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1. 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。

2. 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。

3. 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。

4. 发明授权

US06733235B2 Shroud segment and assembly for a turbine engine 有权
标题翻译：用于涡轮发动机的护罩段和组件
公开(公告)号：US06733235B2
公开(公告)日：2004-05-11
申请号：US10109014
申请日：2002-03-28
申请人： Mary Ellen Alford , Mark Eugene Noe , Toby George Darkins, Jr. , Madeleine Elise Fessler
发明人： Mary Ellen Alford , Mark Eugene Noe , Toby George Darkins, Jr. , Madeleine Elise Fessler
IPC分类号： F01D1108
CPC分类号： F01D25/246 , F01D11/08 , Y10T29/49323
摘要： A turbine engine shroud segment comprises a body including a radially outer surface having axially and circumferentially spaced apart edge surfaces. The segment includes a projection integral with and projecting generally radially outwardly from the body, and positioned at a generally midway surface portion between the axially spaced apart edge surfaces. The projection comprises a head and a transition portion with a cross section smaller than that of the head and integral with and between the head and the body. In a turbine engine shroud assembly, a plurality of such shroud segments are assembled circumferentially with a shroud hanger carrying the projection in a hanger cavity through end portions of radially inner opposed hook members that register with the projection at the transition portion.
摘要翻译：涡轮发动机护罩段包括主体，该主体包括具有轴向和周向间隔开的边缘表面的径向外表面。该段包括与主体一体并且大致径向向外突出并且位于轴向间隔开的边缘表面之间的大致中间表面部分处的突出部。突起包括头部和过渡部分，其横截面小于头部的横截面，并与头部和主体成一体。在涡轮发动机护罩组件中，多个这样的护罩区段与护罩悬挂器组装在一起，护罩悬挂器通过在过渡部分处与突起对准的径向内部相对的钩构件的端部将悬臂承载在衣架空腔中。

5. 发明授权

US06702550B2 Turbine shroud segment and shroud assembly 有权
标题翻译：涡轮护罩段和护罩组件
公开(公告)号：US06702550B2
公开(公告)日：2004-03-09
申请号：US10050451
申请日：2002-01-16
申请人： Toby George Darkins, Jr. , Mary Ellen Alford , Christopher Charles Glynn
发明人： Toby George Darkins, Jr. , Mary Ellen Alford , Christopher Charles Glynn
IPC分类号： F01D1108
CPC分类号： F01D11/08 , F01D9/04 , F01D11/24 , F01D25/12
摘要： A turbine engine shroud segment, preferably a low ductility material, for example a ceramic matrix composite, comprises a segment body extending between body circumferential ends. The body includes a body radially inner surface arcuate at least circumferentially, and a body radially outer surface from which a plurality of hooks extend generally radially outwardly. Each hook comprises a generally radially outwardly extending hook arm with a generally axially extending hook end having a generally radially inner surface in spaced apart juxtaposition with a portion of the body radially outer surface. Such body outer surface includes at least two body contact surfaces each matched in shape and in juxtaposition at least at body circumferential ends with a cooperating hanger contact surface. The radially inner surface of each hook end includes a hook end contact surface matched in shape with a cooperating hanger contact surface at least in a circumferential middle portion of such surface. In a turbine engine shroud assembly, a plurality of such shroud segments are assembled circumferentially with a shroud hanger including at least one hanger foot assembled within and between the segment hooks. The hanger foot includes a plurality of spaced apart hanger foot contact surfaces cooperating in juxtaposition with the contact surfaces of the shroud segment body radially outer surface and the hook end radially inner surfaces. The various contact surfaces cooperating in juxtaposition are matched in shape each to define a fluid choke therebetween.
摘要翻译：涡轮发动机护罩段，优选低延展性材料，例如陶瓷基质复合材料，包括在主体周向端部之间延伸的段体。主体包括至少周向弧形的主体径向内表面，以及主体径向外表面，多个钩从该径向外表面大致径向向外延伸。每个钩包括大致径向向外延伸的钩臂，具有大致轴向延伸的钩端，其具有与主体径向外表面的一部分间隔开并置的大致径向内表面。这种主体外表面包括至少两个身体接触表面，每个至少两个身体接触表面的形状和形状至少在身体周向端部处并置，并具有配合的衣架接触表面。每个钩端的径向内表面包括至少在该表面的周向中间部分中与配合的衣架接触面匹配的钩端接触表面。在涡轮发动机护罩组件中，多个这样的护罩段与护罩悬挂器圆周地组装，护罩悬挂器包括组装在段钩内部和之间的至少一个衣架脚。衣架脚包括多个间隔开的衣架脚接触表面，其与护罩段主体的径向外表面和钩端径向内表面的接触表面并置配合。并列配合的各个接触表面的形状各自在其间形成流体扼流圈。

