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1. 发明申请

WO2017146726A1 CERAMIC MATRIX COMPOSITE MATERIAL WITH ENHANCED THERMAL PROTECTION 审中-公开
标题翻译：增强热防护的陶瓷基复合材料
公开(公告)号：WO2017146726A1
公开(公告)日：2017-08-31
申请号：PCT/US2016/019789
申请日：2016-02-26
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MERRILL, Gary B. , SHIPPER, JR., Jonathan E.
IPC分类号： F01D5/28
CPC分类号： F01D5/284 , C04B2235/5236 , F01D5/147 , F05D2220/32 , F05D2230/13 , F05D2300/21 , F05D2300/6033 , F23D2212/10 , F23D2212/103 , F23R3/007
摘要： There is provided a component (10, 110, 110a, 210) comprising a body (12, 112) comprising a ceramic matrix composite material (14, 114), a top surface (16, 116), a bottom surface (18, 118), and a through thickness (20, 120) between the top surface (16, 116) and the bottom surface (18, 118). A plurality of first grooves (24) and second grooves (26) extend from the top surface (16, 116) down into the through thickness (20, 120) of the body (12, 112) in a predetermined pattern (50). A dopant material (135) may also be provided which enhances the thermal resistance properties of the ceramic matrix composite material (14, 114) may be further be included in the component (10, 110, 110a, 210).
摘要翻译：提供了包括主体（12,112）的部件（10,110,110a，210），所述主体包括陶瓷基质复合材料（14,114），顶表面（16,116），底表面（18,118）和顶表面（16,116）与底表面（18,118）之间的贯通厚度（20,120）。多个第一凹槽（24）和第二凹槽（26）从顶表面（16,116）以预定图案（50）向下延伸到主体（12,112）的贯通厚度（20,120）中。还可以提供增强陶瓷基质复合材料（14,114）的耐热性能的掺杂剂材料（135）可以进一步被包括在部件（10,110,110a，210）中。

2. 发明申请

WO2016133987A3 FORMING COOLING PASSAGES IN COMBUSTION TURBINE SUPERALLOY CASTINGS 审中-公开
公开(公告)号：WO2016133987A3
公开(公告)日：2016-08-25
申请号：PCT/US2016/018215
申请日：2016-02-17
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MERRILL, Gary B. , SHIPPER, JR., Jonathan E. , HITCHMAN, Cora
IPC分类号： F01D11/12 , F01D11/08 , F01D5/18 , F01D5/28 , F01D5/14
摘要： Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inserts (130) within the casting mold (152). Ceramic posts (134) formed in the ceramic shell insert (130) have profiles conforming to corresponding profiles of partially completed cooling passages (156). Posts (134) are removed after superalloy component casting, forming the partially completed cooling passages, which are subsequently completed by removing remaining superalloy material along the cooling passage path.

3. 发明申请

WO2016133488A1 TURBINE AIRFOIL COOLING SYSTEM WITH FILM COOLING HOLE WITHIN PROTRUDED COOLING HOLE SUPPORT 审中-公开
标题翻译：涡轮机空气冷却系统，带有冷却孔的薄膜冷却孔支撑
公开(公告)号：WO2016133488A1
公开(公告)日：2016-08-25
申请号：PCT/US2015/016004
申请日：2015-02-16
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MERRILL, Gary B. , SHIPPER, JR., Jonathan E.
IPC分类号： F01D5/18 , F01D5/28
CPC分类号： F01D5/187 , F01D5/288 , F05D2230/90
摘要： A turbine airfoil (10) for a gas turbine engine (12) having a more resilient film cooling hole (14) configuration is disclosed. The film cooling hole (14) may be positioned in an outer wall (16) of the airfoil (10) and may have an inlet (18) in communication with a cooling system (20) and an outlet (22) in an elevated film cooling exhaust surface (24) that extends outwardly further than an adjacent outer surface (26) of the outer wall (16). A thermal barrier coating (28) may be positioned on the outer wall (16), and the outer surface (30) of the elevated film cooling exhaust surface (24) may be positioned between the outer surface (26) of the outer wall (16) and an outer surface (32) of the thermal barrier coating (28), thereby positioning the elevated film cooling exhaust surface (24) above the outer surface (26) of the outer wall (16) of the airfoil (10). Such position reduces thermal stress at the film cooling hole (14) and improving local stress and bonding adjacent to the outlet (22).
摘要翻译：公开了一种具有更具弹性的薄膜冷却孔（14）结构的用于燃气涡轮发动机（12）的涡轮机翼（10）。薄膜冷却孔（14）可以位于翼型件（10）的外壁（16）中，并且可以具有与冷却系统（20）连通的入口（18）和升高的薄膜中的出口（22）冷却排气表面（24），其比外壁（16）的相邻外表面（26）向外延伸。隔热涂层（28）可以定位在外壁（16）上，并且升高的膜冷却排气表面（24）的外表面（30）可以位于外壁的外表面（26）之间 16）和隔热涂层（28）的外表面（32），从而将升高的薄膜冷却排气表面（24）定位在翼型件（10）的外壁（16）的外表面（26）上方。这种位置减小了薄膜冷却孔（14）处的热应力，并改善了邻近出口（22）的局部应力和粘合。

