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1. 发明申请

WO2020023005A1 COVER PLATE WITH FLOW INDUCER AND METHOD FOR COOLING TURBINE BLADES 审中-公开
公开(公告)号：WO2020023005A1
公开(公告)日：2020-01-30
申请号：PCT/US2018/043286
申请日：2018-07-23
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： SCHRÖDER, Peter , ROSS, Christopher W. , SALAZAR, Santiago R. , PILAPIL, Patrick M. , MATTHEWS, Roger , KAMPKA, Kevin , VERHEYEN, Joana , LEE, Ching-Pang , ALBRIGHT, Javan , MCCOY, James , SIW, Sin Chien , THAM, Kok-Mun
IPC分类号： F01D5/08 , F01D5/30
摘要： The gas turbine engine includes a rotor disk (120) having circumferentially distributed disk grooves (122) and turbine blades (140). Each turbine blade (140) includes a blade root (144) inserted into the blade mounting section (124) of the disk groove (122). Seal plates (200) are attached to an aft side circumference of the rotor disk (120). The flow inducer assembly (300) is integrated to each seal plate (200) at a side facing away from the rotor disk (120). The flow inducer assembly (300) is configured to function as a paddle due to rotation of the rotor disk and the seal plate therewith during operation of the gas turbine engine to drive ambient air as a cooling fluid into the disk cavity and enter inside of the turbine blade from the blade root for cooling the turbine blade.

2. 发明申请

WO2020023007A1 COVER PLATE WITH FLOW INDUCER AND METHOD FOR COOLING TURBINE BLADES 审中-公开
公开(公告)号：WO2020023007A1
公开(公告)日：2020-01-30
申请号：PCT/US2018/043298
申请日：2018-07-23
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： SCHRÖDER, Peter , KAMPKA, Kevin , ROSS, Christopher W. , SALAZAR, Santiago R. , PILAPIL, Patrick M. , MATTHEWS, Roger , VERHEYEN, Joana
IPC分类号： F01D5/08 , F01D5/30
摘要： The gas turbine engine includes a rotor disk 120 having circumferentially distributed disk grooves 122 and turbine blades 140. Each turbine blade 140 includes a blade root 144 inserted into the blade mounting section 124 of the disk groove 122. Seal plates 200 are attached to an aft side circumference of the rotor disk 120. The flow inducer assembly 300 is manufactured as a separate piece and is mountable to the seal plate 200 or rotor disk 120. The flow inducer assembly 300 when mounted is functioned as a paddle due to rotation of the rotor disk during operation of the gas turbine engine to induce ambient air as a cooling fluid into the disk cavity for cooling the turbine blade. The flow inducer assembly is removable from the seal plate or rotor disk which provides flexibility for using different cooling sources to cool the turbine blade.

3. 发明申请

WO2014126760A1 HEAT RETENTION AND DISTRIBUTION SYSTEM FOR GAS TURBINE ENGINES 审中-公开
标题翻译：气体涡轮发动机的保温和分配系统
公开(公告)号：WO2014126760A1
公开(公告)日：2014-08-21
申请号：PCT/US2014/014824
申请日：2014-02-05
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LIGHT, Kevin M. , ROSS, Christopher W.
IPC分类号： F01D5/08 , F01D25/10 , F04D29/58 , F01D11/24
CPC分类号： F02C7/08 , F01D5/08 , F01D11/24 , F01D25/10 , F05D2260/20 , F05D2260/85
摘要： A gas turbine engine including a compressor section, a combustor section, and a turbine section operating to produce a power output during a first mode of operation. A heat retention and distribution system is provided to the engine wherein the heat retention system operates in a second mode of operation, following a shutdown of the engine, to maintain an elevated temperature in components of each of the compressor section, the combustor section and the turbine section in order to effect (1) a reduction in an effective cyclic life consumption of the components and extend a maintenance interval associated with the effective cyclic life consumption, and (2) clearances by maintaining a higher vane carrier temperature with time during a non-power producing mode and more uniform temperature of most stationary components in the circumferential orientation
摘要翻译：一种燃气涡轮发动机，包括压缩机部分，燃烧器部分和在第一操作模式期间产生功率输出的涡轮部分。发动机提供保温分配系统，其中在发动机关闭之后，保温系统在第二操作模式下操作，以在压缩机部分，燃烧器部分和涡轮机部分，以实现（1）减少部件的有效循环寿命消耗并延长与有效循环寿命消耗相关联的维护间隔，以及（2）通过在非涡轮机非零时保持较高的叶片载体温度随时间而增加间隙大多数固定部件在圆周方向上的功率生产模式和更均匀的温度

