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81. 发明申请

US20170159466A1 GUIDE VANE SEGMENT WITH RADIAL SECURING ELEMENTS 审中-公开
公开(公告)号：US20170159466A1
公开(公告)日：2017-06-08
申请号：US15367752
申请日：2016-12-02
申请人： MTU Aero Engines AG
发明人： Markus Schlemmer , Manfred Feldmann , Rudolf Stanka , Oliver Thiele , Bernd Kislinger , Manuel Hein
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , B24B19/14 , F01D25/246 , F05D2230/10
摘要： The invention relates to a guide vane segment (10) for a gas turbine comprising at least one radially outer shroud (14) and one radially inner shroud (12), which extend along a respective arc and together form an annular segment, wherein, in the radial direction (RR) between the outer shroud (14) and the inner shroud (12), a plurality of guide vanes (16) are arranged adjacent to one another in the peripheral direction (UR) and are joined to the inner shroud (12) and to the outer shroud (14) in a material-bonded manner and, in particular, are joined in a one-piece manner, wherein, in an axial lengthwise direction (AR), the outer shroud (14) comprises an axially front end wall element (22) and an axially rear end wall element (24) in such a way that the outer shroud (14) and the two end walls (22, 24) form a tub-like profile in lengthwise section.

82. 发明申请

US20170152866A1 STATOR VANE SYSTEM USABLE WITHIN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170152866A1
公开(公告)日：2017-06-01
申请号：US15323895
申请日：2014-07-24
申请人： Siemens Aktiengesellschaft
发明人： Elliot Griffin
IPC分类号： F04D29/64 , F04D29/08 , F04D29/54
CPC分类号： F04D29/644 , F01D9/042 , F01D11/001 , F01D11/127 , F01D25/246 , F04D29/083 , F04D29/542 , F05D2230/64 , F05D2260/30 , F05D2300/505
摘要： A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).

83. 发明申请

US20170152857A1 CASING FOR A TURBOMACHINE, INSTALLATION SAFEGUARD AND TURBOMACHINE 审中-公开
公开(公告)号：US20170152857A1
公开(公告)日：2017-06-01
申请号：US15359793
申请日：2016-11-23
申请人： MTU Aero Engines AG
发明人： Lothar ALBERS , Georg ZOTZ , Vitalis MAIRHANSER
IPC分类号： F04D29/02 , F04D29/54 , F04D29/64 , F04D29/52
CPC分类号： F04D29/023 , F01D25/246 , F04D29/526 , F04D29/54 , F04D29/644 , F04D29/685 , F05D2260/37 , Y02T50/672
摘要： Disclosed is a casing of a turbomachine which comprises at least a first casing portion comprising a first material having a first coefficient of thermal expansion and a second casing portion comprising a second material having a second coefficient of thermal expansion. The second casing portion comprises a casing structuring with flow-guiding elements and is connected in a force-fitting manner to the first casing portion by a radial press fit. Also disclosed are an installation safeguard and a turbomachine comprising the casing.

84. 发明授权

US09650918B2 Austenitic segment for steam turbine nozzle assembly, and related assembly 有权
公开(公告)号：US09650918B2
公开(公告)日：2017-05-16
申请号：US14584417
申请日：2014-12-29
申请人： General Electric Company
发明人： Steven Sebastian Burdgick , Salvador Mata Lopez
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F05D2220/31
摘要： An austenitic segment for a steam turbine nozzle assembly, along with related assemblies. Various embodiments include a steam turbine austenitic ring segment having: a body portion sized to substantially fill a pocket in a steam turbine outer diaphragm ring, the body portion having a greater circumferential length than an axial depth or a radial width thereof; and a hook-shaped portion extending radially inward from the body portion, the hook-shaped portion sized to engage a hook-shaped slot in the steam turbine outer diaphragm ring, wherein the body portion and the hook-shaped portion form a unitary structure.

