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1. 发明授权

US08459951B2 Rotor for an axial flow turbomachine 失效
标题翻译：转子用于轴流涡轮机
公开(公告)号：US08459951B2
公开(公告)日：2013-06-11
申请号：US12672794
申请日：2008-08-08
申请人： Douglas J. Arrell , Harald Hoell , David W. Hunt , Karsten Kolk , Harald Nimptsch
发明人： Douglas J. Arrell , Harald Hoell , David W. Hunt , Karsten Kolk , Harald Nimptsch
IPC分类号： F01D5/06
CPC分类号： F01D5/06 , F01D5/28 , F04D29/053 , F04D29/321 , F04D29/584 , F05D2240/20 , F05D2300/502
摘要： A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.
摘要翻译：提供了一种用于轴流涡轮机的转子。转子包括多个转子盘，它们被布置成堆叠并且与至少一个拉杆夹紧在一起。转子的转子盘中的至少一个包括比相邻的转子盘之一更小的外径，并且通过围绕具有较小外径的转子盘的转鼓来补偿直径差。滚筒可以由耐热材料制成。由滚筒包围的转子盘可以由较便宜的材料制成。此外，滚筒可以包括比由滚筒包围的转子盘至少多一个叶片环。

2. 发明申请

US20110318184A1 ROTOR FOR AN AXIAL FLOW TURBOMACHINE 失效
标题翻译：旋转轴流动涡轮机
公开(公告)号：US20110318184A1
公开(公告)日：2011-12-29
申请号：US12672794
申请日：2008-08-08
申请人： Douglas J. Arrell , Harald Hoell , David W. Hunt , Karsten Kolk , Harald Nimptsch
发明人： Douglas J. Arrell , Harald Hoell , David W. Hunt , Karsten Kolk , Harald Nimptsch
IPC分类号： F01D5/06
CPC分类号： F01D5/06 , F01D5/28 , F04D29/053 , F04D29/321 , F04D29/584 , F05D2240/20 , F05D2300/502
摘要： A rotor for an axial flow turbomachine is provided. The rotor includes a plurality of rotor discs that are arranged in stacks and clamped together with at least one tie rod. At least one of the rotor discs of the rotor comprises a smaller outer diameter than one of the neighboring rotor discs and that the difference in diameter is compensated by a drum surrounding the rotor disc with the smaller outer diameter as a ring. The drum may be made of a heat resistant material. The rotor discs surrounded by the drum may be made of a less expensive material. Furthermore, the drum may include at least one more blade ring than the rotor discs that are surrounded by the drum.
摘要翻译：提供了一种用于轴流式涡轮机的转子。转子包括多个转子盘，它们被布置成堆叠并且与至少一个拉杆夹紧在一起。转子的转子盘中的至少一个包括比相邻的转子盘之一更小的外径，并且通过围绕具有较小外径的转子盘的转鼓来补偿直径差。滚筒可以由耐热材料制成。由滚筒包围的转子盘可以由较便宜的材料制成。此外，滚筒可以包括比由滚筒包围的转子盘至少多一个叶片环。

3. 发明授权

US08043717B2 Combustion turbine component having rare earth CoNiCrAl coating and associated methods 有权
标题翻译：具有稀土CoNiCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US08043717B2
公开(公告)日：2011-10-25
申请号：US12194577
申请日：2008-08-20
申请人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
发明人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
IPC分类号： B32B15/04 , C23C4/06
CPC分类号： C23C30/00 , B22F1/0085 , B22F1/0088 , B22F9/082 , B22F2998/10 , B22F2999/00 , C22C1/002 , C23C4/073 , C23C4/10 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , C23C28/347 , F01D5/288 , F01D25/007 , F05C2201/0463 , F05C2201/0466 , F05D2300/121 , F05D2300/132 , F05D2300/15 , Y10T428/12535 , Y10T428/12611 , Y10T428/1266 , Y10T428/31678 , B22F2201/01 , B22F2201/03 , C23C24/00
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes a first amount, by weight percent, of cobalt (Co) and a second amount, by weight percent, of nickel (Ni), the first amount being greater than the second amount. The alloy coating further includes chromium (Cr), aluminum (Al), at least one rare earth element, and an oxide of the at least one rare earth element.
摘要翻译：燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。合金涂层（14）包括第一量的重量百分比的钴（Co）和第二量的以镍（Ni）的重量百分比计的第一量，第一量大于第二量。合金涂层还包括铬（Cr），铝（Al），至少一种稀土元素和至少一种稀土元素的氧化物。

