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1. 发明申请

US20050123401A1 COMPONENT AND TURBINE ASSEMBLY WITH FILM COOLING 失效
标题翻译：组件和涡轮组件与薄膜冷却
公开(公告)号：US20050123401A1
公开(公告)日：2005-06-09
申请号：US10611749
申请日：2003-06-30
申请人： Ronald Bunker , Canan Hardwicke
发明人： Ronald Bunker , Canan Hardwicke
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2230/232 , F05D2230/312 , F05D2230/314 , F05D2250/11 , F05D2250/13 , F05D2260/221 , F05D2260/2212 , F05D2260/22141 , Y02T50/67 , Y02T50/672 , Y02T50/676
摘要： A component includes a wall with a cold and a hot surface. At least one film-cooling hole extends through the wall for flowing a coolant from the cold to the hot surface. The film-cooling hole defines an exit site in the hot surface. At least one flow modifier is formed on the hot surface and is adapted to direct the coolant flowing from the film-cooling hole and out of the exit site toward the hot surface. The flow modifier extends outwards from and conforms to the hot surface. A turbine assembly includes a first and a second component that define a secondary cooling slot, which receives and guides a secondary coolant flow. At least one flow modifier is formed on a surface of one of the two components and is adapted to enhance the secondary coolant flow along at least one of the two components within the secondary coolant slot.
摘要翻译：组件包括具有冷和热表面的壁。至少一个薄膜冷却孔延伸穿过壁，用于使冷却剂从冷的表面流到热表面。薄膜冷却孔在热表面中限定出口部位。在热表面上形成至少一个流动改性剂，并适于将从薄膜冷却孔流出的冷却剂引导到离开出口部位的冷却表面。流动调节器向外延伸并符合热表面。涡轮机组件包括限定二次冷却槽的第一和第二部件，其接收和引导二次冷却剂流。在两个部件中的一个部件的表面上形成至少一个流动调节器，并且适于增强沿次级冷却剂槽内的两个部件中的至少一个的二次冷却剂流。

2. 发明申请

US20070235157A1 METHOD OF FORMING CONCAVITIES IN THE SURFACE OF A METAL COMPONENT, AND RELATED PROCESSES AND ARTICLES 有权
标题翻译：金属部件表面形成方法及相关工艺及文章
公开(公告)号：US20070235157A1
公开(公告)日：2007-10-11
申请号：US10841366
申请日：2004-05-06
申请人： Ronald Bunker , Canan Hardwicke , Ching-Pang Lee
发明人： Ronald Bunker , Canan Hardwicke , Ching-Pang Lee
IPC分类号： B22C9/00 , B22C9/10
CPC分类号： B22C9/10 , B33Y10/00 , C04B41/009 , C04B41/5031 , C04B41/87 , C04B2111/0087 , C23C4/01 , F05B2260/222 , C04B41/4539 , C04B41/4572 , C04B41/5029 , C04B35/04 , C04B35/10 , C04B35/14 , C04B35/18 , C04B35/565 , C04B35/48 , C04B35/584 , C04B35/481 , C04B35/505
摘要： A method of forming at least one concavity of a selected size and shape within a surface of an internal passageway of a metallic component comprises: depositing a ceramic-based material by a direct-write technique onto a ceramic core which is suitable for forming the internal passageway during a casting process to form the metallic component, wherein the ceramic-based material is deposited as a positive feature; heat-treating the deposited ceramic-based material; forming the metallic component by a casting process in which the ceramic core is incorporated into the casting, in a position selected as a desired position for the internal passageway; and then removing the ceramic core from the metal component after the casting process is complete, thereby forming the internal passageway, with the concavity contained within the surface of the passageway, said concavity formed by removal of the positive feature of the ceramic-based material.
摘要翻译：在金属部件的内部通道的表面内形成选定尺寸和形状的至少一个凹部的方法包括：通过直接写入技术将陶瓷基材料沉积到适于形成内部的陶瓷芯上在铸造过程中形成金属部件的通道，其中所述陶瓷基材料作为阳性特征沉积; 对沉积的陶瓷基材料进行热处理; 通过铸造工艺形成金属部件，其中将陶瓷芯体结合到铸件中，位于被选择为内部通道的期望位置的位置; 然后在铸造过程完成之后从金属部件上除去陶瓷芯，由此形成内部通道，凹部包含在通道的表面内，通过去除陶瓷基材料的积极特征而形成所述凹部。

