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1. 发明申请

WO2019046006A1 ADVANCED GEOMETRY PLATFORMS FOR TURBINE BLADES 审中-公开
公开(公告)号：WO2019046006A1
公开(公告)日：2019-03-07
申请号：PCT/US2018/046612
申请日：2018-08-14
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MARTIN, Nicholas F. Jr. , WIEBE, David J.
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F05D2230/60 , F05D2240/80
摘要： A blade assembly for a turbine includes an airfoil (10), a root (62) and a platform (52). The platform (52) is positioned radially between the airfoil (10) and the root (62). An airfoil fillet (16) joins the airfoil (10) to an upper surface (56) of the platform (52). A suction side mate face (22) of the platform (52) mates with a pressure side mate face (24) of a similar adjacent platform (52) along a platform mate face angle (26) that substantially aligns with a camber line (68) in relation to an axial direction (A). A method of attaching blades to a rotor assembly is also disclosed.

2. 发明申请

WO2016133514A1 TURBINE AIRFOIL WITH DUAL WALL CONSTRUCTION 审中-公开
标题翻译：具有双层结构的涡轮机
公开(公告)号：WO2016133514A1
公开(公告)日：2016-08-25
申请号：PCT/US2015/016492
申请日：2015-02-19
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： WIEBE, David J.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/189
摘要： The present disclosure provides an airfoil (11) comprising an airfoil main body (12) and at least one inner wall (38). The airfoil main body (12) includes an outer wall (18) defining leading and trailing edges (20, 22), pressure and suction sides (24, 26), a radially inner end (28), and a radially outer tip (30); a main airfoil cavity (32); and a plurality of ribs (34a-e). The inner wall (38), which is located in the main airfoil cavity (32), extends generally parallel to an inner surface (19) of the outer wall (18) and extends radially between the radially inner end (28) and the radially outer tip (30). The inner wall (38) is structurally independent of the outer all (18) and the plurality of ribs (34a-e) such that the inner wall (38) is uncoupled from and movable relative to the airfoil main body (12).
摘要翻译：本公开提供了一种包括翼型件主体（12）和至少一个内壁（38）的翼型件（11）。机翼主体（12）包括限定前缘和后缘（20,22），压力和吸力侧（24,26），径向内端（28）和径向外端（30）的外壁（18））; 主翼型腔（32）; 和多个肋（34a-e）。位于主翼型腔（32）中的内壁（38）大致平行于外壁（18）的内表面（19）延伸，并且在径向内端（28）和径向内端外端（30）。内壁（38）在结构上独立于外部全部（18）和多个肋（34a-e），使得内壁（38）相对于翼型件主体（12）脱离并可移动。

3. 发明申请

WO2016195657A1 LOCKING SPACER ASSEMBLY BETWEEN COMPRESSOR BLADE STRUCTURES IN A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机中压缩机叶片结构之间的隔离间隔装置
公开(公告)号：WO2016195657A1
公开(公告)日：2016-12-08
申请号：PCT/US2015/033637
申请日：2015-06-02
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： WIEBE, David J.
IPC分类号： F01D5/32 , F01D5/30
CPC分类号： F01D5/32 , F01D5/3038
摘要： A locking spacer assembly in a gap between adjacent blade structures (22) in a turbine engine includes opposed side edge members(48,50), opposed end members (100,102), and a cap member (130). The side edge members include a recessed portion along a top surface thereof and define a groove along an inner edge. The end members include opposed tongue members that are received within the grooves of the respective side edge members to prevent radial movement of the end members relative to the side edge members. The end members further include a projection extending from an inner edge thereof toward the opposed end member. The cap member is received by the recessed portions of the side edge members, wherein rotation of the cap member causes notches of the cap member to receive the projections of the end members to prevent radial movement of the cap member relative to the end members.
摘要翻译：在涡轮发动机中的相邻叶片结构（22）之间的间隙中的锁定间隔件组件包括相对的侧边缘部件（48,50），相对的端部部件（100,102）和盖部件（130）。侧边缘构件包括沿着其顶表面的凹陷部分，并且沿着内边缘限定凹槽。端部构件包括相对的舌状构件，其接收在相应的侧边缘构件的凹槽内，以防止端部构件相对于侧边缘构件的径向移动。端部构件还包括从其内边缘朝向相对的端部构件延伸的突起。盖构件被侧边缘构件的凹部接收，盖构件的旋转引起盖构件的凹口接纳端构件的突起，以防止盖构件相对于端构件的径向移动。

