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1. 发明申请

US20180291748A1 RESUPPLY HOLE OF COOLING AIR INTO GAS TURBINE BLADE SERPENTINE PASSAGE 审中-公开
公开(公告)号：US20180291748A1
公开(公告)日：2018-10-11
申请号：US15483003
申请日：2017-04-10
申请人： United Technologies Corporation
发明人： Christopher Whitfield , Carey Clum , Mark Borja
IPC分类号： F01D5/18 , F02C7/12 , F02C3/04
CPC分类号： F01D5/187 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2220/3212 , F05D2230/211 , F05D2240/301 , F05D2250/185 , F05D2260/221 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges and extending in a radial direction. A serpentine cooling passage is provided between the pressure and suction side walls. A passageway adjoins a passage wall and is fluidly interconnected to an upstream turn that has radially spaced apart innermost and outermost contours. The innermost contour is provided at the wall. A resupply hole is configured to exit downstream from the innermost contour.

2. 发明授权

US09528383B2 System for sealing between combustors and turbine of gas turbine engine 有权
标题翻译：燃气轮机和燃气轮机之间的密封系统
公开(公告)号：US09528383B2
公开(公告)日：2016-12-27
申请号：US14145774
申请日：2013-12-31
申请人： General Electric Company
发明人： Keith Cletus Belsom
IPC分类号： F01D9/02 , F23R3/60 , F01D9/04 , F01D11/00
CPC分类号： F02C7/28 , F01D9/023 , F01D9/041 , F01D11/003 , F02C3/14 , F05D2220/3212 , F05D2240/55 , F23R3/46 , F23R3/60 , F23R2900/00012
摘要： A gas turbine engine includes a gas turbine and a plurality of combustors each in fluid communication with the gas turbine. The gas turbine engine includes a first seal disposed between the gas turbine and the plurality of turbine combustors. The first seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors. The gas turbine engine also includes a second seal disposed between the gas turbine and the plurality of turbine combustors. The second seal is configured to sealingly engage with the gas turbine and at least two of the plurality of turbine combustors.
摘要翻译：燃气涡轮发动机包括燃气轮机和多个与燃气轮机流体连通的燃烧器。燃气涡轮发动机包括设置在燃气轮机和多个涡轮燃烧器之间的第一密封件。第一密封件构造成与燃气轮机和多个涡轮燃烧器中的至少两个密封地接合。燃气涡轮发动机还包括设置在燃气轮机和多个涡轮燃烧器之间的第二密封件。第二密封件构造成与燃气轮机和多个涡轮机燃烧器中的至少两个密封地接合。

3. 发明申请

US20160312797A1 INTERCOOLED COOLING AIR TAPPED FROM PLURAL LOCATIONS 审中-公开
标题翻译：从多个地点接收的自动冷却空气
公开(公告)号：US20160312797A1
公开(公告)日：2016-10-27
申请号：US14695534
申请日：2015-04-24
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Jesse M. Chandler , Joseph Brent Staubach , Brian D. Merry
IPC分类号： F04D29/58 , F01D25/12 , F02C7/143
CPC分类号： F04D29/5826 , F01D25/12 , F02C3/13 , F02C6/08 , F02C7/143 , F02C7/185 , F02C9/18 , F04D29/5833 , F05D2220/3212 , F05D2220/3217 , F05D2220/3219 , F05D2260/211 , F05D2260/213 , F05D2260/606 , F05D2270/3062 , Y02T50/675
摘要： A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
摘要翻译：燃气涡轮发动机包括具有下游最末端的高压压缩机和更上游位置的主压缩机部分。涡轮机部分具有高压涡轮机。第一分接头从主压缩机部分中的上游位置中的至少一个抽头抽吸空气，将抽头的空气通过热交换器，然后传递到冷却压缩机。冷却压缩机压缩热交换器下游的空气。第二分接头从距离第一抽头的位置更靠近下游最端的位置敲击空气。第一和第二抽头混合在一起并被输送到高压涡轮。还公开了一种用于燃气涡轮发动机的中间冷却系统。