85. 发明申请

US20170058684A1 TURBINE BAND ANTI-CHORDING FLANGES 审中-公开
标题翻译：涡轮带防反击法兰
公开(公告)号：US20170058684A1
公开(公告)日：2017-03-02
申请号：US14706003
申请日：2015-05-07
申请人： General Electric Company
发明人： Victor Hugo Silva CORREIA , Brian Kenneth CORSETTI , Mark BROOMER
IPC分类号： F01D9/04 , F01D25/00 , F01D25/10
CPC分类号： F01D9/041 , F01D9/04 , F01D25/005 , F01D25/10 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/91 , F05D2250/185 , F05D2260/2212 , F05D2260/22141 , F05D2260/941 , F05D2300/50212
摘要： A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.
摘要翻译：燃气涡轮发动机弓形段包括弓形凸缘，其具有远离环形壁延伸的抗弦装置。抗弦装置可以包括插入或结合到凸缘并且由环形壁不同的α材料制成。抗弦装置可以是用于加热法兰的加热装置。加热装置包括从嵌入凸缘中的周向延伸的加热流动通道到出口和出口，并且还可以包括用于加热流动通道的冷空气入口。加热流路可以是具有起伏加热流路的蛇形加热流路。涡轮喷嘴段包括在内和外弓形带段之间径向延伸的一个或多个翼型件，并且从外弧形带段径向延伸的前后外凸缘包括防弦装置。弓形涡轮机护罩段包括具有防弦装置的前后导轨段。

86. 发明申请

US20170044917A1 SEALING ATTACHMENT FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：密封用于燃气涡轮发动机的附件
公开(公告)号：US20170044917A1
公开(公告)日：2017-02-16
申请号：US15222025
申请日：2016-07-28
申请人： ROLLS-ROYCE plc
发明人： Simon L. JONES
IPC分类号： F01D11/00 , F01D25/28 , F01D25/24
CPC分类号： F01D11/005 , F01D25/246 , F05D2250/711 , F05D2250/75 , F05D2260/37 , F05D2260/38
摘要： A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.
摘要翻译：一种燃气轮机，包括：壁部件，其具有包围所述主气体路径的气体相对表面; 公阳密封附件，具有阳或阴部件，其中：阳部件包括具有主体的部件，其具有在共同方向上延伸的第一和第二臂以及中线平面的任一侧，其中所述臂相对于所述中线平面呈凸形弯曲，从而沿所述臂的长度提供接触部分，所述接触部分最远离所述中线平面; 并且，所述阴部件包括具有主体的部件，所述部件包括在共同的方向和中线平面的任一侧从其延伸的第一臂和第二臂，其中所述第一臂和所述第二臂相对于中线平面，以便沿着臂的长度提供接触部分，接触部分最靠近中线平面。

87. 发明授权

US09562441B2 Turbo machine with a device for preventing a segment of nozzle guide vanes assembly from rotating in a casing; rotation-proofing peg 有权
标题翻译：具有用于防止喷嘴导向叶片组件的一部分在壳体中旋转的装置的涡轮机; 防旋转钉
公开(公告)号：US09562441B2
公开(公告)日：2017-02-07
申请号：US13700641
申请日：2011-05-31
申请人： Thierry Michel Breugnot , Didier Noel Durand , Florence Irene Noelle Leutard
发明人： Thierry Michel Breugnot , Didier Noel Durand , Florence Irene Noelle Leutard
IPC分类号： F01D25/08 , F01D25/24
CPC分类号： F01D25/08 , F01D25/246 , F05D2230/64 , F05D2230/642 , F05D2240/11 , F05D2250/70 , F05D2260/30 , F05D2260/94 , F05D2260/941
摘要： A device for preventing rotation of a segment of nozzle guide vanes assembly in a form of an annulus sector housed inside an annular casing of a turbo machine with interposing of a heat shield sheet between an internal wall of the casing and an external wall of the segment of nozzle guide vanes assembly, the device including a rotation-proofing peg fitted both into a notch formed in the segment of nozzle guide vanes assembly and in a housing formed in the casing, the heat shield sheet including a tab resting against the rotation-proofing peg. A surface portion radially between the tab and the internal wall of the casing forms an end stop in event of a possible radial movement of the heat shield sheet while the turbo machine is in operation.
摘要翻译：一种用于防止喷嘴导向叶片组件的一部分旋转的装置，该喷嘴导向叶片组件形成为容纳在涡轮机的环形壳体内的环形扇形的形式，其中隔热片插入在壳体的内壁和节段的外壁之间的喷嘴导向叶片组件，该装置包括安装在喷嘴导向叶片组件的段中形成的切口和形成在壳体中的壳体中的防旋转栓，该热屏蔽片包括防止旋转防撞的突片钉住当涡轮机运行时，翼片和壳体的内壁之间的表面部分形成端部挡块，以防止隔热片可能的径向移动。

