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1. 发明授权

EP1431664B1 MOUNTING ASSEMBLY FOR THE AFT END OF A CERAMIC MATRIX COMPOSITE LINER IN A GAS TURBINE ENGINE COMBUSTOR 有权
标题翻译： ASSEMBLY燃烧室的燃气轮机的陶瓷基复合材料的壁的后边缘的
公开(公告)号：EP1431664B1
公开(公告)日：2011-10-05
申请号：EP03256559.0
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Mitchell, Krista Anne , Noe, Mark Eugene , Wells, Thomas Allen , Bulman, David Edward , Hansel, Harold Ray , Glynn, Christopher Charles , Bibler, John David , Charneski, Joseph John , Darkins, Jr., Toby George , Burns, Craig Patrick
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007

2. 发明授权

EP1350927B1 Shroud segment, manufacturing method for a shroud segment, as well as shroud assembly for a turbine engine 有权
标题翻译：护罩区段，一个护罩区段和罩组件用于涡轮发动机的制造方法
公开(公告)号：EP1350927B1
公开(公告)日：2007-05-30
申请号：EP03250499.5
申请日：2003-01-28
申请人： GENERAL ELECTRIC COMPANY
发明人： Alford, Mary Ellen , Noe, Mark Eugene , Darkins, Toby George Jr. , Fessler, Madeleine Elise
IPC分类号： F01D25/24 , F01D11/08
CPC分类号： F01D25/246 , F01D11/08 , Y10T29/49323

3. 发明授权

EP1085170B1 Turbine airfoil 有权
标题翻译：涡轮机翼
公开(公告)号：EP1085170B1
公开(公告)日：2007-01-03
申请号：EP00305984.7
申请日：2000-07-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Darkins, Toby George, Jr. , Noe, Mark Eugene , Carper, Douglas Melton
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/18 , F01D5/147 , F05D2240/80 , F05D2300/21 , F05D2300/603

4. 发明公开

EP1350927A2 Shroud segment, manufacturing method for a shroud segment, as well as shroud assembly for a turbine engine 有权
标题翻译： MantelBeckerfenreneines，MantelBrands
公开(公告)号：EP1350927A2
公开(公告)日：2003-10-08
申请号：EP03250499.5
申请日：2003-01-28
申请人： GENERAL ELECTRIC COMPANY
发明人： Alford, Mary Ellen , Noe, Mark Eugene , Darkins, Toby George Jr. , Fessler, Madeleine Elise
IPC分类号： F01D25/24 , F01D11/08
CPC分类号： F01D25/246 , F01D11/08 , Y10T29/49323
摘要： A turbine engine shroud segment (10) comprises a segment body (12) including a radially inner surface (22) arcuate at least circumferentially, a radially outer surface (24), and a plurality of axially and circumferentially spaced apart edge surfaces (26,27/28) connected with and between the inner (22) and outer (24) surfaces. For carrying the segment body (12), the segment (10) includes a projection (14), integral with and projecting generally radially outwardly from the body (12). The projection (14) comprises a projection head (30) spaced apart from the body radially outer surface (24) and a projection transition portion (32), having a transition surface (34), integral with both the projection head (30) and the body radially outer surface (24). In a turbine engine shroud assembly, a plurality of such shroud segments (10) are assembled circumferentially (16) with a shroud hanger (40) that carries the segments (10) in a hanger cavity (46). The cavity (46) is defined at least in part by radially inner opposed hook members (48) each including an end portion (50) that registers with and carries the shroud segment (10) at the projection transition surface (34).
摘要翻译：涡轮发动机护罩区段（10）包括段主体（12），其包括至少周向弧形的径向内表面（22），径向外表面（24）和多个沿轴向和周向间隔开的边缘表面（26， 27/28）与内（22）和外（24）表面连接并在其之间。为了承载分段体（12），分段（10）包括与主体（12）一体并大致径向向外突出的突出部（14）。突起（14）包括与主体径向外表面（24）间隔开的突出头（30）和具有过渡表面（34）的突出过渡部分（32），该过渡表面与突出头（30）和身体径向外表面（24）。在涡轮发动机护罩组件中，多个这样的护罩区段（10）沿圆周（16）与带有悬挂器腔（46）中的段（10）的护罩悬挂器（40）组装。空腔（46）至少部分地由径向内部相对的钩构件（48）限定，每个钩构件（48）包括在所述突出过渡表面（34）处与护罩区段（10）对准并且承载护罩区段（10）的端部（50）。

5. 发明授权

EP1431665B1 Gas turbine engine combustor with a mounting assembly for the forward end of a ceramic matrix composite liner 有权
标题翻译：一个燃气轮机的燃烧器具有用于由陶瓷基体复合材料制成的壁的前边缘的安装装置
公开(公告)号：EP1431665B1
公开(公告)日：2017-03-15
申请号：EP03256565.7
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Mitchell, Krista Anne , Bulman, David Edward , Noe, Mark Eugene , Hansel, Harold Ray , Wells, Thomas Allen , Glynn, Christopher Charles , Bibler, John David , Darkins, Toby George, Jr. , Charneski, Joseph John , Burns, Craig Patrick
IPC分类号： F23R3/60
CPC分类号： F23R3/007 , F23R3/60