4. 发明授权

US08042268B2 Method of producing a turbine component with multiple interconnected layers of cooling channels 有权
标题翻译：制造具有多个相互连接的冷却通道层的涡轮机部件的方法
公开(公告)号：US08042268B2
公开(公告)日：2011-10-25
申请号：US12052937
申请日：2008-03-21
申请人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
发明人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
IPC分类号： B23P15/04
CPC分类号： B21D53/78 , B22D25/00 , Y10T29/4932 , Y10T29/49341 , Y10T29/49885 , Y10T29/4998 , Y10T29/49982
摘要： A method for making a gas turbine component (100). A central core (20) is positioned to occupy a space that will define a central channel (42), and an outer channel core (30) is positioned spaced apart from the central core (20). A mold (35) is formed around the central core (20) and the outer channel core (30), so that an exterior wall (32) contacts the mold (35). A substrate material, such as a metal alloy (247) in liquid form, is added to the mold (35) to form an internal volume (41) of the component (100). The central core (20) and the outer channel core (30) are removed, and interconnect channels (44) are formed between the thus-formed central channel (42) and the inner portion (49) of the outer channel (62) thus far formed. A preform (55) is placed into the inner portion (49) and may have a desired outer surface (57) shape. An overlay material is applied to form an outer layer (60), thus defining the remainder of the outer channel (62), which is obtained upon removal of the preform (55).
摘要翻译：一种制造燃气轮机部件（100）的方法。中心芯（20）定位成占据将限定中心通道（42）的空间，并且外通道芯（30）定位成与中心芯（20）间隔开。围绕中心芯（20）和外通道芯（30）形成模具（35），使得外壁（32）接触模具（35）。液体形式的金属合金（247）等基板材料被加入到模具（35）中以形成部件（100）的内部容积（41）。去除中心芯（20）和外通道芯（30），并且互连通道（44）形成在如此形成的中心通道（42）和外通道（62）的内部部分（49）之间，因此远远形成。将预成型件（55）放置在内部部分（49）中并且可以具有期望的外表面（57）形状。施加覆盖材料以形成外层（60），从而限定了在移除预成型件（55）时获得的外部通道（62）的剩余部分。

5. 发明授权

US07950146B2 Co-forged steel rotor component for steam and gas turbine engines 有权
标题翻译：用于蒸汽和燃气涡轮发动机的共锻钢转子部件
公开(公告)号：US07950146B2
公开(公告)日：2011-05-31
申请号：US11784988
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： F01D5/02 , F01D5/34
CPC分类号： B23P15/006 , B21J1/00 , B21K1/32 , B21K3/00 , F01D5/02 , Y10T29/4932 , Y10T29/49321
摘要： A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second material, such as a low alloy steel, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.
摘要翻译：一种形成涡轮发动机的转子的方法，使得转子由两种材料形成，包括：由第一钢材形成的外圈和由诸如低合金钢的第二材料形成的盘，其具有较大的热膨胀系数比形成内盘的第一种材料高。环可以包括具有圆锥形状的内孔，并且盘可以具有圆锥形的外表面和具有大于环的一部分的部分的直径。可以加热环，使得孔扩大到比内盘最大直径大的尺寸。环可以定位在盘上并允许冷却以允许环附接到盘。然后可以共同锻造环和盘。