4. 发明申请

WO2014137696A2 COMBUSTOR APPARATUS IN A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机中的燃烧器装置
公开(公告)号：WO2014137696A2
公开(公告)日：2014-09-12
申请号：PCT/US2014/018608
申请日：2014-02-26
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： WIEBE, David J. , RAMIER, Stephen A. , BARTLEY, Robert H. , GARAN, Daniel W. , DEANE, Erick J. , ADAMSON, Mark L. , NAGHIAN, Yadollah
IPC分类号： F23R3/28
CPC分类号： F23R3/28 , F02C7/22 , F02C7/222 , F05D2300/50211 , F05D2300/50212 , F05D2300/506 , F16L13/007 , F16L15/006 , F16L19/061 , F16L25/0072 , F16L41/084 , F16L41/086 , F23K2301/20 , F23R3/283 , F23R3/286 , F23R3/34 , F23R2900/00005
摘要： A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.
摘要翻译：燃烧器装置限定了燃烧区域，其中空气和燃料被燃烧以产生高温燃烧产物。燃烧器装置包括外壁，与其燃料入口相邻的外壁上的联接结构，燃料喷射系统，燃料供给组件和配件构件。燃料喷射系统提供在燃烧区域燃烧的燃料。燃料供给结构包括由第一材料形成的螺纹内表面。所述燃料供给组件包括燃料供给管，所述燃料供给管延伸穿过所述外壁中的所述燃料入口，并且具有由所述第一材料形成并与所述燃料供给结构螺纹接合的出口部，以及固定到所述出口部的入口部并由第二材料形成。装配构件相对于外壁固定燃料供给组件。

5. 发明申请

WO2015026534A1 BELLY BAND SEAL WITH CIRCUMFERENTIAL SPACER 审中-公开
标题翻译：贝壳密封与圆形间隔
公开(公告)号：WO2015026534A1
公开(公告)日：2015-02-26
申请号：PCT/US2014/050111
申请日：2014-08-07
申请人： SIEMENS ENERGY, INC.
发明人： WIEBE, David J.
IPC分类号： F01D11/00 , F01D5/06 , F02C7/28
CPC分类号： F01D11/08 , F01D5/06 , F01D5/066 , F01D11/003 , F01D11/005 , F01D11/008 , F02C7/28
摘要： A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other.
摘要翻译：周向延伸的密封带位于形成在相邻的涡轮引擎盘中的密封带接收槽内。密封带包括形成由重叠端部限定的重叠接头的多个密封条，每个密封条由从一个密封条的密封面延伸穿过相邻密封条的密封面的舌部形成，该舌部沿着径向向内的侧面相邻密封条。在一个密封条的密封面和相邻条的密封面之间的至少一个重叠接合部内限定接合间隙，并且间隔件被固定到一个密封条上，并且位于第一密封条之间的接合间隙内的位置密封面面对以限制密封面朝向彼此的周向移动。

6. 发明申请

WO2017074373A1 COMPOSITE METALLIC AND CERAMIC GAS TURBINE ENGINE BLADE 审中-公开
标题翻译：复合金属和陶瓷燃气轮机发动机叶片
公开(公告)号：WO2017074373A1
公开(公告)日：2017-05-04
申请号：PCT/US2015/057945
申请日：2015-10-29
申请人： SIEMENS ENERGY, INC.
发明人： WIEBE, David J. , LANDRUM, Evan C.
IPC分类号： B23P6/00 , B22F3/105 , B22F5/04 , B22F7/06 , F01D5/00 , F01D5/20 , F01D5/28 , B23K26/342
CPC分类号： B23P6/002 , B22F3/1055 , B22F5/04 , B22F7/062 , B23K15/0086 , B23K15/0093 , B23K26/342 , B23K2201/001 , B23K2203/26 , F01D5/005 , F01D5/147 , F01D5/20 , F01D5/282 , F01D5/284 , F05D2230/23 , F05D2240/303 , F05D2240/307 , F05D2260/36 , F05D2300/6033 , Y02P10/295
摘要： Composite metallic-ceramic construction blades (30) for gas turbine engine compressor or turbine sections. A ceramic splice component, such as a squealer or other blade tip (40), or leading edge (184), mechanically interlocks with a metallic blade body (38), including a superalloy blade body. In the embodiment of FIGs. 1-4, the respective interlocking mechanical joint portion ramped, opposed surfaces (44, 46, and 56) are subsequently held in an interlocked position by a separately applied and independent metallic retainer member (50). The retainer member (50) is external the mechanical joint portion ramped, opposed surfaces (44, 46 and 56). Methods for manufacture of such composite blades are also useful for repair or retrofitting of non-composite, metallic blades.
摘要翻译：用于燃气涡轮发动机压缩机或涡轮机部分的复合金属陶瓷结构叶片（30）。陶瓷拼接部件（例如凹槽或其他刀片尖端（40）或前缘（184））与包括超级合金刀片主体的金属刀体（38）机械地互锁。在图1和2的实施例中，如图1-4所示，相应的互锁机械接头部分倾斜的相对表面（44,46和56）随后通过单独施加且独立的金属保持器构件（50）保持在互锁位置。保持器构件（50）在机械接头部分的倾斜的相对表面（44,46和56）的外部。制造这种复合材料刀片的方法也可用于修复或改造非复合材料金属刀片。