6. 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

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

US06895761B2 Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor 有权
标题翻译：用于燃气轮机发动机燃烧器中的陶瓷基体复合衬套的后端的安装组件
公开(公告)号：US06895761B2
公开(公告)日：2005-05-24
申请号：US10326209
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： F23R3/60 , F05B2230/606 , F23R3/007
摘要： A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, 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 in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.
摘要翻译：包括支撑构件的燃气涡轮发动机燃烧器的衬套的后端的安装组件，其中纵向中心线轴线延伸穿过燃气涡轮发动机。安装组件包括销构件，其延伸穿过用于燃烧器的支撑构件的一部分中的多个周向间隔开的开口中的每一个并且形成在衬套的后端中的多个部分开口，每个销构件包括在其一端的头部，以及位于支撑构件中的每个开口内的装置，以便将销构件保持在其中。当支撑构件经历大于衬套的热生长时，销构件和支撑构件能够相对于衬垫后端部径向和/或轴向地滑动。

9. 发明授权

US06884030B2 Methods and apparatus for securing multi-piece nozzle assemblies 有权
标题翻译：用于固定多件式喷嘴组件的方法和装置
公开(公告)号：US06884030B2
公开(公告)日：2005-04-26
申请号：US10325085
申请日：2002-12-20
申请人： Toby George Darkins, Jr. , Daniel Gene Dunn , Christopher Grace , Gregory Scot Corman , Mark Stewart Schroder
发明人： Toby George Darkins, Jr. , Daniel Gene Dunn , Christopher Grace , Gregory Scot Corman , Mark Stewart Schroder
IPC分类号： F01D9/04
CPC分类号： F01D9/042 , F05B2260/301 , F05D2240/10 , Y10T29/49323
摘要： A method for securing a nozzle for a turbine is provided. The nozzle includes an airfoil having a suction side and a pressure side connected at a leading edge and a trailing edge such that a cooling cavity is defined within the airfoil, the airfoil extending between an inner band and an outer band. The method includes extending at least one member through the airfoil, and at least one of the inner band and the outer band. The method further includes securing the nozzle assembly in position with at least one fastener such that the at least one member is coupled adjacent to at least one of the inner band and the outer band.
摘要翻译：提供一种用于固定涡轮喷嘴的方法。喷嘴包括具有吸入侧和连接在前缘和后缘处的压力侧的翼型，使得在翼型内限定冷却腔，翼型件在内带和外带之间延伸。该方法包括使至少一个构件延伸穿过翼型，以及内带和外带中的至少一个。该方法还包括用至少一个紧固件固定喷嘴组件就位，使得至少一个构件与内带和外带中的至少一个相邻地连接。

10. 发明授权

US08876481B2 Turbine airfoil component assembly for use in a gas turbine engine and methods for fabricating same 有权
标题翻译：用于燃气涡轮发动机的涡轮机翼部件组件及其制造方法
公开(公告)号：US08876481B2
公开(公告)日：2014-11-04
申请号：US12984836
申请日：2011-01-05
申请人： Shyh-Chin Huang , Frederic Joseph Klug , Robert John Zabala , Andrea Jeanne Howard , Toby George Darkins, Jr.
发明人： Shyh-Chin Huang , Frederic Joseph Klug , Robert John Zabala , Andrea Jeanne Howard , Toby George Darkins, Jr.
IPC分类号： F01D5/30 , F01D5/28
CPC分类号： F01D5/3007 , C04B41/009 , C04B41/52 , C04B41/89 , F01D5/282 , F01D5/288 , F01D5/30 , F01D5/3092 , F05D2300/6033 , Y02T50/672 , Y10T29/49229 , Y10T29/49337 , Y10T29/49885 , C04B35/565 , C04B35/806 , C04B41/5096 , C04B41/5071 , C04B41/522 , C04B41/5059 , C04B41/5024 , C04B41/5031 , C04B41/5042 , C04B41/5044 , C04B41/5064 , C04B41/5068 , C04B41/5045 , C04B41/5032
摘要： A turbine airfoil component assembly for use with a turbine engine including a attachment assembly having an inner surface defining a cavity. The attachment assembly includes a metal alloy substrate. An airfoil assembly is at least partially positioned within the attachment assembly and extends outwardly from the attachment assembly. The airfoil assembly includes a ceramic matrix composite (CMC) substrate. A reaction barrier coating is disposed over at least a portion of the airfoil assembly. The reaction barrier coating is positioned between the attachment assembly and the airfoil assembly.
摘要翻译：一种与涡轮发动机一起使用的涡轮机翼部件组件，其包括具有限定腔的内表面的附接组件。附接组件包括金属合金基板。翼型组件至少部分地定位在附接组件内并从附接组件向外延伸。翼型组件包括陶瓷基复合材料（CMC）基材。反应阻挡涂层设置在翼型组件的至少一部分上。反应阻挡涂层定位在附接组件和翼型组件之间。

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