4. 发明申请

US20160298545A1 TURBINE AIRFOIL 审中-公开
标题翻译：涡轮机空气
公开(公告)号：US20160298545A1
公开(公告)日：2016-10-13
申请号：US14684908
申请日：2015-04-13
申请人： General Electric Company
发明人： Xiuzhang James Zhang , Sandip Dutta , Gary Michael Itzel
IPC分类号： F02C7/18 , F01D5/02 , F02C3/06 , F01D5/18
CPC分类号： F02C7/185 , F01D5/02 , F01D5/187 , F02C3/06 , F05D2220/3212 , F05D2230/11 , F05D2240/24 , F05D2240/306 , F05D2240/307 , F05D2240/35 , F05D2260/20
摘要： A turbine airfoil includes a leading edge, a trailing edge, a root and a tip. Also included is a pressure side wall extending between the leading edge and the trailing edge and between the root and the tip. Further included is a suction side wall extending between the leading edge and the trailing edge and between the root and the tip. Yet further included is a non-circular cooling channel defined by the turbine airfoil and extending radially from the root to the tip, the non-circular cooling channel routing a cooling air to an outlet hole formed in the tip. Also included is an exhaust hole defined by the turbine airfoil and extending from the non-circular cooling channel to the suction side wall, the exhaust hole radially located between the root and the tip.
摘要翻译：涡轮机翼片包括前缘，后缘，根部和尖端。还包括在前缘和后缘之间以及根部和尖端之间延伸的压力侧壁。还包括在前缘和后缘之间以及根部与尖端之间延伸的吸力侧壁。还包括由涡轮机翼型件限定并从根部到顶端径向延伸的非圆形冷却通道，非圆形冷却通道将冷却空气引导到形成在尖端中的出口孔。还包括由涡轮机翼型件限定并从非圆形冷却通道延伸到吸入侧壁的排气孔，排气孔位于根部和尖端之间。

5. 发明授权

US09416676B2 Gas turbine 有权
标题翻译：燃气轮机
公开(公告)号：US09416676B2
公开(公告)日：2016-08-16
申请号：US14584811
申请日：2014-12-29
申请人： MTU Aero Engines AG
发明人： Walter Gieg , Petra Kufner , Rudolf Stanka
IPC分类号： F01D5/20 , F01D11/00 , F01D11/12 , F01D25/24 , F01D25/28 , B23P15/04 , B25B27/14 , F01D11/08
CPC分类号： F01D11/08 , F01D11/00 , F01D11/12 , F01D11/122 , F01D11/127 , F01D25/24 , F01D25/246 , F01D25/285 , F05D2200/11 , F05D2220/3212 , F05D2230/60 , F05D2230/68 , F05D2230/70 , F05D2240/11 , F05D2260/36 , F05D2260/37
摘要： The present invention relates to a gas turbine having a housing (1), an outer sealing ring (2) that can be fastened detachably to the housing, a clamping member (3) for clamping the outer sealing ring and the housing together radially, and a rotation locking member that has at least one housing groove (10) and a radial flange (20) of the outer sealing ring that can be locked against rotation in the housing groove in form-fitting manner with play (sa) in the axial and/or peripheral direction.
摘要翻译：本发明涉及一种具有壳体（1），能够可拆卸地固定到壳体的外密封环（2）的燃气轮机，用于将外密封环和壳体径向夹持的夹紧构件（3），以及旋转锁定构件具有至少一个外部密封环的容纳凹槽（10）和径向凸缘（20），该外部密封环能够以与轴向和（或）轴向成形配合的方式在壳体凹槽中防止旋转而锁定， /或周边方向。

