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1. 发明授权

US06846575B2 Article having turbulation and method of providing turbulation on an article 失效
标题翻译：具有在制品上提供紊乱的紊乱和方法的物品
公开(公告)号：US06846575B2
公开(公告)日：2005-01-25
申请号：US10455033
申请日：2003-06-05
申请人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
发明人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
IPC分类号： F01D5/28 , B23K1/00 , B23K1/19 , B23K35/02 , B23K35/22 , B23K37/047 , B32B15/01 , B32B15/16 , C22C19/00 , C22C38/00 , C23C24/10 , C23C26/02 , C23C28/00 , F01D5/08 , F01D5/18 , F01D9/02 , F01D25/12 , F02C7/00 , F02C7/18 , F28F13/12 , F28F13/18 , F28F21/08
CPC分类号： F01D5/187 , B22F2998/00 , B23K35/0233 , B23K35/0244 , B23K35/025 , B23K35/3006 , B23K35/3033 , B23K35/3046 , B23K35/3053 , B23K35/322 , B23K37/047 , B23K2101/001 , B32B15/01 , C21D9/08 , C23C24/10 , C23C26/02 , F01D5/08 , F01D25/12 , F05C2201/0463 , F05C2201/0466 , F05D2230/237 , F05D2240/127 , F05D2260/2212 , F05D2260/22141 , F05D2300/611 , F23R2900/03045 , F28F13/12 , F28F13/185 , F28F21/087 , Y10T29/49337 , Y10T29/49393 , Y10T428/12014 , Y10T428/12063 , Y10T428/12097 , Y10T428/12104 , Y10T428/12389 , Y10T428/12431 , Y10T428/12486 , Y10T428/12931 , Y10T428/12993 , B22F3/22 , B22F5/04
摘要： An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.
摘要翻译：一种制品包括通过诸如钎焊合金的粘结剂粘合到基底表面的紊乱材料。在一个实施方案中，该混浊材料包括具有约125微米至约4000微米范围内的平均粒度的离散金属合金颗粒的颗粒相。其他实施例包括用于施加湍流和用于形成湍流的制品的方法。

2. 发明授权

US06598781B2 Article having turbulation and method of providing turbulation on an article 有权
公开(公告)号：US06598781B2
公开(公告)日：2003-07-29
申请号：US10176782
申请日：2002-06-24
申请人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
发明人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
IPC分类号： C23C2602
CPC分类号： F01D5/187 , B22F2998/00 , B23K35/0233 , B23K35/0244 , B23K35/025 , B23K35/3006 , B23K35/3033 , B23K35/3046 , B23K35/3053 , B23K35/322 , B23K37/047 , B23K2101/001 , B32B15/01 , C21D9/08 , C23C24/10 , C23C26/02 , F01D5/08 , F01D25/12 , F05C2201/0463 , F05C2201/0466 , F05D2230/237 , F05D2240/127 , F05D2260/2212 , F05D2260/22141 , F05D2300/611 , F23R2900/03045 , F28F13/12 , F28F13/185 , F28F21/087 , Y10T29/49337 , Y10T29/49393 , Y10T428/12014 , Y10T428/12063 , Y10T428/12097 , Y10T428/12104 , Y10T428/12389 , Y10T428/12431 , Y10T428/12486 , Y10T428/12931 , Y10T428/12993 , B22F3/22 , B22F5/04
摘要： An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.

3. 发明授权

US06558119B2 Turbine airfoil with separately formed tip and method for manufacture and repair thereof 有权
标题翻译：具有单独成形尖端的涡轮翼型及其制造和修理方法
公开(公告)号：US06558119B2
公开(公告)日：2003-05-06
申请号：US09867213
申请日：2001-05-29
申请人： Ching-Pang Lee , Jonathan James Stow , John Peter Heyward , John Howard Starkweather , Lawrence Joseph Roedl , Joseph Howell Bowden, Jr.
发明人： Ching-Pang Lee , Jonathan James Stow , John Peter Heyward , John Howard Starkweather , Lawrence Joseph Roedl , Joseph Howell Bowden, Jr.
IPC分类号： F04D2958
CPC分类号： B23P6/005 , B23P6/007 , B23P15/04 , F01D5/005 , F01D5/18 , F01D5/20 , F05D2230/23 , F05D2230/80 , F05D2260/201 , F05D2260/202 , Y10T29/49318 , Y10T29/49341
摘要： An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.
摘要翻译：一种用于燃气涡轮发动机的翼型件，所述翼型件具有带有翼型本体的芯体，整体部分高度尖叫尖端以及在所述翼型件本身和所述整体式部分高度拨号器尖端之间的整体式顶盖; 以及一个与部分高度的尖叫声结合的尖叫尖端。一种用于制造和修理翼型的方法。

