公开(公告)号：EP3361160A1

公开(公告)日：2018-08-15

申请号：EP18155310.8

申请日：2018-02-06

申请人： General Electric Company

发明人： LIN, Dechao ,  KOTTILINGAM, Srikanth Chandrudu ,  TOLLISON, Brian Lee ,  CUI, Yan

IPC分类号： F23R3/28 ,  F23D14/64 ,  F23R3/04

CPC分类号： F23R3/286 ,  B01F13/0062 ,  B01F2215/0086 ,  B23K1/0018 ,  B23K1/19 ,  B23K2101/001 ,  B23K2103/05 ,  F23D14/64 ,  F23R3/045 ,  F23R3/283 ,  F23R2900/00005

摘要： Manufactured articles (16), and methods of manufacturing enhanced wear protected components (12) and articles (16). More particularly, wear protected components (12) and articles (16), such as combustor components (12) of turbine engines (10), and even more particularly enhanced wear protected micromixer tubes (20) and assemblies thereof with one or more micromixer plates (17), the micromixer tubes (20) having wear protection for enhanced performance and reduced wear related failure. Methods including surface treatment to enhance wear, including vacuum braze application of coatings to enhance surface hardness for wear benefits.

公开(公告)号：EP3306195A2

公开(公告)日：2018-04-11

申请号：EP17191190.2

申请日：2017-09-14

申请人： United Technologies Corporation

发明人： QUACH, San ,  ELLIOT, Scott A. ,  SONNTAG, Robert M. ,  TU, John S. ,  VAN, Anthony ,  SEDOR, Joseph J. ,  SELINSKY, Jr., Robert ,  RUP, Jr., John J. ,  RIDGEWAY, Neil B. ,  CADIEUX, Gerard V. ,  LEON, Jeffrey ,  PACHECO-TOUGAS, Monica ,  JENKINS, Lisa A. ,  TSE, Lisa ,  CERVONI, Andrew ,  TRZCINSKI, Frank J.

IPC分类号： F23R3/00 ,  F23R3/06 ,  F23R3/50

CPC分类号： F23R3/002 ,  F02C7/12 ,  F05D2220/32 ,  F05D2240/35 ,  F05D2300/611 ,  F23R3/06 ,  F23R3/44 ,  F23R3/50 ,  F23R2900/00005 ,  F23R2900/03045

摘要： A wall panel assembly (22) includes a first liner panel (50) and a coating (56). The first liner panel has a first liner panel inner surface (70) and a first liner panel outer surface (72) each axially extending between a first liner panel first end (80) and a first liner panel second end (82). The coating (56) is disposed on at least one of the first liner panel inner surface and the first liner panel outer surface. The coating has an overall thickness (to) that varies axially between the first liner panel first end and the first liner panel second end.

摘要翻译： 墙板组件（22）包括第一衬板（50）和涂层（56）。 第一衬垫面板具有第一衬垫面板内表面（70）和第一衬垫面板外表面（72），第一衬垫面板内表面（70）和第一衬垫面板外表面（72）各自在第一衬垫面板第一端部（80）和第一衬垫面板第二端部（82）之间轴向延伸。 涂层（56）设置在第一衬板内表面和第一衬板外表面中的至少一个上。 涂层具有在第一衬板第一端和第一衬板第二端之间轴向变化的总厚度（t 0）。

公开(公告)号：EP2738354A3

公开(公告)日：2018-02-28

申请号：EP13192687.5

申请日：2013-11-13

申请人： Mitsubishi Hitachi Power Systems, Ltd.

发明人： Sekihara, Masaru ,  Ichikawa, Kunihiro

IPC分类号： F01D9/02

CPC分类号： F01D9/023 ,  F05D2260/941 ,  F23R3/60 ,  F23R2900/00005

摘要： A gas turbine combustion chamber 2 is provided, including a flow sleeve 7 structure with an improved anti-vibration performance. A gas turbine combustion chamber 2 of the present invention includes a liner 5, a transition piece 4, and a flow sleeve 7 including a plurality of segments and integrated by welding a tie piece 8 along joint portions of the segments. The tie piece 8 includes a first member 81 and a second member 82, the first member 81 continuously extending along a longitudinal direction of the joint portions of the segments and being arranged to cover the joint portions, and the second member 82 being formed at an end portion of the first member 81, having a width wider than the first member 81, and including a recess 10.

