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1. 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。

2. 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。

3. 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。

4. 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。

5. 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。

6. 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。

7. 发明授权

US07588412B2 Cooled shroud assembly and method of cooling a shroud 有权
标题翻译：冷却罩组件及其冷却方法
公开(公告)号：US07588412B2
公开(公告)日：2009-09-15
申请号：US11161275
申请日：2005-07-28
申请人： Glenn Herbert Nichols , Duane Allan Busch
发明人： Glenn Herbert Nichols , Duane Allan Busch
IPC分类号： F01D9/06
CPC分类号： F01D9/042 , F01D25/12 , Y02T50/673 , Y02T50/675
摘要： A cooled shroud assembly for a gas turbine engine having a longitudinal centerline includes at least one arcuate shroud segment surrounding a row of rotating turbine blades. The shroud segment has a forward flange, an aft flange defining an axially-facing aft edge, and an inwardly-facing flowpath surface, and the shroud segment lacks cooling holes for cooling the aft flange or the aft edge. At least one stationary turbine nozzle is disposed axially next to the shroud segment and includes an airfoil-shaped airfoil and an arcuate outer band disposed at a radially outer end of the airfoil and positioned axially adjacent to the shroud. At least one cooling hole is formed in the outer band in fluid communication with a source of cooling air. The cooling hole is positioned so as to direct a flow of cooling air against the shroud segment.
摘要翻译：用于具有纵向中心线的燃气涡轮发动机的冷却罩组件包括围绕一排旋转涡轮叶片的至少一个弧形护罩段。护罩区段具有前凸缘，后凸缘，其限定面向轴向的后缘，以及面向内的流路表面，并且护罩段缺少用于冷却后翼缘或后缘的冷却孔。至少一个固定涡轮喷嘴轴向地布置在护罩段的旁边，并且包括翼型翼型和设置在翼型件的径向外端处并且轴向相对于护罩定位的弓形外带。至少一个冷却孔形成在外带中，与冷却空气源流体连通。冷却孔定位成将冷却空气流引导到护罩段。

8. 发明授权

US07229246B2 Compliant seal and system and method thereof 有权
标题翻译：符合密封及其系统及方法
公开(公告)号：US07229246B2
公开(公告)日：2007-06-12
申请号：US10955079
申请日：2004-09-30
申请人： Farshad Ghasripoor , Shorya Awtar , Norman Arnold Turnquist , Biao Fang , Carl Anthony Flecker, III , James William Stegmaier , Glenn Herbert Nichols , James Charles Przytulski , Kurt Grover Brink , Richard Cohen Lykins , Jeffrey Reid Thyssen , Mahmut Faruk Aksit
发明人： Farshad Ghasripoor , Shorya Awtar , Norman Arnold Turnquist , Biao Fang , Carl Anthony Flecker, III , James William Stegmaier , Glenn Herbert Nichols , James Charles Przytulski , Kurt Grover Brink , Richard Cohen Lykins , Jeffrey Reid Thyssen , Mahmut Faruk Aksit
IPC分类号： F01D11/20 , F04D29/08
CPC分类号： F04D29/126
摘要： A compliant seal assembly for a rotating machine is provided. The seal assembly includes a static member, a movable member and a biasing member. The static member is rigidly fixed to the machine at its fore and aft ends. The movable portion has a first sealing surface configured to seal against a rotating member and a rear surface, which may be exposed to a fluid pressure to urge the first sealing surface toward a sealing position with the rotating member. The static and the movable members further include sealing surfaces at their fore, aft and end faces to seal against leakage of gas between the static and the movable members. The biasing member is configured to support the movable member on the static member and to urge the movable member away from the sealing position so as to reduce force on the rotating member during contact of the rotating member with the first sealing surface of the movable member.
摘要翻译：提供了一种用于旋转机器的柔性密封组件。密封组件包括静止构件，可移动构件和偏置构件。静态构件在前后刚性地固定在机器上。可移动部分具有被配置为密封旋转构件和后表面的第一密封表面，该表面可暴露于流体压力以将第一密封表面推向与旋转构件的密封位置。静态和可动构件还包括在其前，后和端面处的密封表面，以防止静态和可移动构件之间的气体泄漏。偏置构件构造成将可动构件支撑在静止构件上，并且将可移动构件推离密封位置，以便在旋转构件与可移动构件的第一密封表面接触期间减小旋转构件上的力。

9. 发明授权

US06416278B1 Turbine nozzle segment and method of repairing same 有权
标题翻译：涡轮喷嘴段及其修理方法
公开(公告)号：US06416278B1
公开(公告)日：2002-07-09
申请号：US09713936
申请日：2000-11-16
申请人： James Walter Caddell, Jr. , James Michael Caldwell , Kenneth Morand Lieland , Glenn Herbert Nichols
发明人： James Walter Caddell, Jr. , James Michael Caldwell , Kenneth Morand Lieland , Glenn Herbert Nichols
IPC分类号： F01D900
CPC分类号： B23P6/002 , F01D5/005 , F05D2230/12 , F05D2230/232 , F05D2230/237 , Y02T50/67 , Y10T29/49318 , Y10T29/49721 , Y10T29/49732
摘要： A method for repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands includes separating the inner band from the nozzle segment, and joining the inner band to a newly manufactured replacement casting having an outer band and at least one vane. The replacement casting includes a mounting platform formed on one end of the vane and a boss formed on the mounting platform. A collar is joined to the inner band and has a slot formed therein. The boss is then inserted into the slot, and the mounting platform is received in a recess formed in the inner band. Joining is completed by joining the boss to the collar and the mounting platform to the inner band.
摘要翻译：一种用于修复具有设置在外带和内带之间的至少一个叶片的涡轮喷嘴段的方法，包括将内带与喷嘴段分离，并将内带连接到具有外带和至少一个叶片的新制造的替换铸件。替代铸件包括形成在叶片的一端上的安装平台和形成在安装平台上的凸台。轴环连接到内带并且在其中形成有槽。然后将凸台插入槽中，并且安装平台被容纳在形成在内带中的凹部中。连接是通过将老板连接到领带和安装平台到内带来完成的。

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