88. 发明申请

US20170022842A1 GAS TURBINE ENGINES INCLUDING CHANNEL-COOLED HOOKS FOR RETAINING A PART RELATIVE TO AN ENGINE CASING STRUCTURE 有权
标题翻译：气体涡轮发动机，包括用于保持与发动机结构相关的部件的通道冷却钩
公开(公告)号：US20170022842A1
公开(公告)日：2017-01-26
申请号：US14807703
申请日：2015-07-23
申请人： United Technologies Corporation
发明人： BRANDON W. SPANGLER
IPC分类号： F01D25/12 , F01D25/14
CPC分类号： F01D25/12 , F01D9/042 , F01D25/14 , F01D25/246 , F05D2260/22141
摘要： A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.
摘要翻译：提供燃气涡轮发动机。燃气涡轮发动机包括发动机壳体结构和通过通道冷却的钩相对于发动机壳体结构保持的部分。通道冷却的钩包括钩冷却通道的至少一部分。还提供了一种用于燃气涡轮发动机的叶片组件。

89. 发明授权

US09551238B2 Pin connector for ceramic matrix composite turbine frame 有权
标题翻译：陶瓷基体复合式汽轮机架的接头连接器
公开(公告)号：US09551238B2
公开(公告)日：2017-01-24
申请号：US13723499
申请日：2012-12-21
申请人： United Technologies Corporation
发明人： Hoyt Y. Chang , Shelton O. Duelm
IPC分类号： F01D25/28 , F01D25/24
CPC分类号： F01D25/28 , F01D25/246 , F05D2300/6033 , Y02T50/672 , Y10T403/217
摘要： A connector between a first object having a first coefficient of thermal expansion and a second object having a second coefficient of thermal expansion has a slot attaching to the second object. The slot formed by an inner shell having a slot shape and a first portion that blends into an outer surface of the second object, the slot having an enclosed portion facing forward and an aft portion that is open.
摘要翻译：具有第一热膨胀系数的第一物体和具有第二热膨胀系数的第二物体之间的连接器具有连接到第二物体的槽。由具有槽形状的内壳和与第二物体的外表面共混的第一部分形成的槽，槽具有面向前的封闭部分和敞开的后部。

90. 发明申请

US20170016341A1 SHROUD ASSEMBLY FOR GAS TURBINE ENGINE 审中-公开
标题翻译：气动涡轮发动机SHROUD装配
公开(公告)号：US20170016341A1
公开(公告)日：2017-01-19
申请号：US14797240
申请日：2015-07-13
申请人： General Electric Company
发明人： David Scott Stapleton , Bryce Loring Heitman , Laura Isabelle Armanios
IPC分类号： F01D11/08 , F01D25/00 , F02C3/04 , F01D9/04
CPC分类号： F01D11/08 , F01D9/04 , F01D9/042 , F01D11/18 , F01D25/005 , F01D25/246 , F02C3/04 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/35 , F05D2260/30 , F05D2260/31 , F05D2300/10 , F05D2300/6033 , Y02T50/672
摘要： Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.
摘要翻译：提供了用于燃气涡轮发动机的护罩组件。护罩组件包括具有前衣架臂，后衣架臂和在前衣架臂和后衣架臂之间延伸的衣架主体的衣架。护罩组件还包括具有前表面，后表面以及在前表面和后表面之间延伸的内表面和外表面的护罩，外表面与内表面径向间隔开，护罩连接到衣架。所述护罩组件还包括位于所述前悬挂臂的轴向前方的支撑构件，所述支撑构件具有连接到所述前悬挂臂的径向外部，以及与所述护罩轴向间隔开的径向内部，使得在径向内部部分和护罩的轴向相邻表面。

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