4. 发明申请

WO2019203826A1 TURBINE BLADES AND METHOD OF FORMING A TURBINE BLADE 审中-公开
公开(公告)号：WO2019203826A1
公开(公告)日：2019-10-24
申请号：PCT/US2018/028226
申请日：2018-04-19
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： HOLLINGSWORTH, Peter Stuart , SHIPPER, JR., Jonathan E. , KULKARNI, Anand A.
IPC分类号： F01D5/28
摘要： A turbine blade (10) includes a root (15), a platform (20) coupled to the root (15), and an airfoil coupled to the platform (20). The root (15), the platform (20), and the airfoil are formed as one continuous piece from a Ceramic Matrix Composite (CMC) material (30). An interlayer (35) is formed directly onto and bonded to at least a portion of the airfoil, and a thermal barrier coating (TBC) (40) is bonded to at least the interlayer (35).

5. 发明申请

WO2016133987A2 FORMING COOLING PASSAGES IN COMBUSTION TURBINE SUPERALLOY CASTINGS 审中-公开
标题翻译：在燃烧涡轮机超级铸造中形成冷却通道
公开(公告)号：WO2016133987A2
公开(公告)日：2016-08-25
申请号：PCT/US2016/018215
申请日：2016-02-17
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： MERRILL, Gary B. , SHIPPER, JR., Jonathan E. , HITCHMAN, Cora
IPC分类号： F01D11/08 , F01D5/18 , F01D11/12
CPC分类号： F01D11/122 , B22C7/02 , B22C9/24 , B22D25/02 , B22D29/001 , B23H1/00 , B23K26/382 , B23P15/02 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/14 , F01D5/18 , F01D5/186 , F01D5/28 , F01D5/288 , F01D11/08 , F01D11/127 , F04D29/526 , F04D29/685 , F05D2230/10 , F05D2230/30 , F05D2230/90 , F05D2250/12 , F05D2250/15 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/23 , F05D2250/282 , F05D2250/292 , F05D2250/294 , F05D2250/75 , F05D2260/202 , F05D2260/22141 , F05D2300/175 , F05D2300/611
摘要： Cooling passages (99, 105) are formed in components for combustion turbine engines, such as blades (92), vanes (104, 106), ring segments (110) or castings in transitions (85), during investment casting, through use of ceramic shell inserts (130) within the casting mold (152). Ceramic posts (134) formed in the ceramic shell insert (130) have profiles conforming to corresponding profiles of partially completed cooling passages (156). Posts (134) are removed after superalloy component casting, forming the partially completed cooling passages, which are subsequently completed by removing remaining superalloy material along the cooling passage path.
摘要翻译：冷却通道（99,105）形成在用于燃料涡轮发动机的部件中，例如叶片（92），叶片（104,106），环形段（110）或过渡（85）中的铸件）铸模（152）内的陶瓷壳体嵌件（130）。形成在陶瓷壳体插入件（130）中的陶瓷柱（134）具有符合部分完成的冷却通道（156）的对应轮廓的轮廓。在超合金部件铸造之后移除柱（134），形成部分完成的冷却通道，随后通过沿着冷却通道路径除去剩余的超合金材料而完成。

6. 发明公开

EP3259452A2 FORMING COOLING PASSAGES IN COMBUSTION TURBINE SUPERALLOY CASTINGS 审中-公开
标题翻译：在燃气轮机高温合金铸造中形成冷却通道
公开(公告)号：EP3259452A2
公开(公告)日：2017-12-27
申请号：EP16710355.5
申请日：2016-02-17
申请人： Siemens Aktiengesellschaft
发明人： MERRILL, Gary B. , SHIPPER, JR., Jonathan E. , HITCHMAN, Cora
IPC分类号： F01D11/08 , F01D5/18 , F01D11/12
CPC分类号： F01D11/122 , B22C7/02 , B22C9/24 , B22D25/02 , B22D29/001 , B23H1/00 , B23K26/382 , B23P15/02 , C23C4/02 , C23C4/073 , C23C4/18 , C23C28/3215 , C23C28/3455 , F01D5/14 , F01D5/18 , F01D5/186 , F01D5/28 , F01D5/288 , F01D11/08 , F01D11/127 , F04D29/526 , F04D29/685 , F05D2230/10 , F05D2230/30 , F05D2230/90 , F05D2250/12 , F05D2250/15 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2250/23 , F05D2250/282 , F05D2250/292 , F05D2250/294 , F05D2250/75 , F05D2260/202 , F05D2260/22141 , F05D2300/175 , F05D2300/611
摘要： Delamination of thermal barrier coatings (“TBC's”) (276) from superalloy substrates (262) of components (260) for turbine engines (80), such as engine blades (92), vanes (104, 106), or castings in transitions (85), is inhibited during subsequent cooling passage (270) formation. Partially completed cooling passages (264), which have skewed passage paths that end at a terminus (268), which is laterally offset from the passage entrance (266), are formed in the superalloy component (260) prior to application of the TBC layer(s) (276). The skewed, laterally offset path of each partially completed cooling passage (264) establishes an overhanging shield layer (269) of superalloy material that protects the TBC layer (276) during completion of the cooling passage (270).

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