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11. 发明授权

EP1284338B1 Tangential flow baffle 有权
标题翻译：冷凝管切向流出
公开(公告)号：EP1284338B1
公开(公告)日：2008-01-02
申请号：EP02254029.8
申请日：2002-06-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Noe, Mark Eugene , Doughty, Roger Lee , Darkins, Toby George Jr.
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2240/10 , F05D2240/126 , F05D2260/201 , F05D2260/202 , F05D2260/22141 , Y02T50/672 , Y02T50/673 , Y02T50/676

12. 发明公开

EP1609952A1 Turbine vane collar seal 有权
标题翻译： ManschettendichtungfürTurbinenleitschaufeln
公开(公告)号：EP1609952A1
公开(公告)日：2005-12-28
申请号：EP05253878.2
申请日：2005-06-22
申请人： GENERAL ELECTRIC COMPANY
发明人： Wells, Thomas Allen , Bulman, David Edward , Noe, Mark Eugene , Bhate, Nitin
IPC分类号： F01D9/04 , F16J15/08
CPC分类号： F01D9/042 , F01D11/005 , F05D2230/642 , F05D2240/57 , F16J15/0812 , F16J15/0887 , Y02T50/672 , Y02T50/673
摘要： A collar seal (34) is configured for a turbine nozzle vane. The seal (34) includes a retainer (36) having a circumferential airfoil contour conforming with the airfoil contour of the vane (32). A flexible leaf (48) is surrounded by the retainer (36) and fixedly joined thereto. A woven sheath (50) encases the leaf (48) and is fixedly joined to the retainer (36). In an exemplary embodiment, the collar seal (34) surrounds one end of a ceramic turbine vane (32) mounted in a metal supporting band (26).
摘要翻译：套筒密封件（34）构造成用于涡轮喷嘴叶片。密封件（34）包括具有与叶片（32）的翼型轮廓相符的周向翼型轮廓的保持器（36）。柔性叶片（48）由保持器（36）围绕并且与其固定连接。编织护套（50）包住叶片（48）并且固定地连接到保持器（36）。在示例性实施例中，套环密封件（34）围绕安装在金属支撑带（26）中的陶瓷涡轮叶片（32）的一端。

13. 发明公开

EP1350927A3 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：EP1350927A3
公开(公告)日：2004-12-29
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).

14. 发明公开

EP1443190A1 Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner 审中-公开
标题翻译：装置，用于安装在燃气轮机燃烧器的点火器具有陶瓷内衬
公开(公告)号：EP1443190A1
公开(公告)日：2004-08-04
申请号：EP03257116.8
申请日：2003-11-12
申请人： GENERAL ELECTRIC COMPANY
发明人： Wells, Thomas Allen , Noe, Mark Eugene , Gylnn, Christopher Charles , Bulman, David Edward , Hansel, Herold Ray
IPC分类号： F02C7/264 , F23R3/00 , F23R3/60
CPC分类号： F16F3/04 , F02C7/264 , F23D2207/00 , F23D2211/00 , F23R3/60 , F23R2900/00012
摘要： An assembly (38) for mounting an igniter in a gas turbine engine combustor between an outer casing (30) and an outer liner (16). The igniter mounting assembly (38) includes a first spring member (42) encircling a portion (44) of said igniter (36) and being positioned between a surface adjacent the outer casing (30) and an outer surface (50) of the outer liner (16), a first ring member (46) connected to a first end (48) of the first spring member (42) adjacent the outer surface (50) of the outer liner (16), and a second ring member (52) connected to a second end (54) of the first spring member (42) adjacent the surface adjacent the outer casing (30). Accordingly, the igniter (36) is able to maintain substantial alignment with respect to an opening (40) in the outer liner (16) while moving radially and/or axially with respect to the outer liner (16) as the outer casing (30) experiences thermal growth greater than the outer liner (16).
摘要翻译：在（30）和上外衬垫（16）在外壳之间的气体涡轮发动机燃烧器点火器上安装的组件（38）。该点火器的安装组件（38）包括第一弹簧件（42）环绕所述点火器（36）的一个部分（44）和一个表面相邻的外壳体（30）之间，并在所述外的外表面（50）被定位衬垫（16），一个连接到所述第一弹簧构件的第一端部（48），第一环构件（46）（42）相邻的所述外外衬垫（16）的表面（50），和一第二环形构件（52 ）连接到所述第一弹簧部件（42）相邻的所述表面相邻的外壳体（30）的第二端（54）。因此，点火器（36）是能够保持相对于基本对齐，以在所述外衬套（16）开口（40），而相对于沿径向和/或轴向移动到外衬套（16）作为外部壳体（30 ）经历热生长比外衬垫（16）大。

15. 发明公开

EP1431518A2 Turbine engine shroud segment assembly with a surface-recessed seal bridging adjacent shroud segments 审中-公开
标题翻译：一个燃气涡轮机的护罩段组件与每个段之间的密封元件
公开(公告)号：EP1431518A2
公开(公告)日：2004-06-23
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
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.

