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1. 发明申请

WO2020068109A1 MODULAR COOLING ARRANGEMENT FOR COOLING AIRFOIL COMPONENTS IN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2020068109A1
公开(公告)日：2020-04-02
申请号：PCT/US2018/053393
申请日：2018-09-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , FISCHLE, Moritz , MARSH, Jan H. , FU, Wentao , JAMES, Allister William , MILLER, Andrew , MITCHELL, David J.
IPC分类号： F01D5/14 , F01D5/28 , F01D9/04
摘要： A modular cooling arrangement for cooling an airfoil component (10) in a combustion turbine engine is provided. A body (16) of the airfoil component, and a cooling manifold (18) or a flow sleeve (50, 60) may be disposed in a cavity in the body of the airfoil component. By way of example, the body of the airfoil component may be a ceramic matrix composite body, a MAX phase ternary ceramic body, or a metallic body. Disclosed embodiments are effective to reliably and cost-effectively reduce a level of internal pressurization in the component while providing appropriate cooling to portions of the component subject to a hot flow of gases and accommodating thermal growth differences that may develop between components of the modular cooling arrangement and anchoring structures to which the modular cooling arrangement may be affixed.

2. 发明申请

WO2020068114A1 RING SEAL FORMED BY CERAMIC-BASED RHOMBOID BODY FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2020068114A1
公开(公告)日：2020-04-02
申请号：PCT/US2018/053429
申请日：2018-09-28
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , CAMPBELL, Christian Xavier , MITCHELL, David J. , GAMBLIN, David
IPC分类号： F01D11/00 , F01D25/24 , F01D5/28 , F01D25/00 , F01D9/04 , F01D11/08
摘要： A ring assembly in a gas turbine engine is provided. The ring seal assembly includes ring seal segments (50) supported by an interfit structure (52). Each ring seal segment is formed by a ceramic-based rhomboid body (54). A metal compression plate (58) is disposed against an inward surface (59) of a side (64) of the ceramic-based body spaced apart and opposite to a hot side (66) of the ring seal assembly. The metal compression plate is arranged to apply radially outward compression against the inward surface of the side (64) of the ceramic-based body. Disclosed embodiments are effective to reliably and cost-effectively make use of CMC and other high-temperature materials, such as MAX phase materials, in the environment of the gas turbine engine while accommodating thermal growth differences that may develop between the body of the ring seal and a metal casing on which the ring seal is disposed.

3. 发明申请

WO2017123207A1 THERMALLY CONDUCTIVE BUMPER ELEMENTS FOR A HYBRID AIRFOIL 审中-公开
标题翻译：混合式机翼的导热保温元件
公开(公告)号：WO2017123207A1
公开(公告)日：2017-07-20
申请号：PCT/US2016/012999
申请日：2016-01-12
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , JAMES, Allister William
IPC分类号： F01D5/18 , F01D5/26
CPC分类号： F01D5/188 , F01D5/189 , F01D5/26
摘要： An airfoil (30) for a turbine (10) wherein the airfoil (30) includes a core support structure (34) having a core outer surface (44) and a high heat resistant outer shell (32) having leading (36) and trailing (38) edges and high (40) and low (42) pressure surfaces. The outer shell (32) also includes a shell inner surface (46), wherein a portion of the core support structure (34) is located within the outer shell (32) and wherein the core outer surface (44) and shell inner surface (46) are separated by a surface gap (48). Further, the airfoil (30) includes at least one bumper element (56) located within the surface gap (48), wherein the at least one bumper element (56) provides a thermally conductive path for conducting heat from the outer shell (32) to the core support structure (34) and wherein the at least one bumper element (56) is flexible to absorb relative movement between the outer shell (32) and the core support structure (34) to reduce stress levels in the airfoil (30).
摘要翻译：一种用于涡轮机（10）的翼型件（30），其中翼型件（30）包括具有型芯外表面（44）和高耐热外壳（32）的型芯支撑结构（34））具有前缘（36）和后缘（38）以及高（40）和低（42）压力表面。外壳（32）还包括壳内表面（46），其中芯支撑结构（34）的一部分位于外壳（32）内，并且其中芯外表面（44）和壳内表面 46）被表面间隙（48）隔开。此外，翼型件（30）包括位于表面间隙（48）内的至少一个缓冲器元件（56），其中至少一个缓冲器元件（56）提供用于从外壳（32）传导热量的导热路径，（34），并且其中所述至少一个缓冲器元件（56）是柔性的以吸收所述外壳（32）和所述芯支撑结构（34）之间的相对运动，以减小所述翼型件（30）中的应力水平。