4. 发明授权

US06329015B1 Method for forming shaped holes 有权
标题翻译：形成孔的方法
公开(公告)号：US06329015B1
公开(公告)日：2001-12-11
申请号：US09576921
申请日：2000-05-23
申请人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
发明人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
IPC分类号： B41N124
CPC分类号： B41C1/141 , B23K26/389 , B23P2700/06 , B24C1/045
摘要： A method of forming a shaped hole in a substrate, including substrates protected by coatings, as is the case where an air-cooled component has a thermal barrier coating for protection from a hostile thermal environment, such as the turbine, combustor and augmentor sections of a gas turbine engine. In particular, cooling holes are formed in an air-cooled component after a ceramic layer has been deposited on the surface of the component without damaging or spalling the ceramic layer. Processing steps generally include forming a hole through the ceramic layer and a substrate protected by the ceramic layer, thereby defining an opening at the surface of the ceramic layer. The diameter of the hole is less than the final size required for the cooling hole. A high-pressure abrasive fluid stream is then directed into the hole to enlarge the cross-section of the hole and impart a noncircular shape to the opening by removing portions of the substrate and ceramic layer without removing the ceramic layer surrounding the resulting noncircular-shaped opening. In a preferred embodiment, the abrasive fluid stream is traversed across the surface of the ceramic through a series of nested patterns that are not concentric with the central axis of the hole. Preferably, the hole acquires the desired noncircular shape in the ceramic layer, but retains a circular shape in the substrate.
摘要翻译：一种在衬底中形成成形孔的方法，包括由涂层保护的衬底，如空气冷却部件具有用于防止恶劣热环境的热障涂层（例如涡轮机，燃烧器和增压器部分）的情况燃气涡轮发动机。特别地，在陶瓷层已经沉积在部件的表面上而不损坏或剥落陶瓷层之后，在空气冷却部件中形成冷却孔。加工步骤通常包括通过陶瓷层形成孔和由陶瓷层保护的衬底，由此在陶瓷层的表面上限定开口。孔的直径小于冷却孔所需的最终尺寸。然后将高压磨料流体引导到孔中以扩大孔的横截面，并通过去除基底和陶瓷层的部分而赋予开口的非圆形形状，而不去除围绕所得非圆形的陶瓷层开放在优选实施例中，磨料流体通过与孔的中心轴线不同心的一系列嵌套图案横穿陶瓷的表面。优选地，该孔在陶瓷层中获得所需的非圆形形状，但在基板中保持圆形。

5. 发明授权

US07900457B2 Method and apparatus to facilitate reducing NOx emissions in turbine engines 有权
标题翻译：有助于减少涡轮发动机中NOx排放的方法和装置
公开(公告)号：US07900457B2
公开(公告)日：2011-03-08
申请号：US11590178
申请日：2006-10-31
申请人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
发明人： David Bruce Patterson , Art Johnson , John Howard Starkweather , Daniel Kirtley , Grzegorz Mlynski
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/06 , Y02T50/675
摘要： A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.
摘要翻译：提供一种用于制造燃气轮机的燃烧器衬套的方法。该方法包括提供包括多个周向延伸的面板的环形壳体，其中多个周向延伸的面板包括位于壳体的上游端的第一面板和位于第一面板的下游和邻近第一面板的第二面板。所述方法还包括在所述第一面板中形成多个初级稀释孔并在所述第二面板中形成多个次级稀释孔，其中所述初级和次级稀释孔构造成将稀释空气排放到所述壳体中。

6. 发明申请

US20120102959A1 SUBSTRATE WITH SHAPED COOLING HOLES AND METHODS OF MANUFACTURE 审中-公开
标题翻译：具有形状冷却孔的衬底及其制造方法
公开(公告)号：US20120102959A1
公开(公告)日：2012-05-03
申请号：US12916099
申请日：2010-10-29
申请人： John Howard STARKWEATHER
发明人： John Howard STARKWEATHER
IPC分类号： F23R3/42 , B23K26/00 , B32B3/10
CPC分类号： F23R3/04 , B23K26/0622 , B23K26/389 , F23M5/08 , F23R2900/00018 , F23R2900/03041 , Y02T50/675 , Y10T428/24273
摘要： A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.
摘要翻译：具有形成在其中的一个或多个形状的排出冷却孔的基板。每个成形的冷却孔具有相对于燃烧器衬套的出口表面成角度的孔。孔的一端是形成在燃烧器衬套的入口表面中的入口。孔的另一端是形成在燃烧器衬套的出口表面中的出口。出口具有仅在一个尺寸上膨胀的成形部分。也是制造成形冷却孔的方法。

