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1. 发明授权

US06234755B1 Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture 有权
标题翻译：用于改善气态冷却剂流的冷却效果的方法以及相关的制品
公开(公告)号：US06234755B1
公开(公告)日：2001-05-22
申请号：US09411206
申请日：1999-10-04
申请人： Ronald Scott Bunker , Jeremy Clyde Bailey , Ching-Pang Lee , Nesim Abuaf
发明人： Ronald Scott Bunker , Jeremy Clyde Bailey , Ching-Pang Lee , Nesim Abuaf
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F01D5/288 , F01D25/12 , F05D2230/90 , F05D2260/202 , F05D2260/221 , F05D2300/611 , Y02T50/67 , Y02T50/676
摘要： A method is described for improving the cooling effectiveness of a fluid which flows through a row of passage holes in a substrate (e.g., a turbine component), out to a high-temperature surface of the substrate. The method involves forming a slot over the holes, within the high temperature surface of the substrate. The slot can be formed within protective coatings applied over the substrate. Alternatively, it can be formed partially within the substrate, and partially within the protective coatings. Movement of a film coolant through the substrate and into the slot results in greater cooling effectiveness. Related articles are also described.
摘要翻译：描述了一种用于改善流过基板（例如，涡轮机部件）中的一排通道孔的流体到基板的高温表面的冷却效率的方法。该方法包括在衬底的高温表面内在孔上形成槽。槽可以形成在施加在基板上的保护涂层内。或者，其可以部分地形成在基底内，部分地形成在保护性涂层内。薄膜冷却剂通过基底并进入槽中的运动导致更大的冷却效果。还描述了相关文章。

2. 发明授权

US5660525A Film cooled slotted wall 失效
标题翻译：薄膜冷却开槽墙
公开(公告)号：US5660525A
公开(公告)日：1997-08-26
申请号：US94998
申请日：1993-07-23
申请人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf , Steven Joseph Brzozowski
发明人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf , Steven Joseph Brzozowski
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/12 , F05D2250/121 , F05D2260/202
摘要： A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. The holes are also disposed in converging pairs to impinge together in the slot the first fluid channeled therethrough. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.
摘要翻译：适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。这些孔也以会聚对设置，以将槽中的第一流体冲入其中。在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

3. 发明授权

US5651662A Film cooled wall 失效
标题翻译：薄膜冷却墙
公开(公告)号：US5651662A
公开(公告)日：1997-07-29
申请号：US968544
申请日：1992-10-29
申请人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf
发明人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F05D2250/12 , F05D2250/121 , F05D2260/202
摘要： A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.
摘要翻译：适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

4. 发明申请

US20060138195A1 Method for providing turbulation on the inner surface of holes in an article, and related articles 审中-公开
标题翻译：在物品的孔的内表面上提供紊流的方法及相关物品
公开(公告)号：US20060138195A1
公开(公告)日：2006-06-29
申请号：US11054635
申请日：2005-02-08
申请人： Wayne Hasz , Nesim Abuaf , Robert Johnson , Ching-Pang Lee
发明人： Wayne Hasz , Nesim Abuaf , Robert Johnson , Ching-Pang Lee
IPC分类号： A47J36/02
CPC分类号： F28F13/18 , B23K35/30 , F01D5/147 , F01D5/186 , F05C2201/0463 , F05C2201/0466 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2230/23 , F05D2230/40 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F05D2300/132 , F05D2300/172 , F05D2300/222 , Y02T50/67 , Y02T50/676 , Y10T428/12993
摘要： A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.
摘要翻译：描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。首先将该紊乱施加到最终可以插入通道孔中的基底。基板通常是由牺牲材料形成的棒或管。在对基板施加了混浊之后，将基板插入到通孔中。然后使用常规的加热技术将紊乱材料熔合到内表面。然后可以通过各种技术从孔中去除牺牲衬底。还描述了相关文章。

