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1. 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。

2. 发明授权

US06595749B2 Turbine airfoil and method for manufacture and repair thereof 有权
公开(公告)号：US06595749B2
公开(公告)日：2003-07-22
申请号：US09940812
申请日：2001-08-28
申请人： Ching-Pang Lee , Lawrence Joseph Roedl , Jonathan James Stow
发明人： Ching-Pang Lee , Lawrence Joseph Roedl , Jonathan James Stow
IPC分类号： F01D518
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 defining a tip shelf, 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.

3. 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。

4. 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.

5. 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。

6. 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。

7. 发明授权

US09630277B2 Airfoil having built-up surface with embedded cooling passage 有权
公开(公告)号：US09630277B2
公开(公告)日：2017-04-25
申请号：US12723880
申请日：2010-03-15
申请人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
发明人： Ching-Pang Lee , Mrinal Munshi , Gm S. Azad , Jae Y. Um
IPC分类号： F02C7/12 , B23P6/00 , F01D5/00 , F01D5/14 , F01D5/18
CPC分类号： B23P6/007 , F01D5/005 , F01D5/145 , F01D5/186 , F05D2230/30 , F05D2230/80 , F05D2240/81 , Y10T29/49318
摘要： A component in a gas turbine engine includes an airfoil extending radially outwardly from a platform associated with the airfoil. The airfoil includes opposed pressure and suction sidewalls, which converge at a first location defined at a leading edge of the airfoil and at a second location defined at a trailing edge of the airfoil opposed from the leading edge. The component includes a built-up surface adjacent to the leading edge at an intersection between the pressure sidewall and the platform, and at least one cooling passage at least partially within the built-up surface at the intersection between the pressure sidewall and the platform. The at least one cooling passage is in fluid communication with a main cooling channel within the airfoil and has an outlet at the platform for providing cooling fluid directly from the main cooling channel to the platform.

8. 发明授权

US09347324B2 Turbine airfoil vane with an impingement insert having a plurality of impingement nozzles 有权
标题翻译：具有冲击插入件的涡轮机翼型叶片具有多个冲击喷嘴
公开(公告)号：US09347324B2
公开(公告)日：2016-05-24
申请号：US14133773
申请日：2013-12-19
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/188 , F01D9/04 , F05D2210/33 , F05D2240/12 , F05D2240/127 , F05D2260/2212
摘要： A turbine vane includes a generally elongated hollow airfoil and a cooling system. The cooling system is positioned within the airfoil and includes a cooling chamber and an impingement insert positioned in the cooling chamber. The impingement insert and an inner surface of an outer wall of the airfoil define a cooling channel therebetween. The impingement insert includes a plurality of impingement nozzles extending toward the inner surface of the outer wall and a plurality of impingement orifices. At least one of the impingement orifices is arranged in a non-aligned pattern with respect to at least one adjacent impingement orifice such that cooling fluid passing out of the at least one impingement orifice does not directly flow into a centerline of a cooling fluid flowpath of cooling fluid passing out of the at least one adjacent impingement orifice.
摘要翻译：涡轮叶片包括大致细长的中空翼型件和冷却系统。冷却系统定位在翼型内，并且包括冷却室和位于冷却室中的冲击插入件。冲击插入件和翼型件的外壁的内表面在它们之间限定冷却通道。冲击插入件包括朝向外壁的内表面延伸的多个冲击喷嘴和多个冲击孔。冲击孔中的至少一个相对于至少一个相邻的冲击孔布置成非对准图案，使得流出至少一个冲击孔的冷却流体不直接流入冷却流体流动路径的中心线从至少一个相邻的冲击孔流出的冷却流体。

9. 发明授权

US09206904B2 Seal including flexible seal strips 有权
标题翻译：密封包括柔性密封条
公开(公告)号：US09206904B2
公开(公告)日：2015-12-08
申请号：US12832141
申请日：2010-07-08
申请人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
发明人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
IPC分类号： F16J15/32 , F01D11/02
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译：一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。密封构件包括多个柔性密封条。每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的轴。密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

10. 发明授权

US09133721B2 Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine 有权
标题翻译：涡轮转换部件由用于燃气涡轮发动机的两段风冷多层外板形成
公开(公告)号：US09133721B2
公开(公告)日：2015-09-15
申请号：US12945948
申请日：2010-11-15
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： F23R3/46 , F01D9/02 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

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