6. 发明申请

US20160146041A1 BLADE OR VANE FOR A TURBOMACHINE AND AXIAL TURBOMACHINE 有权
标题翻译：涡轮机和轴流式涡轮机的叶片或叶片
公开(公告)号：US20160146041A1
公开(公告)日：2016-05-26
申请号：US14943686
申请日：2015-11-17
申请人： MTU Aero Engines AG
发明人： Andreas Hartung , Hermann Klingels , Patrick Wackers , Manfred Feldmann , Frank Stiehler , Markus Schlemmer
IPC分类号： F01D25/06 , F01D9/04 , F04D29/32
CPC分类号： F01D25/06 , F01D5/10 , F01D5/16 , F01D5/26 , F01D9/02 , F01D9/041 , F04D29/324 , F04D29/662 , F04D29/668 , F05D2220/32 , F05D2220/3212 , F05D2220/3215 , F05D2220/3217 , F05D2220/3219 , F05D2240/129 , F05D2240/30 , F05D2250/12 , F05D2250/121 , F05D2250/131 , F05D2250/141 , F05D2250/313 , F05D2260/96 , Y02T50/671
摘要： The present invention relates to a blade (100) or vane for a turbomachine, having at least one impulse element housing (1.1, 1.2) with a first impact cavity (10), in which an impulse element (11) is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity (20), which is in alignment with the first impact cavity in a first matrix direction (A) and in which an impulse element (21) is arranged with play of movement, and has at least one third impact cavity (30), which is in alignment with the first impact cavity in a second matrix direction (B) crosswise to the first matrix direction and in which an impulse element (31) is arranged with play of movement.
摘要翻译：本发明涉及一种用于涡轮机的叶片（100）或叶片，其具有至少一个具有第一冲击腔（10）的脉冲元件壳体（1.1,1.2），其中脉冲元件（11）布置成运动，其中所述脉冲元件壳体具有至少一个第二冲击腔（20），所述第二冲击腔在第一矩阵方向（A）上与所述第一冲击腔对准，并且其中脉冲元件（21）布置成具有运动，并且具有至少一个第三冲击腔（30），其在与第一矩阵方向交叉的第二矩阵方向（B）上与第一冲击腔对准，其中脉冲元件（31）布置成与运动。

7. 发明授权

US09328618B2 High-pressure turbine nozzle for a turbojet 有权
标题翻译：用于涡轮喷气发动机的高压涡轮喷嘴
公开(公告)号：US09328618B2
公开(公告)日：2016-05-03
申请号：US13522163
申请日：2011-01-06
申请人： Régis Grohens , Renaud Gabriel Constant Royan
发明人： Régis Grohens , Renaud Gabriel Constant Royan
IPC分类号： F01D5/18 , F01D9/04 , F01D17/08
CPC分类号： F01D5/189 , F01D9/04 , F01D17/085 , F05D2220/3212 , F05D2240/126 , F05D2270/08 , F05D2300/21 , F05D2300/50212 , F05D2300/603 , Y02T50/672 , Y02T50/676 , Y02T50/677
摘要： A high temperature turbine nozzle with automatic regulation of flow of cooling air passing therethrough. Each of vanes includes a first sleeve drilled with holes and a second sleeve that is engaged in the first sleeve, drilled with corresponding holes, and made of a material possessing a coefficient of expansion different from that of the first sleeve.
摘要翻译：高温涡轮喷嘴，其自动调节通过其中的冷却空气流。每个叶片包括钻有孔的第一套筒和接合在第一套筒中的第二套筒，钻有相应的孔，并由具有不同于第一套筒的膨胀系数的材料制成。