4. 发明申请

WO2017003458A1 HYBRID COMPONENT COMPRISING A METAL-REINFORCED CERAMIC MATRIX COMPOSITE MATERIAL 审中-公开
标题翻译：包含金属增强陶瓷基复合材料的混合组件
公开(公告)号：WO2017003458A1
公开(公告)日：2017-01-05
申请号：PCT/US2015/038574
申请日：2015-06-30
申请人： SIEMENS ENERGY, INC.
发明人： DYER, Zachary D. , SHINDE, Sachin R. , GRAVETT, Phillip W. , MORRISON, Jay A. , BROWN, Kimber-Lee
IPC分类号： F23R3/00 , F23R3/60
CPC分类号： F23R3/007 , F23R3/60 , F23R2900/00017
摘要： A hybrid metal-reinforced ceramic matrix composite (CMC) material component is provided having a body (12) including a ceramic matrix composite material (14) and a metal skeleton structure (18) encompassing at least a portion of the body (12). A retaining structure (20) carried by the metal skeleton structure (20) is further included to induce a compressive force on the body (12) to limit movement of the body (12) and the metal skeleton structure (18) relative to one another and enable the metal skeleton structure (18) to carry a greater amount of an external load than the body (12).
摘要翻译：提供了具有包括陶瓷基复合材料（14）的本体（12）和包围该主体（12）的至少一部分的金属骨架结构（18）的复合金属增强陶瓷基复合材料（CMC）材料部件。还包括由金属骨架结构（20）承载的保持结构（20）以在主体（12）上引起压缩力，以限制主体（12）和金属骨架结构（18）相对于彼此的运动并且使得金属骨架结构（18）能够承载比主体（12）更大的外部负载量。

5. 发明申请

WO2019240785A1 ATTACHMENT ARRANGEMENT FOR CONNECTING COMPONENTS WITH DIFFERENT COEFFICIENT OF THERMAL EXPANSION 审中-公开
公开(公告)号：WO2019240785A1
公开(公告)日：2019-12-19
申请号：PCT/US2018/037255
申请日：2018-06-13
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： DYER, Zachary D. , MARSH, Jan H. , LANDRUM, Evan C.
IPC分类号： F01D9/04 , F01D25/24
摘要： There is provided an arrangement (100) that includes a first component (102), a second component (104) having a greater coefficient of thermal expansion relative to the first component (102), and a pair of rails (126). Each rail (126) includes a channel (128) within a body (129) of the rail (126). An extent (124) of the first component (102) is retained within the channel (128). Each rail (126) is secured to the second component (104) to secure the first component (102) to the second component (104).

6. 发明申请

WO2019209267A1 CERAMIC MATRIX COMPOSITE COMPONENT AND CORRESPONDING PROCESS FOR MANUFACTURING 审中-公开
公开(公告)号：WO2019209267A1
公开(公告)日：2019-10-31
申请号：PCT/US2018/029117
申请日：2018-04-24
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： DYER, Zachary D. , GAMBLIN, David
IPC分类号： F01D5/28 , F01D5/18
摘要： There is provided a component (110) comprising a plurality of ceramic matrix composite members (111) stacked on one another to define an airfoil (116). The airfoil (116) has a radial axis (130) extending therethrough and a horizontal axis (132) perpendicular to the radial axis (132). The ceramic matrix composite members (111) each having a degree of curvature (119) and stacked on one another non-parallel to the horizontal axis (132).