6. 发明申请

US20110110772A1 Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same 审中-公开
标题翻译：具有近表面冷却通道的涡轮发动机部件及其制造方法
公开(公告)号：US20110110772A1
公开(公告)日：2011-05-12
申请号：US12616249
申请日：2009-11-11
申请人： Douglas J. Arrell , Stefan Mazzola
发明人： Douglas J. Arrell , Stefan Mazzola
IPC分类号： F01D25/08 , B23P11/00
CPC分类号： F01D5/187 , B23P15/04 , F01D5/147 , F01D5/18 , F01D9/02 , F01D25/005 , F01D25/12 , F05D2230/60 , F05D2230/90 , F05D2240/12 , F05D2300/502 , F05D2300/50212 , Y10T29/49321 , Y10T29/49341
摘要： A turbine airfoil has an airfoil-shaped core and a skin extending about the outer peripheral surface of the core. The core and/or the skin are configured such that a plurality of cooling channels is formed between them. In one embodiment, the cooling channels are formed by a plurality of radially extending channels in the core. In another embodiment, the cooling channels are formed by providing a wave-shaped skin such that, when the skin is attached to the outer peripheral surface of the core, the cooling channels can be formed in the space between the outer peripheral surface of the core and each wave of the skin. Such airfoil constructions can allow the inclusion of different materials in the airfoil. Further, such constructions can allow greater flexibility in the formation of cooling channels. Moreover, such constructions can help to achieve thinner outer walls and near surface cooling of the airfoil.
摘要翻译：涡轮机翼型具有翼型芯和围绕芯的外周表面延伸的表皮。芯和/或皮肤被配置成使得在它们之间形成多个冷却通道。在一个实施例中，冷却通道由芯中的多个径向延伸的通道形成。在另一个实施例中，冷却通道是通过提供波形皮肤来形成的，使得当皮肤附接到芯的外周表面时，冷却通道可以形成在芯的外周表面之间的空间中和每一波的皮肤。这种翼型结构可以允许在翼型中包括不同的材料。此外，这种结构可以在冷却通道的形成中允许更大的灵活性。此外，这种结构可以帮助实现更薄的外壁和翼面的近表面冷却。

7. 发明授权

US07854809B2 Heat treatment system for a composite turbine engine component 有权
标题翻译：用于复合涡轮发动机部件的热处理系统
公开(公告)号：US07854809B2
公开(公告)日：2010-12-21
申请号：US11784985
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： C21D8/02 , C21D6/02
CPC分类号： C21D1/22 , C21D1/58 , C21D1/613 , C21D6/02 , C22F1/10
摘要： A heat treatment process for a component of a turbine engine formed from multiple materials, such as steel and nickel. The heat treatment process includes two stages: a first stage for austinitizing the steel and solutioning the nickel, and a second stage for ageing and tempering the materials. The heat treatment process may include heating a component formed from a steel portion and a nickel portion such that the steel portion austinitizes and the nickel portion undergoes solutioning, cooling the component to prevent the excessive formation of gamma prime ({grave over (y)}), and subjecting the component to a temper heat treatment during which martensite tempering occurs.
摘要翻译：一种用于由诸如钢和镍的多种材料形成的涡轮发动机的部件的热处理方法。热处理工艺包括两个阶段：用于奥氏体化钢和溶解镍的第一阶段，以及用于老化和回火材料的第二阶段。热处理方法可以包括加热由钢部分和镍部分形成的部件，使得钢部分奥氏体化，并且镍部分进行溶解，冷却该部件以防止过大的γ'（（（y）} ），对该部件进行马氏体回火的回火热处理。

8. 发明申请

US20100043597A1 METHOD OF MAKING RARE-EARTH STRENGTHENED COMPONENTS 有权
标题翻译：制备稀土强化组分的方法
公开(公告)号：US20100043597A1
公开(公告)日：2010-02-25
申请号：US12194154
申请日：2008-08-19
申请人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
发明人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
IPC分类号： B22F9/06
CPC分类号： C22C1/1078 , B22F2998/00 , B22F2998/10 , B22F2999/00 , C22C32/0026 , B22F5/04 , B22F5/009 , B22F9/082 , B22F9/04 , B22F1/0088 , B22F1/0085 , B22F2201/10 , B22F2201/20 , B22F2201/03
摘要： A method of manufacturing a metallic component includes atomizing, in an inert atmosphere, a metallic liquid having at least one rare-earth element and at least one non rare-earth element to form a metallic powder. A series of heat treating steps are performed on the metallic powder. A first heat treating step is performed in an oxidizing atmosphere, and a second heat treating step is performed in an inert atmosphere. A third heat treating step is performed in a reducing atmosphere to form a metallic power having an increased proportion of rare-earth oxides compared to non rare-earth oxides. The metallic component is formed from the metallic powder having the increased proportion of rare-earth oxides compared to non rare-earth oxides.
摘要翻译：制造金属成分的方法包括在惰性气氛中使具有至少一种稀土元素和至少一种非稀土元素的金属液体雾化，形成金属粉末。对金属粉末进行一系列热处理步骤。在氧化气氛中进行第一热处理工序，在惰性气氛中进行第二热处理工序。在还原性气氛中进行第3热处理工序，与非稀土类氧化物相比，形成稀土类氧化物比例增加的金属粉末。与非稀土氧化物相比，金属组分由稀土氧化物比例增加的金属粉末形成。

