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1. 发明授权

US06261054B1 Coolable airfoil assembly 有权
标题翻译：可冷却翼型组件
公开(公告)号：US06261054B1
公开(公告)日：2001-07-17
申请号：US09235914
申请日：1999-01-25
申请人： Ronald Scott Bunker , James William Bartos , Nicholas Damlis , Mark Eugene Noe , Steven Douglas Ward
发明人： Ronald Scott Bunker , James William Bartos , Nicholas Damlis , Mark Eugene Noe , Steven Douglas Ward
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2220/20 , F05D2220/31 , F05D2220/32 , F05D2260/201 , F05D2260/232 , F05D2260/2322 , Y02T50/676
摘要： An apparatus and method including a closed-circuit coolable airfoil assembly for use and exposure in a hot fluid flow of a machine portion. The assembly includes a first flange configured to be connected with a casing of the machine portion. A second flange is configured to be connected with the casing. An airfoil is connected with and between the first flange and the second flange, the airfoil including a peripheral portion surrounding a medial portion. At least one channel is disposed in the peripheral portion, the channel extending between the first flange and the second flange and being in flow communication with each. A closed flow path is formed from the casing and through the first flange, the second flange and the channel in which a coolant fluid can pass to cool the airfoil assembly.
摘要翻译：一种装置和方法，包括用于在机器部分的热流体流中使用和暴露的闭路冷却翼型组件。组件包括构造成与机器部分的壳体连接的第一凸缘。第二凸缘被构造成与壳体连接。翼型件与第一凸缘和第二凸缘之间连接并且在第一凸缘和第二凸缘之间，翼型件包括围绕中间部分的周边部分。至少一个通道设置在周边部分中，该通道在第一凸缘和第二凸缘之间延伸并且与每个通道流动连通。从壳体和第一凸缘，第二凸缘和冷却剂流体可以通过的通道形成封闭的流动路径，以冷却翼型组件。

2. 发明申请

US20110008156A1 COMPOSITE TURBINE NOZZLE 有权
标题翻译：复合涡轮喷嘴
公开(公告)号：US20110008156A1
公开(公告)日：2011-01-13
申请号：US12499329
申请日：2009-07-08
申请人： Ian Francis Prentice , Mark Eugene Noe
发明人： Ian Francis Prentice , Mark Eugene Noe
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D9/042 , F01D11/005 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes.
摘要翻译：复合喷嘴段包括在弓形径向外段和内带段之间径向延伸的一个或多个翼型件，其具有围绕中心线轴线弯曲的带状帘布层，外带段的外后缘上的外弦密封线，外侧翼缘沿着外带段的压力和吸力侧边缘。增厚区域在压力和吸力侧边缘处可以是最厚的，并且在外带段的中间附近最薄。加厚的区域从加厚区域的后端朝向外带段的前凸缘逐渐变细。插入层可以设置在加厚区域之间的一些带状层之间，可以分组在一起，或者分散在一些带状层中。插入层可以具有三角形形状。

3. 发明授权

US06821085B2 Turbine engine axially sealing assembly including an axially floating shroud, and assembly method 有权
标题翻译：涡轮发动机轴向密封组件，包括轴向浮动护罩和组装方法
公开(公告)号：US06821085B2
公开(公告)日：2004-11-23
申请号：US10260599
申请日：2002-09-30
申请人： Toby George Darkins, Jr. , Mary Ellen Alford , Mark Eugene Noe
发明人： Toby George Darkins, Jr. , Mary Ellen Alford , Mark Eugene Noe
IPC分类号： F01D1108
CPC分类号： F01D11/08 , F05D2230/642 , F05D2250/41 , F05D2300/603
摘要： A turbine engine axial series of members, axially distinct at least radially outwardly, enables independent axial movement to close gaps therebetween, eliminating need for fluid seals. During engine operation, an axially forward first member surface is movable an axial movement distance to close any gap between the first member and a second member that floats axially independently of adjacent members and that is movable axially responsive to axial force from the first member. Axial movement of the second member toward a third member closes any gap therebetween, the axial length of the gap, prior to engine operation, being substantially no greater than the axial movement distance of the first member.
摘要翻译：涡轮发动机轴向系列的构件至少径向向外轴向不同，能够独立的轴向运动以在其间封闭间隙，消除了对流体密封的需要。在发动机操作期间，轴向前进的第一构件表面可移动轴向移动距离，以封闭第一构件与第二构件之间的任何间隙，第二构件与邻近构件轴向浮动，并且可轴向地响应于来自第一构件的轴向力而可移动。第二构件朝向第三构件的轴向运动封闭它们之间的任何间隙，在发动机操作之前间隙的轴向长度基本上不大于第一构件的轴向移动距离。