5. 发明授权

US06910620B2 Method for providing turbulation on the inner surface of holes in an article, and related articles 有权
标题翻译：在物品的孔的内表面上提供紊流的方法及相关物品
公开(公告)号：US06910620B2
公开(公告)日：2005-06-28
申请号：US10271098
申请日：2002-10-15
申请人： Wayne Charles Hasz , Nesim Abuaf , Robert Alan Johnson , Ching-Pang Lee
发明人： Wayne Charles Hasz , Nesim Abuaf , Robert Alan Johnson , Ching-Pang Lee
IPC分类号： F01D5/08 , B23K35/30 , C22C19/05 , C22C19/07 , C22C38/00 , F01D5/14 , F01D5/18 , F01D5/28 , F02C7/00 , F28F13/18 , B23K35/12 , B05D3/02 , B23K31/00
CPC分类号： F28F13/18 , B23K35/30 , F01D5/147 , F01D5/186 , F05C2201/0463 , F05C2201/0466 , F05D2230/10 , F05D2230/21 , F05D2230/22 , F05D2230/23 , F05D2230/40 , F05D2260/202 , F05D2260/2212 , F05D2260/22141 , F05D2300/132 , F05D2300/172 , F05D2300/222 , Y02T50/67 , Y02T50/676 , Y10T428/12993
摘要： A method of providing turbulation on the inner surface of a passage hole (e.g., a turbine cooling hole) is described. The turbulation is first applied to a substrate which can eventually be inserted into the passage hole. The substrate is often a bar or tube, formed of a sacrificial material. After the turbulation is applied to the substrate, the substrate is inserted into the passage hole. The turbulation material is then fused to the inner surface, using a conventional heating technique. The sacrificial substrate can then be removed from the hole by various techniques. Related articles are also described.
摘要翻译：描述了在通道孔（例如，涡轮机冷却孔）的内表面上提供紊流的方法。首先将该紊乱施加到最终可以插入通道孔中的基底。基板通常是由牺牲材料形成的棒或管。在对基板施加了混浊之后，将基板插入到通孔中。然后使用常规的加热技术将紊乱材料熔合到内表面。然后可以通过各种技术从孔中去除牺牲衬底。还描述了相关文章。

6. 发明授权

US06526756B2 Method and apparatus for enhancing heat transfer in a combustor liner for a gas turbine 有权
公开(公告)号：US06526756B2
公开(公告)日：2003-03-04
申请号：US09783704
申请日：2001-02-14
申请人： Robert Alan Johnson , Anthony Joseph Loprinzo , Ching-Pang Lee , Nesim Abuaf , Wayne Charles Hasz , Harmon Lindsay Morton
发明人： Robert Alan Johnson , Anthony Joseph Loprinzo , Ching-Pang Lee , Nesim Abuaf , Wayne Charles Hasz , Harmon Lindsay Morton
IPC分类号： F02C730
CPC分类号： F23R3/002 , F23D2214/00 , F23R2900/03045 , Y10T29/4932 , Y10T29/49348
摘要： A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

7. 发明授权

US5822853A Method for making cylindrical structures with cooling channels 失效
标题翻译：用于制造具有冷却通道的圆柱形结构的方法
公开(公告)号：US5822853A
公开(公告)日：1998-10-20
申请号：US669069
申请日：1996-06-24
申请人： Ann Melinda Ritter , John Raymond Hughes , Melvin Robert Jackson , Francis Lawrence Kirkpatrick , Francisco Jose Tenreiro Cunha , Nesim Abuaf , Ronald Scott Bunker
发明人： Ann Melinda Ritter , John Raymond Hughes , Melvin Robert Jackson , Francis Lawrence Kirkpatrick , Francisco Jose Tenreiro Cunha , Nesim Abuaf , Ronald Scott Bunker
IPC分类号： F02C7/00 , B22F5/10 , B23K20/00 , B23P15/00 , F23R3/00 , F23R3/42
CPC分类号： F23R3/005 , B22F5/10 , B23P15/00 , B22F2005/103 , B23P2700/13 , F05B2250/231 , Y02T50/675 , Y10T29/49346 , Y10T29/49353
摘要： Methods of making cylindrical structures with cooling channels, such as, for example, combustor/transition pieces for gas turbines having a double wall with a plurality of cooling channels, both axially and, in some cases, circumferential cross-flow passages positioned between the structure's inner member and the outer member to provide cooling air thereto, are disclosed. The cooling channels are formed in the area between the inner member of the structure and the outer member thereof. The passages preferably extend both axially and circumferentially with respect to the direction of flow through the structure. The axial passages extend completely from one end to the other and the circumferential passages extend around the circumference of the structure.
摘要翻译：制造具有冷却通道的圆柱形结构的方法，例如用于燃气轮机的燃烧器/过渡件，其具有带有多个冷却通道的双壁，轴向和在一些情况下位于结构的内部构件和外部构件以提供冷却空气。冷却通道形成在结构的内部构件和其外部构件之间的区域中。通道优选地相对于通过结构的流动方向轴向地和周向地延伸。轴向通道从一端到另一端完全延伸，周向通道围绕结构的圆周延伸。