6. 发明公开

EP1431518A3 Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments 审中-公开
标题翻译： Mantelringsegmentanordnung einer Gasturbine mit einem Dichtungselement zwischen jeden Segment
公开(公告)号：EP1431518A3
公开(公告)日：2006-08-23
申请号：EP03256564.0
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Alford, Mary Ellen , Noe, Mark Eugene , Darkins, Toby George, Jr.
IPC分类号： F01D11/00 , F01D9/04
CPC分类号： F01D11/005 , F01D9/04 , F05C2203/0839 , F05D2240/11 , F05D2250/131 , F05D2300/21 , F05D2300/2261 , F05D2300/2283 , F05D2300/50 , F05D2300/603
摘要： A turbine engine shroud segment (12) is provided with a radially outer surface (24) including a pair of spaced apart, opposed first and second edge portion surface depressions (28,30), for example spaced circumferentially (16), having a seal surface (40) shaped to receive, in a surface depression (36) formed between assembled adjacent segments (12,14) in a shroud assembly (10), or axially (18) assembled adjacent segments (12,14) and engine members, a radially outer fluid seal member (44). The depression portions (28,30) of a shroud segment are joined with the radially outer surface (24) of the shroud segment (12/14) through an arcuate transition surface (42). Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions (28,30) are provided with a first shape and the fluid seal member (44), disposed at the depression (28,30), is provided with a surface (46) of a second shape matched in shape with the first shape.
摘要翻译：涡轮发动机护罩区段（12）设置有径向外表面（24），该径向外表面（24）包括一对间隔开的相对的第一和第二边缘部分表面凹陷（28,30），例如周向隔开（16），具有密封表面（40）成形为在形成在护罩组件（10）中的组装的相邻节段（12,14）或轴向（18）组装的相邻节段（12,14）和发动机构件之间的表面凹陷（36）中，径向外部流体密封构件（44）。护罩段的凹陷部分（28,30）通过弧形过渡表面（42）与护罩段（12/14）的径向外表面（24）连接。在护罩材料中的发动机操作期间产生的应力减小，使得可以实际使用低延展性材料，例如陶瓷基体复合材料。边缘部分表面凹陷（28,30）设置有第一形状，并且设置在凹部（28,30）处的流体密封构件（44）设置有形状匹配的第二形状的表面（46）与第一个形状。

7. 发明公开

EP1431515A3 Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface 审中-公开
标题翻译：一个燃气涡轮机的护罩段和上段的平坦表面与密封构件的系统
公开(公告)号：EP1431515A3
公开(公告)日：2006-08-23
申请号：EP03256566.5
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Darkin, Jr., Toby George , Alford, Mary Ellen , Noe, Mark Eugene
IPC分类号： F01D11/00 , F01D9/04
CPC分类号： F01D9/02 , F01D11/005
摘要： A turbine engine shroud segment (14) having a body (22) including a circumferentially (16) arcuate radially inner surface (26) defining a circumferential arc and a radially outer surface (24) is provided, at least at one axially (18) spaced apart outer surface edge portion surface (30/32), with a surface depression (36/38) extending circumferentially (16) across the outer edge portion (30/32) and including a planar seal surface (40). The planar seal surface (40) is spaced apart radially (20) outwardly from the circumferential arc (26) defining a spaced apart chord (40) of the arc. The planar seal surface (40) is joined with the segment body radially outer surface (24) through an arcuate transition surface (42). In a circumferential (16) assembly of a plurality of the shroud segments (12,14) into a turbine engine shroud assembly (10), at least one of the outer surface edge portions (30/32) and its respective depression portion (36/38) and fluid seal surface (40) is distinct axially (18) from an axially (18) juxtaposed engine member (48) by a separation (46) therebetween. A fluid seal member (44), including a fluid seal surface (50) matched in shape with the planar seal surface (40) of the segment (12/14), is retained in juxtaposition for contact with the segment planar seal surface (40) along the separation (46), for example as a result of pressure loading during engine operation.

8. 发明公开

EP1431664A3 Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor 有权
标题翻译：安装壁的在燃气涡轮机的燃烧器由陶瓷基体复合材料的后缘
公开(公告)号：EP1431664A3
公开(公告)日：2006-01-18
申请号：EP03256559.0
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Mitchell, Krista Anne , Noe, Mark Eugene , Wells, Thomas Allen , Bulman, David Edward , Hansel, Harold Ray , Glynn, Christopher Charles , Bibler, John David , Charneski, Joseph John , Darkins, Toby George Jr. , Burns, Craig Patrick
IPC分类号： F23R3/60
CPC分类号： F23R3/60 , F05B2230/606 , F23R3/007
摘要： A mounting assembly (36) for an aft end (38) of a liner of a gas turbine engine combustor includes a support member (40). The mounting assembly (36) includes a pin member (46) extending through each one of a plurality of circumferentially spaced openings (42) in a portion of the support member (40) for the combustor and into a plurality of partial openings (44) formed in the aft end (38) of the liner, with each pin member (46) including a head portion (48) at one end thereof, and a device (50) positioned within each opening (42) in the support member (40) so as to retain the pin members (42) therein. The pin members (42) and the support member (40) are able to slide radially and/or axially with respect to the liner aft end (38) as the support member (40) experiences thermal growth greater than the liner.