4. 发明申请

WO2015130497A1 THERMAL SHIELDS FOR GAS TURBINE ROTOR 审中-公开
标题翻译：用于气体涡轮转子的热风炉
公开(公告)号：WO2015130497A1
公开(公告)日：2015-09-03
申请号：PCT/US2015/015996
申请日：2015-02-16
申请人： SIEMENS ENERGY, INC.
发明人： ROSS, Christopher W. , ACAR, Bulent
IPC分类号： F01D5/06 , F01D5/08 , F01D11/00
CPC分类号： F01D5/082 , F01D5/06 , F01D5/085 , F01D11/006 , F01D25/12 , F05D2240/24 , F05D2250/75
摘要： A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk. A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk. A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
摘要翻译：一种涡轮机，其包括具有轴线的转子和在轴向方向上彼此相邻定位的多个盘，每个盘包括相对的轴向相对表面和位于轴向相对表面之间的周向延伸的径向面对的表面。至少一排叶片位于每个盘上，并且叶片包括从盘径向向外延伸的翼型件。非分段的周向连续的环形结构包括限定在至少一个盘的径向面向表面的一部分上以重叠关系轴向延伸并且延伸到与盘上的刀片相邻的位置的热障壁的外缘。柔性元件位于环形结构的径向内周部分和从盘的轴向面向轴向延伸的凸缘结构之间。

5. 发明申请

WO2013130309A1 MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE 审中-公开
标题翻译： CAN-ANNULAR气体涡轮发动机的中间部分，从压缩机到涡轮机的空气流改进
公开(公告)号：WO2013130309A1
公开(公告)日：2013-09-06
申请号：PCT/US2013/026776
申请日：2013-02-20
申请人： SIEMENS ENERGY, INC. , LITTLE, David A. , SCHILP, Reinhard , ROSS, Christopher W.
发明人： LITTLE, David A. , SCHILP, Reinhard , ROSS, Christopher W.
IPC分类号： F01D9/02 , F02C3/14
CPC分类号： F01D9/023 , F02C3/14 , F02C3/145 , F23R3/425
摘要： A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
摘要翻译：呈现燃气涡轮发动机（310）的中架部分（313）并且包括具有最后级叶片的压缩机部分，以使空气流（311）以第一角度（372）定向。中间部分（313）还包括具有第一级叶片的涡轮机部分，以接收以第二角度（374）定向的空气流（311）。中间部分（313）还包括歧管（314），用于将空气流（311）从压缩机部分直接耦合到涡轮部分上游的燃烧器头部（318）。燃烧器头部（318）将空气流（311）中的偏移角从第一角度（372）引入第二角度（374），以使空气流（311）以第二角度从燃烧器头部（318）排出（374）。在引入偏移角的同时，燃烧器头（318）至少保持或增加第一角度（372）。

6. 发明公开

EP3111047A1 THERMAL SHIELDS FOR GAS TURBINE ROTOR 审中-公开
标题翻译： THERMISCHE ABSCHIRMUNGENFÜRGASTURBINENROTOR
公开(公告)号：EP3111047A1
公开(公告)日：2017-01-04
申请号：EP15706354.6
申请日：2015-02-16
申请人： Siemens Energy, Inc.
发明人： ROSS, Christopher W. , ACAR, Bulent
IPC分类号： F01D5/06 , F01D5/08 , F01D11/00
CPC分类号： F01D5/082 , F01D5/06 , F01D5/085 , F01D11/006 , F01D25/12 , F05D2240/24 , F05D2250/75
摘要： A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
摘要翻译：一种涡轮机，包括具有轴线的转子和在轴向方向上彼此相邻定位的多个盘，每个盘包括相对的轴向面对的表面和位于轴向相对表面之间的周向延伸的径向对置的表面。至少一排叶片被定位在每个盘上，并且叶片包括从盘A径向向外延伸的翼型件。非分段的周向连续的环形结构包括外缘，该外缘限定了以重叠关系在一部分上的轴向轴向延伸的热障壁至少一个盘的径向面向表面并且延伸到与盘上的叶片相邻的位置。柔顺元件位于环形结构的径向内圆周部分和凸缘结构之间，凸缘结构从轴向面向表面轴向延伸的磁盘

7. 发明申请

WO2019040171A1 SEAL PLATE ASSEMBLY 审中-公开
公开(公告)号：WO2019040171A1
公开(公告)日：2019-02-28
申请号：PCT/US2018/038675
申请日：2018-06-21
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SCHRÖDER, Peter , ROSS, Christopher W. , GLOSS, Daniel , CHEHAB, Abdullatif M. , ARRELL, Douglas J. , SHREEDHARA, Swaroop , BAKER, Jonathon , HALCHAK, William
IPC分类号： F01D5/30 , F01D11/00 , F16J15/08
CPC分类号： F01D5/3015 , F01D11/005 , F01D11/006 , F05D2240/11 , F05D2240/57 , F05D2250/182 , F05D2260/36 , F05D2260/961 , F16J15/0887
摘要： The present invention is related to a seal plate assembly (300) for a rotor disk assembly (100) of a gas turbine engine, wherein the seal plate assembly includes a plurality of adjacent seal plate segments (320, 340). Shiplaps (322,323,342,343) of the adjacent seal plate segments are overlapped with each other. The overlapped shiplaps of the adjacent seal plate segments are configured to have different stiffness. The less stiff shiplaps deflect toward to the overlapped stiffer shiplaps such that the overlapped shiplaps move toward to each other under pressure differences. Stiffness may be varied by providing stiffeners (324,344) of different heights, providing grooves (310), modifying thickness of the shiplaps or combining any of these. The seal plate assembly improves sealing and reduces leakage of cooling air between the adjacent seal plate segments and improves efficiency of the gas turbine engine.