摘要翻译： 提供燃气涡轮燃烧室2，其包括具有改善的抗振动性能的流动套筒7结构。 本发明的燃气轮机燃烧室2包括衬套5，过渡件4和包括多个节段并且通过沿着节段的接合部分焊接连接件8而集成的流动套筒7。 连接件8包括第一构件81和第二构件82，第一构件81沿着节段的连接部分的纵向方向连续地延伸并且布置成覆盖连接部分，并且第二构件82形成为 第一构件81的宽度大于第一构件81的端部，并且包括凹部10。

公开(公告)号：EP3220047A1

公开(公告)日：2017-09-20

申请号：EP17160282.4

申请日：2017-03-10

申请人： General Electric Company

发明人： WILLIS, Christopher Paul ,  CIHLAR, David William ,  KEGLEY, Jonathan Hale ,  GODFREY, Andrew Grady ,  PORZIO, David Philip

IPC分类号： F23R3/00 ,  F23R3/06

CPC分类号： F23R3/002 ,  F02C3/04 ,  F23R3/06 ,  F23R3/46 ,  F23R2900/00005

摘要： The present disclosure is directed a combustor 16. The combustor 16 includes an annularly shaped liner 42 having a downstream end 60 that is rigidly connected to an aft frame 62. A flow sleeve 54 circumferentially surrounds at least a portion of the liner 42 and is radially spaced from the liner 42 to form a cooling flow annulus 56 therebetween. A plurality of fuel injector assemblies 102 is circumferentially spaced about the flow sleeve 54. Each fuel injector assembly 102 extends radially through the flow sleeve 54 and the liner 42. Each fuel injector assembly 102 is rigidly connected to the flow sleeve 54 and to the liner 42. An aft end 66 of the flow sleeve 54 terminates axially short of the aft frame 62 to form an axial gap 72 between the aft end 66 and the aft frame 62 to allow for unrestrained axial expansion and contraction of the aft end 66.

摘要翻译： 本发明涉及燃烧器16.燃烧器16包括环形衬里42，其具有刚性连接到后框架62的下游端60.流动套筒54沿周向围绕衬里42的至少一部分并径向地 与衬套42间隔开以在其间形成冷却流动环56。 多个燃料喷射器组件102围绕流动套筒54周向间隔开。每个燃料喷射器组件102径向延伸穿过流动套筒54和衬里42.每个燃料喷射器组件102刚性连接到流动套筒54和衬套 42.流动套筒54的后端66在轴向上短于后框架62终止，以在后端66和后框架62之间形成轴向间隙72，以允许后端66的无约束轴向膨胀和收缩。

公开(公告)号：EP3044511A4

公开(公告)日：2017-09-06

申请号：EP14843708

申请日：2014-08-19

申请人： UNITED TECHNOLOGIES CORP

发明人： CHANG HOYT Y

IPC分类号： F23R3/00 ,  F23R3/50 ,  F23R3/60

CPC分类号： F23R3/007 ,  F02C7/24 ,  F23R3/002 ,  F23R3/06 ,  F23R3/50 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/03044 ,  Y02T50/672 ,  Y02T50/675

公开(公告)号：EP2184542A3

公开(公告)日：2017-08-30

申请号：EP09174684.2

申请日：2009-10-30

申请人： General Electric Company

发明人： Myers, Geoffrey D. ,  Simmons, Scott ,  Thomas, Stephen R. ,  Bailey, Donald Mark