16. 发明公开

EP1284338A2 Tangential flow baffle 有权
标题翻译： Kühleinsatzmit切线机Ausströmung
公开(公告)号：EP1284338A2
公开(公告)日：2003-02-19
申请号：EP02254029.8
申请日：2002-06-10
申请人： GENERAL ELECTRIC COMPANY
发明人： Noe, Mark Eugene , Doughty, Roger Lee , Darkins, Toby George Jr.
IPC分类号： F01D5/18
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 (22) includes a plurality of apertures (30) inclined through a shell (32) for discharging a coolant (20) tangentially therefrom. The baffle is disposed inside a nozzle vane (14) and the tangentially discharged coolant (20) flows generally parallel along the inner surface of the vane for convection cooling thereof.
摘要翻译：涡轮喷嘴挡板（22）包括通过壳体（32）倾斜的多个孔（30），用于从其切向排出冷却剂（20）。挡板设置在喷嘴叶片（14）的内部，切向排出的冷却剂（20）沿叶片的内表面大致平行地流动，用于对流冷却。

17. 发明公开

EP1126135A3 Ceramic turbine airfoils with cooled trailing edge blocks 有权
标题翻译：陶瓷涡轮机叶片后缘与冷却
公开(公告)号：EP1126135A3
公开(公告)日：2003-01-08
申请号：EP00311265.3
申请日：2000-12-15
申请人： GENERAL ELECTRIC COMPANY
发明人： Darkins, Toby George, Jr. , Shelton, Monty Lee , Doughty, Roger Lee , Noe, Mark Eugene
IPC分类号： F01D5/18 , F01D9/02 , F01D5/28
CPC分类号： F01D5/187 , F01D5/186 , F01D5/284 , F05D2250/323 , F05D2300/2261 , F05D2300/603 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine hollow turbine airfoil (12), such as a first stage vane (10) of a high pressure turbine of a gas turbine engine includes an outer wall (40) surrounding a hollow interior (22). The outer wall (40) extends radially outwardly in a spanwise direction (S) from an airfoil base (46) to an airfoil tip (48) and has chordwise spaced apart leading and trailing edges (LE, TE) and widthwise spaced apart pressure and suction side portions (52, 54) extending chordwise between the leading edge (LE) and a trailing edge block (50) which terminates at the trailing edge. A plurality of trailing edge cooling air ducts (60) extend chordwise through the trailing edge block (50) aftwardly from the hollow interior (22) and a plurality of trailing edge film cooling holes (62) extend from the ducts through the trailing edge block (50). The cooling air ducts (60) are preferably centered near a neutral axis (64) of chordwise and spanwise bending of the trailing edge block (50). The trailing edge cooling air ducts (60) converge aftwardly from the hollow interior (22) and preferably converge in width with a substantially constant spanwise height (66). The invention is particularly suitable for turbine airfoils (12) and vanes (10) made with a ceramic matrix composite material such as one having a SiC matrix and, more particularly, with an SiC-SiC ceramic matrix composite. The airfoil (12) is disposed between radially inner and outer segmented platforms (16, 18) that are, in one embodiment, integrally formed of a ceramic matrix composite (CMC) preferably a SiC-SiC CMC.

18. 发明授权

EP2570600B1 Turbine rotor blade assembly and method of assembling same 有权
公开(公告)号：EP2570600B1
公开(公告)日：2019-02-20
申请号：EP12182828.9
申请日：2012-09-03
申请人： General Electric Company
发明人： Paige II, Anthony Reid , Verrilli, Michael James , Jamison, Joshua Brian , Noe, Mark Eugene , Izon, Paul , Marusko, Mark Willard
IPC分类号： F01D5/26 , F01D5/28 , F01D5/30 , F01D11/08 , F01D5/22 , F01D11/00

19. 发明公开

EP2570600A3 Turbine rotor blade assembly and method of assembling same 有权
标题翻译：涡轮转子叶片组件及其组装方法
公开(公告)号：EP2570600A3
公开(公告)日：2017-11-15
申请号：EP12182828.9
申请日：2012-09-03
申请人： General Electric Company
发明人： Paige II, Anthony Reid , Verrilli, Michael James , Jamison, Joshua Brian , Noe, Mark Eugene , Izon, Paul , Marusko, Mark Willard
IPC分类号： F01D5/26 , F01D5/28 , F01D5/30 , F01D11/08 , F01D5/22 , F01D11/00
CPC分类号： F01D5/284 , F01D5/22 , F01D5/3007 , F01D11/006 , F01D11/08 , F05D2300/6033 , Y02T50/672 , Y10T29/49321
摘要： A rotor blade assembly (100) for a rotor (30) of a gas turbine engine (10) having an axis of rotation (8) includes a shank portion (106) formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion (104) formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions (128) of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus (120). At least a portion of the damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus (120) extending toward a circumferentially adjacent rotor blade assembly (100).
摘要翻译：一种用于具有旋转轴线（8）的燃气涡轮发动机（10）的转子（30）的转子叶片组件（100）包括由陶瓷基质复合材料（CMC）材料形成的柄部分（106）。转子叶片组件还包括平台部分（104），该平台部分（104）由与杆部分基本相似的CMC材料形成。平台部分连接到柄部分。平台部分和柄部配合以至少部分地限定转子叶片组件的两个相对的侧部（128）。相对的侧面部分相对于旋转轴线成角度地分开。转子叶片组件还包括阻尼器保持装置（120）。阻尼器保持装置的至少一部分联接到柄部分。阻尼器保持装置包括朝向周向相邻的转子叶片组件（100）延伸的至少一个成角度的支架装置（120）。

20. 发明授权

EP1609952B1 Turbine vane collar seal 有权
标题翻译：杯形密封件用于涡轮
公开(公告)号：EP1609952B1
公开(公告)日：2008-01-23
申请号：EP05253878.2
申请日：2005-06-22
申请人： GENERAL ELECTRIC COMPANY
发明人： Wells, Thomas Allen , Bulman, David Edward , Noe, Mark Eugene , Bhate, Nitin
IPC分类号： F01D9/04 , F16J15/08
CPC分类号： F01D9/042 , F01D11/005 , F05D2230/642 , F05D2240/57 , F16J15/0812 , F16J15/0887 , Y02T50/672 , Y02T50/673

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