3. 发明申请

US20080000610A1 METHOD OF FORMING CONCAVITIES IN THE SURFACE OF A METAL COMPONENT, AND RELATED PROCESSES AND ARTICLES 审中-公开
标题翻译：金属部件表面形成方法及相关工艺及文章
公开(公告)号：US20080000610A1
公开(公告)日：2008-01-03
申请号：US11855709
申请日：2007-09-14
申请人： Ronald Bunker , Canan Hardwicke , Ching-Pang Lee
发明人： Ronald Bunker , Canan Hardwicke , Ching-Pang Lee
IPC分类号： B22C7/06 , B22D29/00
CPC分类号： B22C9/10 , B33Y10/00 , C04B41/009 , C04B41/5031 , C04B41/87 , C04B2111/0087 , C23C4/01 , F05B2260/222 , C04B41/4539 , C04B41/4572 , C04B41/5029 , C04B35/04 , C04B35/10 , C04B35/14 , C04B35/18 , C04B35/565 , C04B35/48 , C04B35/584 , C04B35/481 , C04B35/505
摘要： A method of forming at least one concavity of a selected size and shape within a surface of an internal passageway of a metallic component comprises: depositing a ceramic-based material by a direct-write technique onto a ceramic core which is suitable for forming the internal passageway during a casting process to form the metallic component, wherein the ceramic-based material is deposited as a positive feature; heat-treating the deposited ceramic-based material; forming the metallic component by a casting process in which the ceramic core is incorporated into the casting, in a position selected as a desired position for the internal passageway; and then removing the ceramic core from the metal component after the casting process is complete, thereby forming the internal passageway, with the concavity contained within the surface of the passageway, said concavity formed by removal of the positive feature of the ceramic-based material.
摘要翻译：在金属部件的内部通道的表面内形成选定尺寸和形状的至少一个凹部的方法包括：通过直接写入技术将陶瓷基材料沉积到适于形成内部的陶瓷芯上在铸造过程中形成金属部件的通道，其中所述陶瓷基材料作为阳性特征沉积; 对沉积的陶瓷基材料进行热处理; 通过铸造工艺形成金属部件，其中将陶瓷芯体结合到铸件中，位于被选择为内部通道的期望位置的位置; 然后在铸造过程完成之后从金属部件上除去陶瓷芯，由此形成内部通道，凹部包含在通道的表面内，通过去除陶瓷基材料的积极特征而形成所述凹部。

4. 发明申请

US20050268615A1 METHOD AND APPARATUS FOR COOLING COMBUSTOR LINER AND TRANSITION PIECE OF A GAS TURBINE 有权
标题翻译：用于冷却燃气轮机和气体涡轮机过渡部件的方法和装置
公开(公告)号：US20050268615A1
公开(公告)日：2005-12-08
申请号：US10907866
申请日：2005-04-19
申请人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson , John Intile
发明人： Ronald Bunker , Jeremy Bailey , Stanley Widener , Thomas Johnson , John Intile
IPC分类号： F23R3/06 , F02C7/12 , F02C7/18 , F23R3/00 , F23R3/30 , F23R3/42
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： A method and apparatus for cooling a combustor liner and transitions piece of a gas turbine include a combustor liner with a plurality of turbulators arranged in an array axially along a length defining a length of the combustor liner and located on an outer surface thereof; a first flow sleeve surrounding the combustor liner with a first flow annulus therebetween, the first flow sleeve having a plurality of rows of cooling holes formed about a circumference of the first flow sleeve for directing cooling air from the compressor discharge into the first flow annulus; a transition piece connected to the combustor liner and adapted to carry hot combustion gases to a stage of the turbine; a second flow sleeve surrounding the transition piece a second plurality of rows of cooling apertures for directing cooling air into a second flow annulus between the second flow sleeve and the transition piece; wherein the first plurality of cooling holes and second plurality of cooling apertures are each configured with an effective area to distribute less than 50% of compressor discharge air to the first flow sleeve and mix with cooling air from the second flow annulus.
摘要翻译：一种用于冷却燃烧器衬套和燃气轮机的过渡件的方法和设备包括具有多个湍流器的燃烧器衬套，该多个湍流器沿着限定燃烧器衬套的长度并位于其外表面上的长度轴向排列; 围绕所述燃烧器衬套的第一流动套筒，其间具有第一流动环空，所述第一流动套筒具有围绕所述第一流动套筒的圆周形成的多排冷却孔，用于将冷却空气从所述压缩机排出口引导到所述第一流动环空中; 连接到所述燃烧器衬套并适于将热燃烧气体运送到所述涡轮机的级的过渡件; 围绕所述过渡件的第二流动套筒，用于将冷却空气引导到所述第二流动套筒和所述过渡件之间的第二流动环空中的第二多排冷却孔; 其中所述第一多个冷却孔和第二多个冷却孔分别配置有有效区域以将小于50％的压缩机排出空气分配到所述第一流动套筒并与来自所述第二流动环的冷却空气混合。

