至少一个叶片，以及在至少一个叶片和至少一个叶片之间延伸的至少一个前缘圆角 内部和外部带，其中所述至少一个叶片的前缘在所述内部和外部带的前缘的下游，以及将所述涡轮喷嘴连接在所述燃气涡轮发动机内，使得所述前缘圆角被配置为有助于最小化涡旋 沿着与内带和外带中的至少一个相邻的叶片前缘的形成。
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公开(公告)号：US07118342B2
公开(公告)日：2006-10-10
申请号：US10937642
申请日：2004-09-09
IPC分类号： F01D5/14
CPC分类号： F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges and root and tip. The tip includes squealer ribs extending from a tip floor forming an open tip cavity. The rib along the pressure sidewall has a squared external corner, and a flute extends along the base of the rib at the tip floor.
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公开(公告)号：US20060051209A1
公开(公告)日：2006-03-09
申请号：US10937642
申请日：2004-09-09
申请人： Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
发明人： Ching-Pang Lee , James Bailey , Nicholas Palmer , Wenfeng Lu
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/20 , F01D11/08 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges and root and tip. The tip includes squealer ribs extending from a tip floor forming an open tip cavity. The rib along the pressure sidewall has a squared external corner, and a flute extends along the base of the rib at the tip floor.
摘要翻译： 涡轮机叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及根部和尖端的翼型件。 尖端包括从形成开口尖端腔的尖端底部延伸的尖叫肋。 沿着压力侧壁的肋具有平方的外角，并且凹槽沿尖端底部的肋的基部延伸。
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公开(公告)号：US07140835B2
公开(公告)日：2006-11-28
申请号：US10956299
申请日：2004-10-01
IPC分类号： F01D9/02
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.
摘要翻译： 涡轮喷嘴包括连接到相对的内部和外部带的中空叶片。 内带包括在叶片的前缘下方的前唇，在叶片的后缘下方的后唇，以及间隔开的安装凸缘。 冲击孔从安装凸缘的底部在内带的角部向后缘倾斜地向后延伸，用于冲击冷却。
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公开(公告)号：US20060073011A1
公开(公告)日：2006-04-06
申请号：US10956299
申请日：2004-10-01
申请人： Ching-Pang Lee , Baolan Shi , Wenfeng Lu , Joseph Guentert , Steven Brassfield
发明人： Ching-Pang Lee , Baolan Shi , Wenfeng Lu , Joseph Guentert , Steven Brassfield
IPC分类号： F01D9/00
CPC分类号： F01D5/187 , F05D2240/81 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle includes a hollow vane joined to opposite inner and outer bands. The inner band includes a forward lip under the leading edge of the vane, an aft lip under the trailing edge of the vane, and a mounting flange spaced therebetween. An impingement bore extends obliquely and aft from the base of the mounting flange under a corner of the inner band toward the aft lip for impingement cooling thereof.
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公开(公告)号：US07341427B2
公开(公告)日：2008-03-11
申请号：US11306221
申请日：2005-12-20
申请人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
发明人： Andrew David Farmer , Bangalore Aswatha Nagaraj , Wenfeng Lu , Ching-Pang Lee , Joseph Michael Guentert
IPC分类号： F04D9/02
CPC分类号： F01D5/288 , F01D9/041 , F05D2220/31 , F05D2230/21 , F05D2230/31 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611
摘要： A gas turbine engine nozzle segment and process for producing such a nozzle segment to exhibit improved durability and aerodynamic performance. The process produces a nozzle segment having at least one vane between and interconnecting a pair of platforms. The nozzle segment is cast from a gamma prime-strengthened nickel-base superalloy, on whose surface is thermal sprayed an environmental coating formed of a MCrAlX-type coating material. The surface of the environmental coating is then worked to cause the coating to have a surface finish of less than 2.0 micrometers Ra. Cooling holes are then drilled in the nozzle segment, after which an oxidation-resistant coating is applied on the smoothed surface of the nozzle segment so as to maintain an outermost surface on the nozzle segment having surface finish of less than 2.0 micrometers Ra.
摘要翻译： 一种燃气涡轮发动机喷嘴段和用于生产这种喷嘴段的工艺，以显示出改善的耐久性和空气动力性能。 该过程产生具有在一对平台之间并互连的至少一个叶片的喷嘴段。 喷嘴段由伽马强化镍基超级合金铸造，其表面被热喷涂为由MCrAlX型涂层材料形成的环境涂层。 然后对环境涂层的表面进行加工，使涂层的表面光洁度小于2.0微米。 然后在喷嘴段中钻出冷却孔，然后在喷嘴段的平滑表面上施加耐氧化涂层，以便保持表面光洁度小于2.0微米Ra的喷嘴段上的最外表面。
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