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1. 发明授权

US07387488B2 Cooled turbine shroud 有权
标题翻译：冷却涡轮罩
公开(公告)号：US07387488B2
公开(公告)日：2008-06-17
申请号：US11161500
申请日：2005-08-05
申请人： Glenn Herbert Nichols , Kurt Grover Brink , Ching-Pang Lee
发明人： Glenn Herbert Nichols , Kurt Grover Brink , Ching-Pang Lee
IPC分类号： F03B11/00
CPC分类号： F01D9/04 , F01D5/288 , F01D11/08 , F01D11/24 , F01D25/12 , F01D25/246 , F05D2230/90 , F05D2240/11
摘要： A cooled turbine shroud includes an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge, an outwardly-extending forward wall and an outwardly-extending aft wall; opposed first and second sidewalls, wherein the forward and aft walls and the sidewalls define an open shroud plenum; at least one leading edge cooling hole extending from the shroud plenum to the leading edge; and at least one sidewall cooling hole extending from the plenum to one of the sidewalls. The flow path surface is free of cooling holes and may include a protective coating applied thereto.
摘要翻译：冷却的涡轮机护罩包括适于围绕一排旋转涡轮叶片的弧形流动路径表面和相对的内表面; 向前突出部，其限定面向前的前缘，向外延伸的前壁和向外延伸的后壁; 相对的第一和第二侧壁，其中前壁和后壁以及侧壁限定开放的护罩增压室; 至少一个前缘冷却孔从护罩增压室延伸到前缘; 以及至少一个侧壁冷却孔，其从所述增压室延伸到所述侧壁之一。流路表面没有冷却孔，并且可以包括施加到其上的保护涂层。

2. 发明授权

US06612808B2 Article wall with interrupted ribbed heat transfer surface 失效
标题翻译：文章墙具有中断的肋状传热面
公开(公告)号：US06612808B2
公开(公告)日：2003-09-02
申请号：US09997183
申请日：2001-11-29
申请人： Ching-Pang Lee , Glenn Herbert Nichols
发明人： Ching-Pang Lee , Glenn Herbert Nichols
IPC分类号： F01D518
CPC分类号： F28F13/02 , F01D5/187 , F01D25/12 , F05D2260/22141 , F28F1/40 , F28F3/04 , F28F2270/00 , Y02T50/672 , Y02T50/676
摘要： An article, for example a turbine engine component such as a shroud, airfoil, etc., comprises a wall having a first wall surface subject to a first temperature, for example from the flow stream of the engine. The wall includes a second wall surface, substantially opposite the first wall surface, for exposure to a cooling fluid, for example cooling air. The second wall surface includes a plurality of adjacent ribs protruding from the second wall surface to facilitate transfer of heat from the second wall surface. The ribs comprise a plurality of elongated rib portions each spaced apart one from another across a gap between rib portions, the gaps having a gap length in the range of about 0.002-0.05″.
摘要翻译：例如涡轮发动机部件（例如护罩，翼型件等）的物品包括具有经受第一温度的第一壁表面的壁，例如来自发动机的流动流。壁包括基本上与第一壁表面相对的第二壁表面，用于暴露于冷却流体，例如冷却空气。第二壁表面包括从第二壁表面突出的多个相邻肋，以便于从第二壁表面传热。这些肋包括多个细长的肋部，每个细长的肋部分彼此跨越肋部分之间的间隙间隔开，间隙的间隙长度在约0.002-0.05“的范围内。

3. 发明授权

US07438520B2 Thermally compliant turbine shroud mounting assembly 有权
标题翻译：符合标准的涡轮机罩安装组件
公开(公告)号：US07438520B2
公开(公告)日：2008-10-21
申请号：US11161516
申请日：2005-08-06
申请人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
发明人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D11/12 , F01D11/122
摘要： A shroud assembly is provided for a gas turbine engine that has a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes: at least one arcuate shroud segment adapted to surround a row of rotating turbine blades which has an arcuate, axially extending mounting flange; a shroud hanger having an arcuate, axially-extending hook disposed in mating relationship to the mounting flange; and an arcuate C-clip having inner and outer arms overlapping the hook and the mounting flange. The curvatures of the mounting flange and the inner arm of the C-clip are selected so as to define a matched interface therebetween. Their curvatures are substantially greater that the curvature of the hook.
摘要翻译：提供一种用于燃气涡轮发动机的护罩组件，其具有基本上大于其冷组装状态下的热操作状态的温度。所述护罩组件包括：至少一个弧形护罩段，其适于包围一排旋转的涡轮叶片，所述旋转涡轮叶片具有弓形的轴向延伸的安装凸缘; 护罩悬挂器具有与安装凸缘成配合关系设置的弓形的轴向延伸的钩; 以及弓形C形夹具，其内外臂与钩和安装法兰重叠。选择安装法兰和C形夹的内臂的曲率，以便在它们之间限定一个匹配的接口。它们的曲率大大地大于钩的曲率。