8. 发明授权

US06183197B2 Airfoil with reduced heat load 有权
标题翻译：减少热负荷的翼型
公开(公告)号：US06183197B2
公开(公告)日：2001-02-06
申请号：US09253367
申请日：1999-02-22
申请人： Ronald Scott Bunker , Nesim Abuaf
发明人： Ronald Scott Bunker , Nesim Abuaf
IPC分类号： F01D508
CPC分类号： F01D5/141 , F05D2260/231 , Y02T50/67 , Y02T50/673 , Y02T50/675 , Y10S415/914
摘要： An airfoil with a reduced heat load for use in either a turbine or a compressor of a gas turbine engine comprises having at least one heat reducing dimple on the body of the airfoil or on the associated endwall of the airfoil. The body of the airfoil is comprised of a leading edge, a trailing edge, a pressure side and a suction side. The length of the heat reducing dimple in the expected direction of hot gas stream flow is at least equal to or greater than the width transverse to such direction. The heat reducing dimple is located on the airfoil or endwall so as to reduce the heat load as the hot gas stream flow passes from the leading edge to the trailing edge.
摘要翻译：具有用于燃气涡轮发动机的涡轮或压缩机中的具有降低的热负荷的翼型件包括在翼型体的主体或翼型的相关端壁上具有至少一个减热凹坑。机翼的主体由前缘，后缘，压力侧和吸力侧构成。热气流期望方向上的减热凹坑的长度至少等于或大于横向于该方向的宽度。减热凹坑位于翼型件或端壁上，以便随着热气流从前缘到后缘流动而减少热负荷。

9. 发明授权

US5933699A Method of making double-walled turbine components from pre-consolidated assemblies 失效
标题翻译：从预固结组件制造双层涡轮机部件的方法
公开(公告)号：US5933699A
公开(公告)日：1999-08-03
申请号：US669070
申请日：1996-06-24
申请人： Ann Melinda Ritter , Melvin Robert Jackson , Nesim Abuaf , Robert Patrick Campbell , Ronald Scott Bunker
发明人： Ann Melinda Ritter , Melvin Robert Jackson , Nesim Abuaf , Robert Patrick Campbell , Ronald Scott Bunker
IPC分类号： F02C7/00 , B21D51/12 , B21D53/84 , B21H1/06 , B23P15/00 , F01D9/02 , F23R3/00 , F23R3/42 , B22F7/02 , B22F7/06
CPC分类号： F01D9/023 , B23P15/00 , F23R3/002 , B21H1/06 , B23P2700/13 , Y02T50/67 , Y02T50/672 , Y02T50/675
摘要： Methods of making gas turbine structures with cooling channels, such as, for example, combustor/transition pieces for gas turbines having a double wall with a plurality of cooling channels, having axially and/or circumferential cross-flow passages positioned between the structure's inner member and the outer member to provide cooling air thereto, are disclosed. A representative method of producing such annular structures having a hot and a cold wall, and joining ribs, for the inner and the outer components of an annulus, such as for jet engine turbine combustors, to net shape as an annular pre-form includes: forming a pre-form assembly including materials for the hot wall, cold wall, and ribs and sacrificial segments for maintaining cooling channels during forming of the pre-assembly and later processing; rolling the pre-form to a required thickness and length as a flat pre-form; hoop-rolling the preform to a required thickness and a required length; welding the assembly; ring rolling to the pre-form to a desired inner diameter; ring-rolling or metal spinning the pre-form to produce the proper wall contour and removing the sacrificial material to open the cooling channels.
摘要翻译：制造具有冷却通道的燃气轮机结构的方法，例如具有带有多个冷却通道的双壁的燃气涡轮机的燃烧器/过渡件，具有位于结构的内部构件之间的轴向和/或周向的横向流动通道和外部构件以提供冷却空气。用于制造具有热壁和冷壁的环形结构的代表性方法，以及用于环形的内部和外部部件（例如用于喷气式发动机涡轮机燃烧器）的连接肋，作为环形预成型体的净形状包括：形成预成型组件，其包括用于热壁，冷壁和肋的材料以及用于在形成预组件和稍后处理期间保持冷却通道的牺牲段; 将预制件滚压成所需的厚度和长度作为平面预制件; 将预制棒环绕到所需的厚度和所需长度; 焊接组件; 环状轧制成预制件至期望的内径; 环形轧制或金属纺丝预成型件以产生适当的壁轮廓并去除牺牲材料以打开冷却通道。

10. 发明授权

US06589600B1 Turbine engine component having enhanced heat transfer characteristics and method for forming same 失效
标题翻译：具有增强的传热特性的涡轮发动机部件及其形成方法
公开(公告)号：US06589600B1
公开(公告)日：2003-07-08
申请号：US09345541
申请日：1999-06-30
申请人： Wayne Charles Hasz , Nesim Abuaf , Robert Alan Johnson , Ching-Pang Lee
发明人： Wayne Charles Hasz , Nesim Abuaf , Robert Alan Johnson , Ching-Pang Lee
IPC分类号： B05D312
CPC分类号： F28F21/089 , B22C9/10 , B22C9/22 , B22D25/02 , F01D5/18 , F01D25/08 , F05D2260/2214 , F23R2900/03045 , F28F13/185 , F28F21/087
摘要： A turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour and improve the heat transfer characteristics of the component. Methods for forming the turbine engine components are also disclosed.
摘要翻译：提供一种涡轮发动机部件，其具有包含有效增加部件的表面积的多个凹部的表面。凹陷通常在轮廓上是凹的并且改善了部件的传热特性。还公开了用于形成涡轮发动机部件的方法。

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