9. 发明公开

EP1431515A2 Turbine engine shroud segment and assembly with circumferential seal on a planar segment surface 审中-公开
标题翻译：一个燃气涡轮机的护罩段和上段的平坦表面与密封构件的系统
公开(公告)号：EP1431515A2
公开(公告)日：2004-06-23
申请号：EP03256566.5
申请日：2003-10-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Darkin, Jr., Toby George , Alford, Mary Ellen , Noe, Mark Eugene
IPC分类号： F01D9/00 , F01D9/02 , F01D11/00
CPC分类号： F01D9/02 , F01D11/005
摘要： A turbine engine shroud segment (14) having a body (22) including a circumferentially (16) arcuate radially inner surface (26) defining a circumferential arc and a radially outer surface (24) is provided, at least at one axially (18) spaced apart outer surface edge portion surface (30/32), with a surface depression (36/38) extending circumferentially (16) across the outer edge portion (30/32) and including a planar seal surface (40). The planar seal surface (40) is spaced apart radially (20) outwardly from the circumferential arc (26) defining a spaced apart chord (40) of the arc. The planar seal surface (40) is joined with the segment body radially outer surface (24) through an arcuate transition surface (42). In a circumferential (16) assembly of a plurality of the shroud segments (12,14) into a turbine engine shroud assembly (10), at least one of the outer surface edge portions (30/32) and its respective depression portion (36/38) and fluid seal surface (40) is distinct axially (18) from an axially (18) juxtaposed engine member (48) by a separation (46) therebetween. A fluid seal member (44), including a fluid seal surface (50) matched in shape with the planar seal surface (40) of the segment (12/14), is retained in juxtaposition for contact with the segment planar seal surface (40) along the separation (46), for example as a result of pressure loading during engine operation.
摘要翻译：具有主体（22），其包括沿周向（16）的弧形径向内表面（26）限定圆周弧和径向外表面（24）的涡轮发动机护罩段（14）设置，至少在一个轴向（18）间隔开的外表面边缘部分表面（30/32），与整个外边缘部分（30/32）和包括平面密封表面（40）的表面凹陷（36/38）周向地延伸（16）。面状密封表面（40）间隔开的径向（20）向外的圆周弧（26）间隔开，限定所述弧的弦（40）。面状密封表面（40）接合于段本体径向外表面（24）通过以弧形过渡表面（42）。在护罩段（12,14）到涡轮发动机罩组件（10）的多个圆周（16）的组件，所述外表面的边缘部分（30/32）及其respectivement凹陷部中的至少一个（36 / 38之间有）和流体密封表面（40）是不同的轴向（18）在从轴向（18）通过分离（46）并列的发动机部件（48）。流体密封构件（44）包括在形状上与所述段（12/14）的面状密封表面（40）相匹配的流体密封表面（50），被保持在并置用于与所述段平坦密封面接触（40 ）沿分离（46），例如，作为压力负荷的发动机操作期间的结果。

10. 发明公开

EP1085170A2 Turbine airfoil 有权
标题翻译： Turbinenschaufel
公开(公告)号：EP1085170A2
公开(公告)日：2001-03-21
申请号：EP00305984.7
申请日：2000-07-14
申请人： GENERAL ELECTRIC COMPANY
发明人： Darkins, Toby George, Jr. , Noe, Mark Eugene , Carper, Douglas Melton
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/18 , F01D5/147 , F05D2240/80 , F05D2300/21 , F05D2300/603
摘要： A turbine airfoil (10) includes at least one spar arrangement (11) having a length (92) less than an associated turbine airfoil length. During operation, the turbine airfoil has an outer skin surface (21) which operates at a substantially higher temperature than that of an internal supporting parted spar arrangement. The parted spar arrangement permits the turbine airfoil outer skin surface to thermally expand between spar arrangements, thus preventing self-constraining thermal stresses from forming within the spar arrangement or the airfoil skin surfaces.
摘要翻译：涡轮机翼片（10）包括具有小于相关联的涡轮机翼长度的长度（92）的至少一个翼梁布置（11）。在操作期间，涡轮机翼型件具有外表面（21），其在比内部支撑分离翼梁装置的温度明显更高的温度下操作。分段翼梁布置允许涡轮机翼型外皮表面在翼梁布置之间热膨胀，从而防止在翼梁布置或翼型皮肤表面内形成的自限制热应力。

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