9. 发明申请

US20090235525A1 Method of Producing a Turbine Component with Multiple Interconnected Layers of Cooling Channels 有权
标题翻译：制造具有冷却通道多个互连层的涡轮机部件的方法
公开(公告)号：US20090235525A1
公开(公告)日：2009-09-24
申请号：US12052937
申请日：2008-03-21
申请人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
发明人： Douglas J. Arrell , Allister W. James , Anand A. Kulkarni
IPC分类号： B23P15/02 , B21D53/78 , B22D25/06
CPC分类号： B21D53/78 , B22D25/00 , Y10T29/4932 , Y10T29/49341 , Y10T29/49885 , Y10T29/4998 , Y10T29/49982
摘要： A method for making a gas turbine component (100). A central core (20) is positioned to occupy a space that will define a central channel (42), and an outer channel core (30) is positioned spaced apart from the central core (20). A mold (35) is formed around the central core (20) and the outer channel core (30), so that an exterior wall (32) contacts the mold (35). A substrate material, such as a metal alloy (247) in liquid form, is added to the mold (35) to form an internal volume (41) of the component (100). The central core (20) and the outer channel core (30) are removed, and interconnect channels (44) are formed between the thus-formed central channel (42) and the inner portion (49) of the outer channel (62) thus far formed. A preform (55) is placed into the inner portion (49) and may have a desired outer surface (57) shape. An overlay material is applied to form an outer layer (60), thus defining the remainder of the outer channel (62), which is obtained upon removal of the preform (55).
摘要翻译：一种制造燃气轮机部件（100）的方法。中心芯（20）定位成占据将限定中心通道（42）的空间，并且外通道芯（30）定位成与中心芯（20）间隔开。围绕中心芯（20）和外通道芯（30）形成模具（35），使得外壁（32）接触模具（35）。液体形式的金属合金（247）等基板材料被加入到模具（35）中以形成部件（100）的内部容积（41）。去除中心芯（20）和外通道芯（30），并且互连通道（44）形成在如此形成的中心通道（42）和外通道（62）的内部部分（49）之间，因此远远形成。将预成型件（55）放置在内部部分（49）中并且可以具有期望的外表面（57）形状。施加覆盖材料以形成外层（60），从而限定了在移除预成型件（55）时获得的外部通道（62）的剩余部分。

10. 发明申请

US20090075112A1 Combustion Turbine Component Having Rare Earth FeCrAl Coating and Associated Methods 有权
标题翻译：具有稀土FeCrAl涂层的燃烧涡轮机组件及相关方法
公开(公告)号：US20090075112A1
公开(公告)日：2009-03-19
申请号：US12194596
申请日：2008-08-20
申请人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
发明人： Anand A. Kulkarni , Allister W. James , Douglas J. Arrell
IPC分类号： B32B15/00 , B32B15/01 , B32B15/04 , B05D1/02
CPC分类号： C23C30/00 , B22F1/0018 , B22F5/04 , B22F7/08 , B22F9/082 , B22F2998/10 , C23C4/06 , C23C4/10 , C23C4/12 , C23C24/04 , C23C28/321 , C23C28/3215 , C23C28/3455 , C23C28/347 , Y10T428/12611 , Y10T428/1266 , Y10T428/31678 , B22F9/04 , B22F2201/04 , B22F2201/10 , B22F2201/01 , B22F2201/03
摘要： A combustion turbine component (10) includes a combustion turbine component substrate (16) and an alloy coating (14) on the combustion turbine component substrate. The alloy coating (14) includes iron (Fe), chromium (Cr), aluminum (Al), at least one of titanium (Ti) and molybdenum (Mo), at least one rare earth element, and an oxide of the at least one rare earth element.
摘要翻译：燃气涡轮机部件（10）包括燃气轮机部件基板（16）和燃烧涡轮部件基板上的合金涂层（14）。合金涂层（14）包括铁（Fe），铬（Cr），铝（Al），钛（Ti）和钼（Mo）中的至少一种，至少一种稀土元素和至少一种氧化物一个稀土元素。

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