7. 发明申请

WO2017074372A1 METHOD FOR MANUFACTURING AND REPAIRING A COMPOSITE CONSTRUCTION TURBINE BLADE 审中-公开
标题翻译：制造和修复复合建筑涡轮叶片的方法
公开(公告)号：WO2017074372A1
公开(公告)日：2017-05-04
申请号：PCT/US2015/057936
申请日：2015-10-29
申请人： SIEMENS ENERGY, INC.
发明人： WIEBE, David J. , LANDRUM, Evan C.
IPC分类号： B23P6/00 , F01D5/00 , F01D5/20 , F01D5/28 , B22F3/105 , B22F5/04 , B22F7/06 , B23K26/342
CPC分类号： B23P6/002 , B22F3/1055 , B22F5/04 , B22F7/08 , B22F2007/068 , B23K2201/001 , B33Y10/00 , B33Y80/00 , F01D5/005 , F01D5/147 , F01D5/20 , F01D5/284 , F05D2240/303 , F05D2240/307 , F05D2260/37 , F05D2300/6033
摘要： Methods for manufacture of composite construction blades (30) for gas turbine engine compressor or turbine sections. A splice component (42), such as a squealer or other blade tip (40), or leading edge (184), or repair splice mechanically interlocks with a metallic blade body (38), including a superalloy blade body. In the embodiment of FIGs. 1-4 the respective interlocking mechanical joints ramped, opposed surfaces (44, 46, and 56) are subsequently held in an interlocked position by a separately formed and applied, independent metallic retainer member (50). The retainer member (50) is external the mechanical joint portion ramped, opposed surfaces (44, 46 and 56) and is formed by a sequential-layer material addition, additive manufacturing method. The methods are also useful for repair or retrofitting of non-composite, metallic blades end caps, leading edges, or other damaged structure.
摘要翻译：用于制造用于燃气涡轮发动机压缩机或涡轮部分的复合建筑叶片（30）的方法。诸如凹槽或其他刀尖（40）或前缘（184）或修理接头的拼接组件（42）与包括超级合金刀片主体的金属刀体（38）机械地互锁。在图1和2的实施例中，在图1-4的实施例中，相应的互锁机械接头倾斜，相对表面（44,46和56）随后通过单独形成和施加的独立金属保持器构件（50）保持在互锁位置。保持构件（50）在机械接头部分的倾斜相对表面（44,46和56）的外部，并且通过顺序层材料添加，增量制造方法形成。该方法也可用于修复或改造非复合材料，金属叶片端盖，前缘或其他受损结构。

8. 发明申请

WO2016148695A1 TURBINE AIRFOIL WITH INTERNAL COOLING SYSTEM HAVING NEARWALL COOLING CHANNELS FORMED FROM AN INNER WALL FORMED SEPARATELY FROM AN OUTER WALL FORMING THE TURBINE AIRFOIL 审中-公开
标题翻译：具有内部冷却系统的涡轮机空气具有从外壁形成的内壁冷却通道从外壁分离形成涡轮机空气
公开(公告)号：WO2016148695A1
公开(公告)日：2016-09-22
申请号：PCT/US2015/020921
申请日：2015-03-17
申请人： SIEMENS ENERGY, INC.
发明人： RODRIGUEZ, Jose L. , WIEBE, David J. , JAMES, Allister William , MERRILL, Gary B.
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F05D2230/644
摘要： An airfoil (10) for a gas turbine engine is disclosed in which the airfoil (10) includes an internal cooling system (14) formed from one or more midchord cooling channels (16) with at least one inner wall (18) positioned within the midchord cooling channel (16) forming a nearwall cooling channel (20). The inner wall (18) may be held in place with an inner wall connection system (22). The inner wall connection system (22) may be configured such that the inner wall (18) can slide spanwise and may have a limited degree of freedom to move towards a pressure or suction side (26, 28), or both. With the inner wall (18) being positioned within the airfoil (10) and not being rigidly connected to the airfoil (10), there exists little, if any, thermal stress between the inner wall (18) and the outer wall (30) forming the airfoil (10). The inner wall (18) may be formed via a bi-cast process in which the inner wall (18) has a higher melting point than the airfoil (10).
摘要翻译：公开了一种用于燃气涡轮发动机的翼型件（10），其中翼型件（10）包括由一个或多个中间冷却通道（16）形成的内部冷却系统（14），其中至少一个内壁（18）位于形成近壁冷却通道（20）的中间冷却通道（16）。内壁（18）可以用内壁连接系统（22）保持就位。内壁连接系统（22）可以被构造成使得内壁（18）能够翼展地滑动，并且可以具有朝向压力或吸力侧（26,28）或两者移动的有限的自由度。在内壁（18）定位在翼型件（10）内并且不刚性地连接到翼型件（10）的情况下，内壁（18）和外壁（30）之间的热应力几乎不存在，形成翼型件（10）。内壁（18）可以通过双壁铸造工艺形成，其中内壁（18）具有比翼型（10）更高的熔点。