4. 发明授权

US06884026B2 Turbine engine shroud assembly including axially floating shroud segment 有权
标题翻译：涡轮发动机罩组件包括轴向浮动的护罩段
公开(公告)号：US06884026B2
公开(公告)日：2005-04-26
申请号：US10260478
申请日：2002-09-30
申请人： Christopher Charles Glynn , Mary Ellen Alford , Mark Eugene Noe , Toby George Darkins, Jr.
发明人： Christopher Charles Glynn , Mary Ellen Alford , Mark Eugene Noe , Toby George Darkins, Jr.
IPC分类号： F01D11/08 , F02C7/20 , F04D29/08 , F04D29/44
CPC分类号： F01D11/08 , F02C7/20 , F05D2230/642 , F05D2240/11 , F05D2250/41 , F05D2300/603
摘要： At least one shroud segment, floating axially independently of adjacent turbine engine shroud assembly members, includes a segment body comprising a radially outer surface and a radially outwardly projecting segment support that includes an axial support wall surface therein. The assembly includes a shroud hanger in axial juxtaposition with the segment support, and at least one axial support projection from the shroud hanger into the segment support at the support wall surface. The support projection supports the shroud segment releasably at the support wall surface sufficiently to enable relative axial movement of the shroud segment on the support projection independently of the shroud hanger and adjacent engine members.
摘要翻译：至少一个护罩段，其轴向独立于相邻的涡轮发动机罩组件构件浮动，包括一段，其包括径向外表面和径向向外突出的段支撑件，其包括其中的轴向支撑壁表面。组件包括与分段支撑件轴向并置的护罩悬挂器，以及从护罩悬挂到支撑壁表面处的段支撑件中的至少一个轴向支撑突起。支撑突出部可释放地支撑在支撑壁表面处的护罩区段，足以使护罩段在支撑突起上的相对轴向运动独立于护罩悬挂器和相邻的发动机构件。

5. 发明授权

US06808363B2 Shroud segment and assembly with circumferential seal at a planar segment surface 有权
标题翻译：护罩段和在平面段表面具有圆周密封的组件
公开(公告)号：US06808363B2
公开(公告)日：2004-10-26
申请号：US10325760
申请日：2002-12-20
申请人： Toby George Darkins, Jr. , Mary Ellen Alford , Mark Eugene Noe
发明人： Toby George Darkins, Jr. , Mary Ellen Alford , Mark Eugene Noe
IPC分类号： F01D1108
CPC分类号： F01D9/02 , F01D11/005
摘要： A turbine engine shroud segment having a body including a circumferentially arcuate radially inner surface defining a circumferential arc and a radially outer surface is provided, at least at one axially spaced apart outer surface edge portion surface, with a surface depression extending circumferentially across the outer edge portion and including a planar seal surface. The planar seal surface is spaced apart radially outwardly from the circumferential arc defining a spaced apart chord of the arc. The planar seal surface is joined with the segment body radially outer surface through an arcuate transition surface. In a circumferential assembly of a plurality of the shroud segments into a turbine engine shroud assembly, at least one of the outer surface edge portions and its respective depression portion and fluid seal surface is distinct axially from an axially juxtaposed engine member by a separation therebetween. A fluid seal member, including a fluid seal surface matched in shape with the planar seal surface of the segment, is retained in juxtaposition for contact with the segment planar seal surface along the separation, for example as a result of pressure loading during engine operation.
摘要翻译：具有本体的涡轮发动机护罩段具有包括限定圆周弧和径向外表面的周向弧形径向内表面的主体，至少在一个轴向间隔开的外表面边缘部分表面处，具有周向延伸穿过外边缘的表面凹陷并且包括平面密封表面。平面密封表面与周向弧线径向向外间隔开，形成间隔开的弧形弦。平面密封表面通过弧形过渡表面与段体径向外表面接合。在多个护罩段的涡轮发动机护罩组件的圆周组件中，外表面边缘部分及其相应的凹陷部分和流体密封表面中的至少一个通过它们之间的间隔与轴向并置的发动机构件轴向分开。流体密封构件包括形状与管段的平面密封表面相匹配的流体密封表面，例如由于在发动机操作期间的压力加载而与分隔件平行的密封表面并列保持并置。