7. 发明授权

US5823741A Cooling joint connection for abutting segments in a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机中的邻接段的冷却接头连接
公开(公告)号：US5823741A
公开(公告)日：1998-10-20
申请号：US719666
申请日：1996-09-25
申请人： Daniel Ross Predmore , Iain Robertson Kellock , Victor Hugo Correia , John Howard Starkweather , Dean Thomas Lenahan
发明人： Daniel Ross Predmore , Iain Robertson Kellock , Victor Hugo Correia , John Howard Starkweather , Dean Thomas Lenahan
IPC分类号： F01D11/00 , F01D25/26
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/81 , F23R2900/00012
摘要： A seal joint including a sealing member for sealing segmented components of a gas turbine engine is spaced from the gas path to provide more effective cooling. The segments include radial extension flanges spacing the seal joint from the gas path. Various cooling arrangements are adaptable to the modified segments to provide for open or closed circuit impingement or convection cooling plus film cooling. Excessive thermal gradients are avoided as the entire corner of the segment is evenly cooled. Moreover, air usage at the joint is bounded by seal leakage with no extra dedicated cooling air.
摘要翻译：包括用于密封燃气涡轮发动机的分段部件的密封构件的密封接头与气体路径间隔开以提供更有效的冷却。这些段包括将密封接头与气体路径间隔开的径向延伸凸缘。各种冷却装置适用于经修改的部分，以提供开路或闭路冲击或对流冷却加膜冷却。避免了过度的热梯度，因为片段的整个角均匀冷却。此外，关节处的空气使用受密封泄漏限制，无需额外的专用冷却空气。

8. 发明授权

US06478540B2 Bucket platform cooling scheme and related method 有权
标题翻译：铲斗平台冷却方案及相关方法
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。

9. 发明授权

US06468669B1 Article having turbulation and method of providing turbulation on an article 有权
标题翻译：具有在制品上提供紊乱的紊乱和方法的物品
公开(公告)号：US06468669B1
公开(公告)日：2002-10-22
申请号：US09304276
申请日：1999-05-03
申请人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
发明人： Wayne Charles Hasz , Robert Alan Johnson , Ching-Pang Lee , Mark Gerard Rettig , Nesim Abuaf , John Howard Starkweather
IPC分类号： B32B1516
CPC分类号： F01D5/187 , B22F2998/00 , B23K35/0233 , B23K35/0244 , B23K35/025 , B23K35/3006 , B23K35/3033 , B23K35/3046 , B23K35/3053 , B23K35/322 , B23K37/047 , B23K2101/001 , B32B15/01 , C21D9/08 , C23C24/10 , C23C26/02 , F01D5/08 , F01D25/12 , F05C2201/0463 , F05C2201/0466 , F05D2230/237 , F05D2240/127 , F05D2260/2212 , F05D2260/22141 , F05D2300/611 , F23R2900/03045 , F28F13/12 , F28F13/185 , F28F21/087 , Y10T29/49337 , Y10T29/49393 , Y10T428/12014 , Y10T428/12063 , Y10T428/12097 , Y10T428/12104 , Y10T428/12389 , Y10T428/12431 , Y10T428/12486 , Y10T428/12931 , Y10T428/12993 , B22F3/22 , B22F5/04
摘要： An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.
摘要翻译：一种制品包括通过诸如钎焊合金的粘结剂粘合到基底表面的紊乱材料。在一个实施方案中，该混浊材料包括具有约125微米至约4000微米范围内的平均粒度的离散金属合金颗粒的颗粒相。其他实施例包括用于施加湍流和用于形成湍流的制品的方法。

10. 发明授权

US06422821B1 Method and apparatus for reducing turbine blade tip temperatures 失效
标题翻译：降低涡轮叶片尖端温度的方法和装置
公开(公告)号：US06422821B1
公开(公告)日：2002-07-23
申请号：US09756902
申请日：2001-01-09
申请人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
发明人： Ching-Pang Lee , Chander Prakash , Monty Lee Shelton , John Howard Starkweather , Hardev Singh , Gerard Anthony Rinck
IPC分类号： F01D518
CPC分类号： F01D5/20 , F01D5/186 , F05D2240/121 , F05D2240/303 , F05D2250/70 , F05D2260/202
摘要： A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A notch is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf.
摘要翻译：描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。在翼型件前缘处的第一和第二尖端壁之间限定了切口。第二末端壁的至少一部分被凹入以限定尖端架。

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