9. 发明申请

WO2016010554A1 TURBINE ASSEMBLY WITH DETACHABLE STRUTS 审中-公开
标题翻译：涡轮组件与可拆卸的钢筋混合
公开(公告)号：WO2016010554A1
公开(公告)日：2016-01-21
申请号：PCT/US2014/047179
申请日：2014-07-18
申请人： SIEMENS ENERGY, INC.
发明人： WIEBE, David J. , KATY, Jerome H. , SELESKI, Richard , HETTINGER, Benjamin G. , WALLACE, Adam
IPC分类号： F01D25/16 , F01D25/28 , F01D9/06
CPC分类号： F01D25/28 , F01D9/065 , F01D25/162 , F05D2240/14 , F05D2260/30 , F05D2260/31
摘要： A turbine assembly having an outer casing (36), an inner structural ring (38), and an annular gas path (42) defined between outer and inner flow path walls (44, 46) for conducting a gas flow through the turbine assembly. A plurality of structural struts (52) are spaced apart in a circumferential direction, each strut (52) including a strut body (52a) extending in a radial direction for supporting the inner structural ring (38) to the outer casing (36). A first strut end (64) at a radially outer end of the strut body (52a) is detachably attached to the outer casing (36) with a first fastener structure (68) engaging the outer casing (36), and a second strut end (66) at a radially inner end of the strut body (52a) is detachably attached to the inner structural ring (38) with a second fastener structure (70) engaging the inner structural ring (38).
摘要翻译：一种具有外壳（36），内结构环（38）和限定在外流路壁（44,46）之间的环形气体通道（42）的涡轮机组件，用于传导气流通过涡轮组件。多个结构支柱（52）沿圆周方向间隔开，每个支柱（52）包括沿径向延伸的支柱体（52a），用于将内结构环（38）支撑到外壳（36）。在支柱主体（52a）的径向外端处的第一支柱端（64）通过与外壳（36）接合的第一紧固件结构（68）可拆卸地附接到外壳（36），并且第二支柱端支柱主体（52a）的径向内端部（66）通过与内部结构环（38）接合的第二紧固件结构（70）可拆卸地附接到内部结构环（38）。

10. 发明申请

WO2017127255A1 TRANSITION DUCT SYSTEM WITH STRAIGHT CERAMIC LINER FOR DELIVERING HOT-TEMPERATURE GASES IN A COMBUSTION TURBINE ENGINE 审中-公开
标题翻译：燃烧涡轮发动机中用于输送热温度气体的带有直式陶瓷衬套的过渡管道系统
公开(公告)号：WO2017127255A1
公开(公告)日：2017-07-27
申请号：PCT/US2017/012792
申请日：2017-01-10
申请人： SIEMENS ENERGY, INC.
发明人： WIEBE, David J.
IPC分类号： F01D9/02 , F23R3/42
CPC分类号： F01D9/023 , F05D2260/30 , F05D2260/941 , F05D2300/20 , F23R3/007 , F23R3/425
摘要： A transition duct system (10) for delivering hot-temperature gases from a plurality of combustors in a combustion turbine engine is provided. The system includes an exit piece (16) for each combustor. The exit piece may include a straight path segment (26) for receiving a gas flow from a respective combustor. A straight ceramic liner (40) may be inwardly disposed onto a metal outer shell (38) along the straight path segment of the exit piece. Structural arrangements are provided to securely attach the ceramic liner in the presence of substantial flow path pressurization. Cost-effective serviceability of the transition duct systems is realizable since the liner can be readily removed and replaced as needed.
摘要翻译：提供了一种用于输送来自燃气涡轮发动机中的多个燃烧器的热温度气体的过渡管道系统（10）。该系统包括用于每个燃烧器的出口件（16）。出口件可以包括用于接收来自相应燃烧器的气流的直路段（26）。直陶瓷衬里（40）可沿着出口件的直线路径段向内设置在金属外壳（38）上。提供结构布置以在存在大量流动路径加压的情况下牢固地附接陶瓷衬里。过渡管道系统的经济有效的可维护性是可以实现的，因为可以根据需要容易地移除和更换衬管。

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