6. 发明授权

US06775985B2 Support assembly for a gas turbine engine combustor 失效
标题翻译：用于燃气涡轮发动机燃烧器的支撑组件
公开(公告)号：US06775985B2
公开(公告)日：2004-08-17
申请号：US10342040
申请日：2003-01-14
申请人： Krista Anne Mitchell , David Edward Bulman , Mark Eugene Noe , Harold Ray Hansel , Christopher Charles Glynn
发明人： Krista Anne Mitchell , David Edward Bulman , Mark Eugene Noe , Harold Ray Hansel , Christopher Charles Glynn
IPC分类号： F02C100
CPC分类号： F23R3/007 , F05B2230/606 , F23R3/50 , F23R3/60 , F23R2900/00014
摘要： A support assembly for a gas turbine engine combustor including an inner liner and an inner casing spaced therefrom, wherein a longitudinal centerline axis extends through the gas turbine engine. The support assembly includes an annular inner support cone located adjacent an aft end of said inner liner, an annular nozzle support connected to the inner support cone, and a plurality of support members connected at a first end to a forward end of the inner liner and connected at a second end to the inner support cone.
摘要翻译：一种用于燃气涡轮发动机燃烧器的支撑组件，包括内衬和与其分开的内壳，其中纵向中心线轴线延伸穿过燃气涡轮发动机。所述支撑组件包括邻近所述内衬的后端定位的环形内支撑锥体，连接到所述内支撑锥体的环形喷嘴支撑件以及在第一端连接到所述内衬垫的前端的多个支撑构件，以及在第二端连接到内支撑锥体。

7. 发明授权

US06554563B2 Tangential flow baffle 有权
公开(公告)号：US06554563B2
公开(公告)日：2003-04-29
申请号：US09928763
申请日：2001-08-13
申请人： Mark Eugene Noe , Toby George Darkins, Jr. , Roger Lee Doughty
发明人： Mark Eugene Noe , Toby George Darkins, Jr. , Roger Lee Doughty
IPC分类号： F01D906
CPC分类号： F01D5/189 , F05D2240/10 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine nozzle baffle includes a plurality of apertures inclined through a shell for discharging a coolant tangentially therefrom. The baffle is disposed inside a nozzle vane and the tangentially discharged coolant flows generally parallel along the inner surface of the vane for convection cooling thereof.

8. 发明授权

US08206096B2 Composite turbine nozzle 有权
标题翻译：复合涡轮喷嘴
公开(公告)号：US08206096B2
公开(公告)日：2012-06-26
申请号：US12499329
申请日：2009-07-08
申请人： Ian Francis Prentice , Mark Eugene Noe
发明人： Ian Francis Prentice , Mark Eugene Noe
IPC分类号： F01D9/04
CPC分类号： F01D5/282 , F01D9/042 , F01D11/005 , F01D25/246 , F05D2300/603 , Y02T50/672
摘要： A composite nozzle segment includes one or more airfoils extending radially between arcuate radially outer and inner band segments having band plies curved about a centerline axis, an outer chordal seal line on an outer aft flange of the outer band segment, and thickened areas in corners of the outer aft flange along pressure and suction side edges of the outer band segment. The thickened areas may be thickest at the pressure and suction side edges and thinnest near a middle of the outer band segment. The thickened areas taper off from an aft end of the thickened area towards a forward flange of the outer band segment. Insert plies may be disposed between some of the band plies within the thickened areas may be grouped together in a discrete group or be interspersed with some of the band plies. The insert plies may have triangular shapes.
摘要翻译：复合喷嘴段包括在弓形径向外段和内带段之间径向延伸的一个或多个翼型件，其具有围绕中心线轴线弯曲的带状帘布层，外带段的外后缘上的外弦密封线，外侧翼缘沿着外带段的压力和吸力侧边缘。增厚区域在压力和吸力侧边缘处可以是最厚的，并且在外带段的中间附近最薄。加厚的区域从加厚区域的后端朝向外带段的前凸缘逐渐变细。插入层可以设置在加厚区域之间的一些带状层之间，可以分组在一起，或者分散在一些带状层中。插入层可以具有三角形形状。

