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公开(公告)号：US06733229B2
公开(公告)日：2004-05-11
申请号：US10092572
申请日：2002-03-08
IPC分类号： F01D906
CPC分类号： F01D5/189 , F01D9/065 , F05D2260/201
摘要： The invention comprises a metering plate which is assembled to an impingement insert for use in the nozzle of a gas turbine. The metering plate can have one or more metering holes and is used to balance the cooling flow within the nozzle. A metering plate with multiple holes reduces static pressure variations which result from the cooling airflow through the metering plate. The metering plate can be assembled to the insert before or after the insert is inserted into the nozzle.
摘要翻译： 本发明包括计量板，其被组装到用于燃气轮机的喷嘴中的冲击插入件。 计量板可以具有一个或多个计量孔，并用于平衡喷嘴内的冷却流。 具有多个孔的计量板减少了由通过计量板的冷却气流引起的静压变化。 在将插入件插入喷嘴之前或之后，计量盘可以组装到插入件上。
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公开(公告)号：US06478540B2
公开(公告)日：2002-11-12
申请号：US09739445
申请日：2000-12-19
申请人： Nesim Abuaf , Kevin Joseph Barb , Sanjay Chopra , David Max Kercher , Iain Robertson Kellock , Dean Thomas Lenahan , Sankar Nellian , John Howard Starkweather , Douglas Arthur Lupe
发明人： Nesim Abuaf , Kevin Joseph Barb , Sanjay Chopra , David Max Kercher , Iain Robertson Kellock , Dean Thomas Lenahan , Sankar Nellian , John Howard Starkweather , Douglas Arthur Lupe
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/2214
摘要： A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.
摘要翻译： 涡轮机桶包括从平台延伸的具有高低压侧的翼型件; 轮安装部; 位于所述平台和所述车轮安装部之间的中空柄部，所述平台具有下表面。 冲击冷却板位于空心柄部分中，与下表面间隔开，并且冲击板在其中形成有多个冲击冷却孔。
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3.发明申请Method for providing turbulation on the inner surface of holes in an article, and related articles 审中-公开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。
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4.发明授权Method for providing turbulation on the inner surface of holes in an article, and related articles 有权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
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。
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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.
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公开(公告)号：US5980209A
公开(公告)日：1999-11-09
申请号：US884091
申请日：1997-06-27
CPC分类号： F01D5/141 , F01D5/187 , Y10S416/05
摘要： A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.
摘要翻译： 第一级涡轮机叶片包括具有根据表I的轮廓的翼型件。翼型件具有多个冷却空气通道，该冷却空气通道从翼部的根部直线延伸到翼型部分。 叶片包括具有一对空腔的柄，所述一对空腔通过叶片燕尾榫与在车轮空间中的增压室连通，用于向翼型中的通道供应冷却空气。 翼型件中的冷却通道终止在尖端部分处的凹部中，该凹部具有与翼型件的后缘相邻并且沿着吸力侧的开口，以使冷却空气能够排出到翼型的低压侧上的热气流中。 大部分冷却通道是混浊的。 这些通道中的某些通道排列成与翼型的压力和吸力侧相邻的排。
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7.发明授权Turbine engine component having enhanced heat transfer characteristics and method for forming same 失效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
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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公开(公告)号：US06546730B2
公开(公告)日：2003-04-15
申请号：US10166748
申请日：2002-06-12
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： F02C300
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.
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9.发明授权Method for forming a turbine engine component having enhanced heat transfer characteristics 失效用于形成具有增强的传热特性的涡轮发动机部件的方法公开(公告)号：US06505673B1
公开(公告)日：2003-01-14
申请号：US09473295
申请日：1999-12-28
IPC分类号： B22C702
CPC分类号： B22C9/10 , B22C7/06 , B22C23/00 , B23K35/3033
摘要： A method of forming a turbine engine component, includes providing a mold having a textured region, pouring a molten alloy into the mold, and cooling the molten alloy to form a turbine engine component, wherein the turbine engine component has an enhanced surface area region corresponding to the textured region of the mold, the enhanced surface area region comprising randomly arranged bumps.
摘要翻译： 一种形成涡轮发动机部件的方法，包括提供具有纹理区域的模具，将熔融合金浇注到模具中，以及冷却熔融合金以形成涡轮发动机部件，其中涡轮发动机部件具有相应的增强的表面积区域 到模具的纹理区域，增强的表面积区域包括随机排列的凸块。
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10.发明授权Modification and repair of film cooling holes in gas turbine engine components 失效燃气轮机发动机部件中薄膜冷却孔的修改和修理公开(公告)号：US06243948B1
公开(公告)日：2001-06-12
申请号：US09443132
申请日：1999-11-18
申请人： Ching-Pang Lee , Robert A. Johnson , Nesim Abuaf
发明人： Ching-Pang Lee , Robert A. Johnson , Nesim Abuaf
IPC分类号： B23P1500
CPC分类号： F01D5/186 , B23K26/389 , B23P6/002 , B23P2700/06 , F01D5/005 , F05D2230/10 , F05D2230/80 , Y02T50/67 , Y02T50/676 , Y10T29/49318 , Y10T29/49341 , Y10T29/49725 , Y10T29/49726
摘要： A method for modifying cooling holes in a gas turbine engine film-cooled component by machining cooling hole outlets to enlarge the outlets and remove any portion of the cooling hole walls which might exhibit cracks.
摘要翻译： 一种用于通过加工冷却孔出口来改变燃气涡轮发动机膜冷却部件中的冷却孔的方法，以扩大出口并去除可能发生裂纹的冷却孔壁的任何部分。
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