8. 发明申请

US20160108748A1 GAS TURBINE ENGINE WITH DOVE-TAILED TOBI VANE 审中-公开
标题翻译：燃气涡轮发动机与DOVE-TAILED TOBI VANE
公开(公告)号：US20160108748A1
公开(公告)日：2016-04-21
申请号：US14892138
申请日：2014-05-28
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Meggan HARRIS
IPC分类号： F01D9/06 , F01D9/04
CPC分类号： F01D9/065 , F01D5/081 , F01D5/3007 , F01D9/04 , F01D9/042 , F01D25/12 , F05D2220/3212 , Y02T50/676
摘要： A combustor assembly for a gas turbine engine includes a TOBI module which includes a TOBI housing. The TOBI housing has a slot. A vane including a dovetail is removably received within the slot.
摘要翻译：用于燃气涡轮发动机的燃烧器组件包括包括TOBI壳体的TOBI模块。 TOBI外壳有一个插槽。包括燕尾的叶片可拆卸地被容纳在槽内。

9. 发明申请

US20150135715A1 Cooling System for Gas Turbine 审中-公开
标题翻译：燃气轮机冷却系统
公开(公告)号：US20150135715A1
公开(公告)日：2015-05-21
申请号：US14546138
申请日：2014-11-18
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Tomoyuki MATSUI , Hayato MAEKAWA , Ryo KAWAI
IPC分类号： F02C7/18 , F01D5/18
CPC分类号： F02C7/18 , F01D5/081 , F01D5/187 , F05D2220/3212 , F05D2260/201 , Y02T50/676
摘要： The invention provides a gas turbine cooling system that efficiently cools a first-stage turbine wheel and the attachment portions of first-stage turbine blades.A gas turbine comprises: a compressor 1 for compressing air; a combustor 2 for combusting the air compressed by the compressor 1 with fuel; and a turbine 3 driven by the combustion gas generated by the combustor 2, the turbine 3 including at least one turbine wheel 12a having turbine blades 11a on an outer circumferential section thereof. A gas turbine cooling system comprises a group of impingement cooling holes 32, provided in a partition wall 16a that separates the exit space 42 of the compressor 1 and the wheel space 43a located upstream of the turbine wheel 12a, for ejecting the compressed air 101 in the exit space 42 toward the turbine wheel 12a and the attachment portions of the turbine blades 11a.
摘要翻译：本发明提供了一种有效地冷却第一级涡轮机叶轮和第一级涡轮叶片的附接部分的燃气轮机冷却系统。燃气轮机包括：用于压缩空气的压缩机1; 用于燃烧由压缩机1压缩的空气的燃烧器2; 以及由燃烧器2产生的燃烧气体驱动的涡轮机3，涡轮机3包括在其外周部分上具有涡轮叶片11a的至少一个涡轮机叶片12a。燃气轮机冷却系统包括一组冲击冷却孔32，其设置在分隔压缩机1的出口空间42和位于涡轮机叶片12a上游的轮空间43a的分隔壁16a中，用于将压缩空气101排出出口空间42朝向涡轮叶片12a和涡轮叶片11a的附接部分。

10. 发明申请

US20120294706A1 SEALING ARRANGEMENT AND GAS TURBINE ENGINE WITH THE SEALING ARRANGEMENT 有权
标题翻译：密封装置和气体涡轮发动机密封装置
公开(公告)号：US20120294706A1
公开(公告)日：2012-11-22
申请号：US13521635
申请日：2011-01-11
申请人： Ryozo Tanaka , Tomoki Taniguchi
发明人： Ryozo Tanaka , Tomoki Taniguchi
IPC分类号： F16J15/06 , F04D29/08 , F16J15/08
CPC分类号： F01D11/005 , F01D11/003 , F05D2220/3212 , F05D2230/642 , F05D2240/12 , F05D2250/131 , F05D2250/75
摘要： At least one sealing arrangement is provided for a connecting mechanism between an inner annular member or an outer annular member and an associated segment to connect between the annular members and the segments. The sealing arrangement includes an elastic sealing member provided between the sealing surfaces, disposed linearly along a side of polygon defined around a central axis.
摘要翻译：为内环形构件或外环形构件之间的连接机构提供至少一个密封装置和相关联的节段以在环形构件和段之间连接。密封装置包括设置在密封表面之间的弹性密封构件，其沿着围绕中心轴限定的多边形线性设置。

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