9. 发明申请

US20110271684A1 GAS TURBINE ENGINE COMBUSTOR WITH CMC HEAT SHIELD AND METHODS THEREFOR 有权
标题翻译：燃气涡轮发动机燃烧器与CMC热风及其方法
公开(公告)号：US20110271684A1
公开(公告)日：2011-11-10
申请号：US12776535
申请日：2010-05-10
申请人： Donald Michael CORSMEIER , Mark Eugene Noe , Michael Todd Radwanski , Oliver Roghe , Jessica Licardi Subit , Ming Xie
发明人： Donald Michael CORSMEIER , Mark Eugene Noe , Michael Todd Radwanski , Oliver Roghe , Jessica Licardi Subit , Ming Xie
IPC分类号： F02C3/14 , B23P11/00
CPC分类号： F23R3/42 , F23R3/002 , F23R3/007 , F23R2900/00017 , Y10T29/4932 , Y10T29/49826
摘要： A combustor for a gas turbine engine is disclosed. The combustor is described as comprising a dome plate coupled to a liner thereof, with at least one heat shield comprised of a ceramic matrix composite coupled at the aft end of the dome plate. Also described is a method for assembling a combustor for a gas turbine engine, including releasing a metal alloy heat shield from a dome plate and providing a ceramic matrix composite heat shield as replacement.
摘要翻译：公开了一种用于燃气涡轮发动机的燃烧器。燃烧器被描述为包括联接到其衬垫的圆顶板，至少一个隔热罩包括耦合在圆顶板的后端的陶瓷基体复合体。还描述了一种用于组装用于燃气涡轮发动机的燃烧器的方法，包括从圆顶板释放金属合金隔热罩并提供陶瓷基复合隔热罩作为替代物。

10. 发明授权

US06904757B2 Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor 有权
标题翻译：用于燃气涡轮发动机燃烧器中的陶瓷基体复合衬套前端的安装组件
公开(公告)号：US06904757B2
公开(公告)日：2005-06-14
申请号：US10324871
申请日：2002-12-20
申请人： Krista Anne Mitchell , David Edward Bulman , Mark Eugene Noe , Harold Ray Hansel , Thomas Allen Wells , Christopher Charles Glynn , John David Bibler , Toby George Darkins, Jr. , Joseph John Charneski , Craig Patrick Burns
发明人： Krista Anne Mitchell , David Edward Bulman , Mark Eugene Noe , Harold Ray Hansel , Thomas Allen Wells , Christopher Charles Glynn , John David Bibler , Toby George Darkins, Jr. , Joseph John Charneski , Craig Patrick Burns
IPC分类号： F23R3/00 , F23R3/60 , F02C7/20
CPC分类号： F23R3/007 , F23R3/60
摘要： A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings. In this way, the cowl aft portion and the dome portion are fixedly connected together between the bushing and the nut so that the bushings are able to slide radially through the openings in the liner forward end as the cowl and the dome experience thermal growth greater than the liner.
摘要翻译：一种用于在包括圆顶和整流罩的燃气涡轮发动机的燃烧器中的衬套的前端的安装组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。安装组件包括延伸穿过形成在衬套的前端中的多个周向间隔开的开口中的每一个的销构件，整流罩的后部和圆顶的一部分，每个销构件包括头部其一端。螺母可调节地连接到与头部相对的每个销构件的端部。衬套位于每个销构件的位于头部部分和螺母之间的位置处，其中衬里前端中的开口的尺寸设置成适合围绕衬套。以这种方式，整流罩后部和穹顶部分在衬套和螺母之间固定连接在一起，使得衬套能够径向滑过衬套前端中的开口，因为整流罩和穹顶经历热膨胀大于班轮

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