IPC分类号： F23R3/28 ,  F23D14/46

CPC分类号： F23R3/28 ,  F16L9/02 ,  F16L9/18 ,  F16L51/00 ,  F23D14/46 ,  F23D2206/10 ,  F23D2211/00 ,  F23D2212/20 ,  F23R2900/00005

摘要： A fuel nozzle (400) configured to channel fluid towards a combustion chamber (128) defined within a gas turbine engine (100) is provided. The fuel nozzle includes a first hollow tube (420) fabricated from a first material that has a first coefficient of thermal expansion and a second tube (410) fabricated from a second material that has a second coefficient of thermal expansion that is different from the first coefficient of thermal expansion, wherein the second tube is coupled within the first tube such that the first tube substantially circumscribes the second tube, wherein the second tube thermally expands approximately at a same rate as the first tube during fuel nozzle operation.

摘要翻译： 提供了构造成将流体导向限定在燃气涡轮发动机（100）内的燃烧室（128）的燃料喷嘴（400）。 燃料喷嘴包括由具有第一热膨胀系数的第一材料制成的第一中空管（420）和由具有不同于第一热膨胀系数的第二热膨胀系数的第二材料制成的第二管（410） 其中第二管联接在第一管内使得第一管基本上包围第二管，其中第二管在燃料喷嘴操作期间与第一管大致以相同的速率热膨胀。

公开(公告)号：EP3022407A4

公开(公告)日：2017-03-22

申请号：EP14826220

申请日：2014-06-18

申请人： UNITED TECHNOLOGIES CORP

发明人： COOK III GRANT O ,  ABBOTT MICHAEL G ,  MCCAFFREY MICHAEL G

IPC分类号： F01D25/28 ,  B32B37/12 ,  C09J5/00 ,  F01D25/08 ,  F02C7/20 ,  F02C7/24

CPC分类号： F23R3/007 ,  C09J5/00 ,  C09J2400/123 ,  C09J2400/163 ,  F01D5/284 ,  F01D9/02 ,  F01D25/246 ,  F05D2230/236 ,  F05D2230/642 ,  F05D2240/11 ,  F23R3/002 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00017 ,  Y02T50/672

摘要： A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic. A bonding material secures the ceramic component to the metallic component. The bonding material includes at least one of a transient liquid phase bond and a partial transient liquid phase bond. The bonding material is configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics.

摘要翻译： 燃气涡轮发动机部件组件包括具有第一热特性的陶瓷部件。 金属部件具有第二热特性。 接合材料将陶瓷部件固定在金属部件上。 接合材料包括瞬态液相和部分瞬态液相键中的至少一种。 接合材料被配置为承受与第一和第二热特性之间的差异相关的剪切应力参数。

公开(公告)号：EP3134681A1

公开(公告)日：2017-03-01

申请号：EP15778915.7

申请日：2015-10-08

申请人： Siemens Aktiengesellschaft

发明人： BECK, Christian ,  BÖTTCHER, Andreas ,  GRANDT, Christopher ,  HAUSER, Thomas ,  LAPP, Patrick ,  REICH, Stefan

IPC分类号： F23R3/28 ,  F23R3/36 ,  F23D17/00

CPC分类号： F23R3/36 ,  F02C3/04 ,  F23D17/002 ,  F23D2211/00 ,  F23D2900/00008 ,  F23R3/286 ,  F23R2900/00005

摘要： The invention relates to a fuel nozzle body (1) comprising a rearward end (2) and a front end (3) comprising an outer tube (4) which extends from the rearward end (2) to the front end (3) and has radial openings (5) for a first fuel (6) in the region of the front end (3), and an inner tube (7) which is arranged concentrically to the outer tube (4) and which opens in the region of the front end (3) into a nozzle head (8), which has additional openings (9) for a second fuel (10), wherein, in the region of the front end (3), the inner tube (7) is guided in the outer tube (4) by two fits (11, 12) which are arranged axially between the radial openings (5) and the additional openings (9), and wherein the first fit (11) closest to the radial openings (5) is configured as a circumferential web (13) around the inner tube (7), and wherein the second fit (12) is configured with at least one interruption on the perimeter. The invention further relates to a burner (23) and to a gas turbine (24).