7. 发明申请

WO2018080418A1 RING SEGMENT MOUNTING SYSTEM FOR TURBINE ENGINE, WITH PIN ATTACHMENT 审中-公开
标题翻译：带引脚的汽轮机环段安装系统
公开(公告)号：WO2018080418A1
公开(公告)日：2018-05-03
申请号：PCT/US2016/058372
申请日：2016-10-24
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： CAMPBELL, Christian Xavier , LANDRUM, Evan C. , DYER, Zachary D.
IPC分类号： F01D25/24
CPC分类号： F01D25/246 , F05D2240/11 , F05D2260/30 , F05D2300/6033 , Y02T50/672
摘要： Clevis-type pin attachment mounting system (200) accommodates varying thermal expansion rates between ring segments (202) and other ring-segment support components within a combustion turbine engine casing (22). Through-apertures (218) in a first flange (212) of the ring segment (202) slidably receive mounting pins (220). A ring-segment support ring has a pair of second and third flanges (232, 234), which define apertures (236, 338) that receive opposite projecting ends of the mounting pin (220). A gap (g) is maintained between the first flange and its flanking second and third flanges, allowing for thermal expansion by sliding the first flange along the mounting pin, allowing axial movement of the ring segment,. Embodiments also facilitate circumferential movement of the ring segment, for thermal expansion.
摘要翻译： U形夹销附件安装系统（200）适应燃烧涡轮发动机壳体（22）内的环形部分（202）和其他环形部分支撑部件之间的不同热膨胀率。环段（202）的第一凸缘（212）中的通孔（218）可滑动地接收安装销（220）。环段支撑环具有一对第二和第三凸缘（232,234），所述一对第二和第三凸缘限定容纳安装销（220）的相对突出端的孔（236,338）。在第一凸缘和其侧翼的第二和第三凸缘之间保持间隙（g），通过沿着安装销滑动第一凸缘允许热膨胀，从而允许环段的轴向移动。实施例也有利于环段的周向运动，用于热膨胀。

8. 发明申请

WO2018080417A1 CERAMIC-MATRIX-COMPOSITE (CMC) TURBINE ENGINE BLADE WITH PIN ATTACHMENT, AND METHOD FOR MANUFACTURE 审中-公开
标题翻译： CERAMIC-MATRIX-COMPOSITE（CMC）涡轮发动机叶片用销附件及制造方法
公开(公告)号：WO2018080417A1
公开(公告)日：2018-05-03
申请号：PCT/US2016/058369
申请日：2016-10-24
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： CAMPBELL, Christian Xavier , LANDRUM, Evan C. , DYER, Zachary D.
IPC分类号： F01D5/28 , F01D5/32
摘要： Clevis-type pin attachment mounts for ceramic-matric-composite (CMC) blades (50) accommodate varying thermal expansion rates between ceramic blades and the mating engine rotor disc (46). A two-dimensional array of apertures (124, 126, 128, and 130) the CMC blade shank (70) receives of rows of load-carrying pins (132, 134, 136, and 138). Tensile loads applied to the pin and aperture array are distributed within the blade shank, so that applied tensile load stress is split between successive rows of apertures and pins, so that each row of apertures carries its own tensile load plus aggregate tensile load of all other rows of apertures that are closer to the blade tip. Axial gaps (GA) between tips of load-carrying pins and partial-depth apertures in clevis attachment pieces (100, 102) provide compressive loading on the blade shank (70).
摘要翻译：用于陶瓷基质复合材料（CMC）叶片（50）的U形夹销附件安装座适应陶瓷叶片和配合的发动机转子盘（46）之间不同的热膨胀率。 CMC叶片杆（70）的二维孔阵列（124,126,128和130）接收成排的承载销（132,134,136和138）。施加到销和孔阵列的拉伸载荷分布在叶片杆内，使得施加的拉伸载荷应力在连续排孔和销之间分开，使得每排孔承载其自身的拉伸载荷加上所有其他载荷的总体拉伸载荷更靠近叶片尖端的一排孔。承载销的尖端与U形夹附接件（100,102）中的部分深度孔之间的轴向间隙（GA）在刀柄（70）上提供压缩载荷。

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