4. 发明授权

US07452183B2 Thermally compliant turbine shroud assembly 有权
标题翻译：耐热兼容的涡轮机罩组件
公开(公告)号：US07452183B2
公开(公告)日：2008-11-18
申请号：US11161517
申请日：2005-08-06
申请人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
发明人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
IPC分类号： F01D11/08
CPC分类号： F01D11/005 , F01D25/246
摘要： A shroud assembly is provided for a gas turbine engine having a temperature at a hot operating condition substantially greater than at a cold assembly condition thereof. The shroud assembly includes at least one arcuate shroud segment adapted to surround a row of rotating turbine blades. The shroud segment has an arcuate, axially extending mounting flange. A shroud hanger includes an arcuate, axially-extending hook. A dimension of one of the shroud segments and the shroud hanger are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.
摘要翻译：提供了一种用于燃气涡轮发动机的护罩组件，其具有基本上大于其冷组装状态的热操作状态下的温度。护罩组件包括适于包围一排旋转涡轮叶片的至少一个弓形护罩段。护罩段具有弓形的轴向延伸的安装凸缘。护罩悬挂器包括弓形的轴向延伸的钩。选择护罩段和护罩悬挂器中的一个的尺寸以在热操作条件下产生其间的预选尺寸关系。

5. 发明授权

US07442004B2 Thermally compliant C-clip 有权
标题翻译：耐热兼容的C形夹
公开(公告)号：US07442004B2
公开(公告)日：2008-10-28
申请号：US11161518
申请日：2005-08-06
申请人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
发明人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
IPC分类号： F01D11/08
CPC分类号： F01D9/04 , F05D2230/60 , F05D2240/11 , F05D2260/30 , F05D2260/941
摘要： A C-clip for a gas turbine engine includes an arcuate outer arm having a first radius of curvature; an arcuate, inner arm having a second radius of curvature which is substantially greater than the first radius of curvature; and an arcuate extending flange connecting the outer and inner arms. The flange, the outer arm, and the inner arm collectively define a generally C-shaped cross-section. A shroud assembly includes a shroud segment with a mounting flange, and a shroud hanger with an arcuate hook disposed in mating relationship to the mounting flange. An arcuate C-clip having inner and outer arms overlaps the hook and the mounting flange. The shroud segment and the C-clip are subject to thermal expansion at the hot operating condition. A dimension of one of the shroud segment and the C-clip are selected to produce a preselected dimensional relationship therebetween at the hot operating condition.
摘要翻译：用于燃气涡轮发动机的C形夹包括具有第一曲率半径的弓形外臂; 具有第二曲率半径的弓形内臂，其基本上大于所述第一曲率半径; 以及连接外臂和内臂的弓形延伸法兰。凸缘，外臂和内臂共同地限定了大致C形的横截面。护罩组件包括具有安装凸缘的护罩段和具有与安装法兰配合关系设置的弓形钩的护罩。具有内臂和外臂的弧形C形夹与钩和安装法兰重叠。护罩段和C形夹在热操作条件下经受热膨胀。选择护罩段和C形夹之一的尺寸以在热操作条件下产生预定尺寸关系。

6. 发明授权

US07448846B2 Thermally compliant turbine shroud mounting 有权
标题翻译：耐热兼容的涡轮机护罩安装
公开(公告)号：US07448846B2
公开(公告)日：2008-11-11
申请号：US11161515
申请日：2005-08-06
申请人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
发明人： Michael Anthony Ruthemeyer , Glenn Herbert Nichols , Ching-Pang Lee
IPC分类号： F01D11/08
CPC分类号： F01D11/127 , F01D11/12
摘要： A shroud segment is adapted to surround a row of rotating turbine blades in a gas turbine engine. The shroud segment includes: an arcuate, axially extending first mounting flange having a first radius of curvature, and an arcuate, axially extending first overhang having a second radius of curvature. The overhang is disposed parallel to and radially inboard of the first mounting flange so that a first groove is defined between the first mounting flange and the first overhang. The first and second radii of curvature are substantially different from each other. The shroud segment may attached to a supporting structure or shroud hanger to form a shroud assembly.
摘要翻译：护罩段适于围绕燃气涡轮发动机中的一排旋转涡轮叶片。护罩部分包括：具有第一曲率半径的弓形轴向延伸的第一安装凸缘，以及具有第二曲率半径的弓形的轴向延伸的第一突出部。突出部平行于第一安装凸缘并且径向设置在第一安装凸缘的内侧，使得在第一安装凸缘和第一突出部之间限定第一凹槽。第一和第二曲率半径彼此大不相同。护罩部分可以附接到支撑结构或护罩悬挂器以形成护罩组件。

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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