摘要翻译： 本发明涉及一种燃料喷嘴主体（1），包括后端（2）和前端（3），前端（3）包括从后端（2）延伸到前端（3）的外管（4），并且具有 在前端（3）的区域中的用于第一燃料（6）的径向开口（5）和与外管（4）同心设置并且在前端（3）的区域中开口的内管 端部（3）进入喷嘴头（8），其具有用于第二燃料（10）的附加开口（9），其中在前端（3）的区域中，内管（7）被引导到 外管（4）通过两个配合（11,12）轴向布置在径向开口（5）和附加开口（9）之间，并且其中最靠近径向开口（5）的第一配合（11）被配置 作为围绕所述内管（7）的周向腹板（13），并且其中所述第二配合（12）在所述周边上配置有至少一个中断。 本发明还涉及燃烧器（23）和燃气轮机（24）。

公开(公告)号：EP3114409A1

公开(公告)日：2017-01-11

申请号：EP15706859.4

申请日：2015-01-27

申请人： Safran Helicopter Engines

发明人： SAVARY, Nicolas ,  BERTEAU, Patrick ,  CARRERE, Bernard ,  DUBOURDIEU, Jean-Marc ,  NAUDOT, Ludovic

IPC分类号： F23R3/00 ,  F23R3/52 ,  F23R3/60

CPC分类号： F23R3/52 ,  F02C7/20 ,  F05D2230/50 ,  F05D2230/51 ,  F05D2230/64 ,  F05D2230/642 ,  F05D2240/35 ,  F05D2240/90 ,  F05D2260/30 ,  F23C5/02 ,  F23D11/103 ,  F23R3/002 ,  F23R3/007 ,  F23R3/28 ,  F23R3/283 ,  F23R3/42 ,  F23R3/425 ,  F23R3/46 ,  F23R3/48 ,  F23R3/50 ,  F23R3/54 ,  F23R3/56 ,  F23R3/58 ,  F23R3/60 ,  F23R2900/00005 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/00019

摘要： The invention relates to an annular turbine engine combustion chamber having an axial direction (X), a radial direction, and an azimuthal direction. Said chamber includes a first annular wall (12) and a second annular wall (14). Each wall defines at least part of the enclosure of the annular combustion chamber. The first and second walls (12, 14) have complementary interlocking elements (12d, 14d). The first wall (12) has at least one first through-hole (12f), while the second wall (14) has at least one second through-hole (14f). The combustion chamber also includes at least one pin inserted into a pair of holes that include a first hole (12f) and a second hole (14f). Said pin (18) is formed by an injector and securely interlocks the first and second walls (12, 14).

摘要翻译： 一种用于涡轮机（100）的环形燃烧室（10），所述燃烧室具有轴向方向（X），径向方向和方位方向，并且包括第一环形壁（12）和第二环形壁 ），限定所述环形燃烧室（10）的体积的至少一部分的每个壁，所述第一和第二壁（12,14）呈现互补的配合元件（12d，14d），所述第一壁（12）至少呈现 一个第一通孔（12f），而第二壁（14）呈现至少一个第二通孔（14f），燃烧室（10）还具有接合在一对孔中的至少一个销（18） 孔（12f）和第二孔（14f），所述销（18）锁定第一和第二壁（12,14）的配件。

公开(公告)号：EP1507121B1

公开(公告)日：2016-09-14

申请号：EP04254573.1

申请日：2004-07-30

申请人： GENERAL ELECTRIC COMPANY

发明人： McMasters, Marie Ann ,  Cooper, James Neil ,  Thomsen, Duane Douglas ,  Vandike, John Lawrence ,  Vermeersch, Michael Louis ,  Danis, Allen Michael

IPC分类号： F23R3/60 ,  F23R3/10

CPC分类号： F23R3/10 ,  F23R2900/00005