5. 发明申请

US20050106020A1 Hot gas path component with mesh and turbulated cooling 失效
标题翻译：热气路组件与网状和紊流冷却
公开(公告)号：US20050106020A1
公开(公告)日：2005-05-19
申请号：US10718003
申请日：2003-11-19
申请人： Ronald Bunker , Jeremy Bailey , Ching-Pang Lee
发明人： Ronald Bunker , Jeremy Bailey , Ching-Pang Lee
IPC分类号： F01D5/18 , F01D5/20 , F01D9/02 , B63H1/14
CPC分类号： F01D5/20 , F01D5/187 , F05D2260/2212 , F05D2260/22141 , Y02T50/67 , Y02T50/671 , Y02T50/676
摘要： A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions of the wall. The pins define a mesh cooling arrangement having a number of flow channels. A number of turbulators are disposed on at least one of the inner and outer portions of the wall.
摘要翻译：一个部件包括至少一个具有内部部分和外部部分的壁。多个销在壁的内部和外部之间延伸。销钉限定具有多个流动通道的网状冷却装置。多个扰流器设置在壁的内部和外部的至少一个上。

6. 发明申请

US20060099080A1 Methods and apparatus for cooling gas turbine engine components 失效
标题翻译：用于冷却燃气涡轮发动机部件的方法和装置
公开(公告)号：US20060099080A1
公开(公告)日：2006-05-11
申请号：US10984292
申请日：2004-11-09
申请人： Ching-Pang Lee , Ronald Bunker , Harvey Maclin , Ramgopal Darolia
发明人： Ching-Pang Lee , Ronald Bunker , Harvey Maclin , Ramgopal Darolia
IPC分类号： F03B3/12
CPC分类号： F23R3/002 , F01D5/183 , F01D5/186 , F01D5/288 , F05D2230/90 , F05D2300/611 , F23R2900/03041
摘要： A method of cooling a gas turbine engine component having a perforate metal wall includes providing a plurality of pores in the wall, wherein the pores extend substantially perpendicularly through the wall, and wherein the pores are covered and sealed closed at first ends thereof by a thermal barrier coating disposed over a first surface of the wall, and providing a plurality of film cooling holes in the wall, wherein the holes extend substantially perpendicularly through the wall and the thermal barrier coating. The method also includes providing cooling fluid to the plurality of pores and the plurality of film cooling holes along a second surface of the wall, channeling the cooling fluid through the pores for back side cooling an inner surface of the thermal barrier coating, and channeling the cooling fluid through the holes for film cooling an outer surface of the thermal barrier coating.
摘要翻译：一种冷却具有穿孔金属壁的燃气涡轮发动机部件的方法包括在壁中提供多个孔，其中孔基本上垂直延伸穿过壁，并且其中孔在其第一端被热封屏障涂层，其设置在所述壁的第一表面上，并且在所述壁中提供多个膜冷却孔，其中所述孔基本上垂直延伸穿过所述壁和所述热障涂层。该方法还包括沿着壁的第二表面向多个孔和多个膜冷却孔提供冷却流体，将冷却流体引导通过孔，用于背面冷却热障涂层的内表面，并且引导冷却流体通过孔，用于薄膜冷却隔热涂层的外表面。