8. 发明申请

WO2019149474A1 ROTOR MIT DICHTELEMENT UND DICHTRING 审中-公开
公开(公告)号：WO2019149474A1
公开(公告)日：2019-08-08
申请号：PCT/EP2019/050247
申请日：2019-01-07
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SCHRÖDER, Peter , KOLK, Karsten , KURY, Peter , SPRINGBORN, Dirk , KAMPKA, Kevin , ROSS, Christopher W. , BAGAEVA, Yulia
IPC分类号： F01D5/02 , F01D5/06 , F01D5/30 , F01D5/32 , F01D11/00
CPC分类号： F01D5/3015 , F01D5/025 , F01D5/066 , F01D5/3007 , F01D5/326 , F01D11/00 , F05D2230/60 , F05D2240/55 , F05D2240/58
摘要： Die Erfindung betrifft ein Dichtelement (21) und einen Rotor einer Gasturbine mit zumindest einer Rotorscheibe (01) und mit einem ringförmigen benachbart zur Rotorscheibe (01) angeordneten Rotorbauteil (11) und mit einer Mehrzahl im Umfang verteilt angeordneter Dichtelemente (21). Die Dichtelemente (21) sind zumindest in axialer Richtung an der Rotorscheibe (01) befestigt. Ein jeweils innerer Randabschnitt (23) der Dichtelemente (21) grenzt an einen Dichtabschnitt (13) des Rotorbauteils (11) an. Zur Abdichtung zwischen Dichtelement (21) und Rotorbauteil (11) bei Ermöglichung einer relativen axialen Verschiebung wird ein Dichtring (31) einem von Dichtelement (21) und Rotorbauteil (11) gebildeten Aufnahmeraum (14) angeordnet.

9. 发明申请

WO2020025406A1 ROTOR MIT ZWISCHEN ZWEI ROTORSCHEIBEN ANGEORDNETEM ROTORBAUTEIL 审中-公开
公开(公告)号：WO2020025406A1
公开(公告)日：2020-02-06
申请号：PCT/EP2019/069866
申请日：2019-07-24
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： KURY, Peter , HOELL, Harald , KOLK, Karsten , VEITSMAN, Vyacheslav , BAGAEVA, Yulia , ROSS, Christopher W. , SCHRÖDER, Peter , WADDELL, Andrew R.
IPC分类号： F01D5/30 , F01D11/00
摘要： Die Erfindung betrifft einen Rotor einer Gasturbine zwei benachbarten Rotorscheiben (01, 06), welche am Umfang verteilt eine Mehrzahl Schaufelhaltenuten (02) zur Aufnahme von Laufschaufeln und radial unterhalb der Schaufelhaltenuten (02) einen sich axial erstreckenden umlaufenden Ringvorsprung (03, 08) aufweisen. Zwischen den Rotorscheiben (01,06) an den Ringvorsprüngen (03, 08) befestigt befindet sich ein umlaufendes Rotorbauteil (11). Zur Umfangssicherung weist die Rotorscheibe (01) oder das Rotorbauteil (11) zumindest zwei am Umfang verteilt angeordnete Ausnehmungen (14) auf, in denen jeweils Eingriffsabsätze (15) des Rotorbauteils (11) bzw. der Rotorscheibe (01) eingreifen.

10. 发明公开

EP3161692A1 METHOD FOR ANALYSIS OF 3D FEATURES USING A 2D PROBABILISTIC ANALYSIS 审中-公开
标题翻译：用二维概率分析法分析三维特征的方法
公开(公告)号：EP3161692A1
公开(公告)日：2017-05-03
申请号：EP15811254.0
申请日：2015-06-22
申请人： Siemens Aktiengesellschaft
发明人： KADAU, Kai , ROSS, Christopher W. , PATEL, Chirag B. , AMANN, Christian
IPC分类号： G06F17/50 , G06T17/00 , F01D5/14
CPC分类号： G01L1/00 , G05B19/4065 , G05B23/0283 , G06F17/5009 , G06F17/5018 , G06F2217/10 , G06N7/005
摘要： A method for analyzing a three-dimensional stress concentrating feature of a component (60), such as a borehole (62), using a two-dimensional probabilistic technique. A circumferentially-dependent stress concentration profile around the stress concentrating feature is determined, and then a probability of failure of the component is calculated using a 2D probabilistic failure analysis of the stress concentration profile. The probabilistic failure analysis may include a Monte Carlo theta integration approach.
摘要翻译：一种用于使用二维概率技术来分析诸如钻孔（62）的部件（60）的三维应力集中特征的方法。确定应力集中特征周围的周向依赖应力集中轮廓，然后使用应力集中轮廓的2D概率失效分析来计算该部件的故障概率。概率失效分析可能包括蒙特卡洛theta集成方法。

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