7. 发明申请

US20050232769A1 Thermal shield turbine airfoil 失效
标题翻译：隔热涡轮机翼型
公开(公告)号：US20050232769A1
公开(公告)日：2005-10-20
申请号：US10824922
申请日：2004-04-15
申请人： Ching-Pang Lee , Ronald Bunker
发明人： Ching-Pang Lee , Ronald Bunker
IPC分类号： F01D5/18 , B63H1/14
CPC分类号： F01D5/187 , Y02T50/676
摘要： A turbine airfoil includes opposite pressure and suction sides joined together at leading and trailing edges. An outwardly convex nose bridge bridges the pressure and suction sides behind the leading edge, and is integrally joined to a complementary thermally insulating shield spaced therefrom to define a bridge channel. The shield includes the leading edge and wraps laterally aft around the nose bridge along both the pressure and suction sides.
摘要翻译：涡轮机翼片包括在前缘和后缘处连接在一起的相对的压力和吸力侧。一个向外凸起的鼻梁桥接了前缘后面的压力和吸力侧，并且与其隔开的互补隔热屏蔽件整体地接合以限定桥接通道。护罩包括前缘，沿着压力和吸力侧在鼻梁周围侧向包裹。

8. 发明申请

US20070245741A1 Methods and system for reducing pressure losses in gas turbine engines 有权
标题翻译：减少燃气轮机发动机压力损失的方法和系统
公开(公告)号：US20070245741A1
公开(公告)日：2007-10-25
申请号：US11409807
申请日：2006-04-24
申请人： David Johnson , Kenneth Whaling , Ronald Bunker
发明人： David Johnson , Kenneth Whaling , Ronald Bunker
IPC分类号： F23R3/00
CPC分类号： F23R3/005 , F01D9/023 , F01D25/14 , F23R3/04 , F23R2900/03044
摘要： A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the flowsleeve and the combustor liner. The method also includes orienting the flowsleeve such that a plurality of inlets formed within the flowsleeve are positioned to inject cooling air in a substantially axial direction into the annular flow path to facilitate cooling the combustor liner.
摘要翻译：提供了一种组装燃烧器组件的方法，其中所述方法包括提供具有中心线轴线并且在其中限定燃烧室的燃烧器衬套，并且将环形流动叶片从燃烧器衬套径向向外耦合，使得环形流动路径基本上周向地限定在流动与燃烧器衬套之间。该方法还包括使流动方向定向，使得形成在流动中的多个入口被定位成将大致轴向的冷却空气注入到环形流动路径中以便于冷却燃烧器衬套。

9. 发明申请

US20070144179A1 Shaped walls for enhancement of deflagration-to-detonation transition 有权
标题翻译：形状的墙壁，用于加强爆燃转爆
公开(公告)号：US20070144179A1
公开(公告)日：2007-06-28
申请号：US11315407
申请日：2005-12-22
申请人： Pierre Pinard , Venkat Tangirala , Adam Rasheed , Anthony Dean , Ronald Bunker , David Chapin
发明人： Pierre Pinard , Venkat Tangirala , Adam Rasheed , Anthony Dean , Ronald Bunker , David Chapin
IPC分类号： F23R7/00
CPC分类号： F23R7/00
摘要： A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber
摘要翻译：一种用于脉冲爆震燃烧器的爆轰室，包括：多个凹坑，其设置在所述爆炸室的内表面的至少一部分上，其中所述多个凹坑增强了通过所述爆轰室的流体流动的紊流

10. 发明申请

US20060285974A1 TURBINE BUCKET TIP CAP 有权
标题翻译：涡轮提篮盖
公开(公告)号：US20060285974A1
公开(公告)日：2006-12-21
申请号：US11160272
申请日：2005-06-16
申请人： Ronald Bunker , Gary Itzel
发明人： Ronald Bunker , Gary Itzel
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05C2201/0463 , F05C2201/0466 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.
摘要翻译：用于涡轮机桶的顶盖件。尖端盖可以包括冷侧和位于冷侧的多个销。

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