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21. 发明授权

US07534086B2 Multi-layer ring seal 有权
标题翻译：多层环密封
公开(公告)号：US07534086B2
公开(公告)日：2009-05-19
申请号：US11418863
申请日：2006-05-05
申请人： Stefan Mazzola , Douglas A. Keller , Anthony L. Schiavo , David C. Radonovich
发明人： Stefan Mazzola , Douglas A. Keller , Anthony L. Schiavo , David C. Radonovich
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F05D2250/70 , F05D2250/712 , F05D2300/21 , F05D2300/603 , F16J15/104
摘要： Aspects of the invention are directed to a multi-layer ring seal segment that can incorporate a plurality of material systems. The ring seal segment can include an inner layer, a central layer and an outer layer. The inner layer can be attached to one side of the central layer, and the outer layer can be attached to an opposite side of the central layer. The inner and outer layers can be made of a ceramic matrix composite, such as a hybrid oxide ceramic matrix composite or an oxide-oxide ceramic matrix composite. The central layer can be made of a material that has high shear strength relative to the inner and outer layers. The ring seal segment according to aspects of the invention can take advantage of the benefits of the different materials so as to better withstand the operational loads of the turbine.
摘要翻译：本发明的方面涉及可以结合多个材料系统的多层环密封段。环形密封段可以包括内层，中心层和外层。内层可以附接到中心层的一侧，并且外层可以附接到中心层的相对侧。内层和外层可以由陶瓷基复合材料制成，例如杂化氧化物陶瓷基复合材料或氧化物 - 氧化物陶瓷基复合材料。中心层可以由相对于内层和外层具有高剪切强度的材料制成。根据本发明的方面的环形密封段可以利用不同材料的优点，以便更好地承受涡轮机的操作负载。

22. 发明申请

US20080107521A1 Stacked laminate fiber wrapped segment 有权
标题翻译：堆叠层压纤维包裹片段
公开(公告)号：US20080107521A1
公开(公告)日：2008-05-08
申请号：US11591907
申请日：2006-11-02
申请人： Jay A. Morrison , David C. Radonovich , Anthony L. Schiavo , Gary B. Merrill , Malberto F. Gonzalez
发明人： Jay A. Morrison , David C. Radonovich , Anthony L. Schiavo , Gary B. Merrill , Malberto F. Gonzalez
IPC分类号： F01D11/08 , F04D29/08 , B32B18/00
CPC分类号： F01D11/08 , F01D9/04 , F05D2240/11 , F05D2300/603 , Y10T29/49888
摘要： A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a ceramic matrix composite overwrap or plurality of overwraps designed to help prevent delamination of the ceramic plates when the ceramic article is in use by placing the plates in compression.
摘要翻译：用于涡轮发动机的陶瓷环段，其可用作一种或多种金属组分的替代物。陶瓷环段可以由多个陶瓷板形成，例如陶瓷基复合板，其使用强化机构连接在一起以加强陶瓷板，同时允许所得的陶瓷制品用作涡轮机部件的替代品通常是金属的系统，从而利用由陶瓷材料提供的性质。加强机构可以包括陶瓷基复合材料外包装或多个外包装，其被设计成当陶瓷制品在使用时通过将板放置在压缩中来帮助防止陶瓷板的分层。

23. 发明授权

US06273683B1 Turbine blade platform seal 有权
标题翻译：涡轮叶片平台密封
公开(公告)号：US06273683B1
公开(公告)日：2001-08-14
申请号：US09245816
申请日：1999-02-05
申请人： Thomas W. Zagar , Anthony L. Schiavo
发明人： Thomas W. Zagar , Anthony L. Schiavo
IPC分类号： F01D522
CPC分类号： F01D5/22 , F01D11/008 , F05D2240/80 , Y10S416/50
摘要： A rotating blade group 90 for a turbo-machine having an improved device for sealing the gap 110 between the edges 112,114 of adjacent blade platforms 96,104. The gap 110 between adjacent blades 92,100 is sealed by a seal pin 20 its central portion 110 and by a seal plate 58,60 at each of the front 54 and rear 56 portions. The seal plates 58,60 are inserted into corresponding grooves 62,64 formed in the adjacent edges 112,114 of adjoining blades 92,100 and held in place by end plates 40,42. The end of the seal plates 58,60 may be chamfered 78,80 to improve the seal against the end plate 40,42. The seal pin 20 provides the required damping between the blades 92,100 and the seal plates 58,60 provide improved sealing effectiveness.
摘要翻译：用于涡轮机的旋转叶片组90具有用于密封相邻叶片平台96,104的边缘112,114之间的间隙110的改进的装置。相邻叶片92,100之间的间隙110由其中心部分110的密封销20和前部54和后部56中的每一个处的密封板58,60密封。密封板58,60插入形成在相邻叶片92,100的相邻边缘112,114中的对应的凹槽62,64中，并通过端板40,42保持在适当的位置。密封板58,60的端部可以被倒角78,80以改进对端板40,42的密封。密封销20在叶片92,100和密封板58,60之间提供所需的阻尼，提供改进的密封效果。

24. 发明授权

US07950234B2 Ceramic matrix composite turbine engine components with unitary stiffening frame 有权
标题翻译：陶瓷基体复合涡轮发动机部件采用单一加筋架
公开(公告)号：US07950234B2
公开(公告)日：2011-05-31
申请号：US11581165
申请日：2006-10-13
申请人： David Charles Radonovich , Douglas Allen Keller , Jay Alan Morrison , Malberto Fernandez Gonzalez , Anthony L. Schiavo
发明人： David Charles Radonovich , Douglas Allen Keller , Jay Alan Morrison , Malberto Fernandez Gonzalez , Anthony L. Schiavo
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F01D11/122 , F05D2240/11 , F05D2250/12 , F05D2250/121 , F05D2300/21 , F05D2300/603
摘要： Aspects of the invention are directed to a ring seal segment having a base portion and a frame portion. The base portion and the frame portion are a unitary structure. The frame portion is made of four unitary side walls: a forward wall, an aft wall and a pair of transverse side walls. The side walls can be arranged in a rectangular configuration. At least a part of the base portion can be coated with a thermal insulating material. A ring seal segment according to aspects of the invention is well suited to withstand the expected operational loads in the turbine section. The transverse side walls can provide bending strength to the base and can strengthen the forward and aft side walls. Transition regions between the side walls and the base portion are strengthened by three perpendicular planes that cooperate to provide structural strength to the ring seal segment.
摘要翻译：本发明的方面涉及具有基部和框架部分的环形密封段。基部和框架部分是整体结构。框架部分由四个单一侧壁制成：前壁，后壁和一对横向侧壁。侧壁可以以矩形配置布置。基部的至少一部分可以用绝热材料涂覆。根据本发明的方面的环形密封段非常适合于承受涡轮机部分中的预期操作负载。横向侧壁可以为基座提供弯曲强度，并且可以加强前后侧壁。通过三个垂直平面来加强侧壁和基部之间的过渡区域，这三个垂直平面协作以提供环形密封段的结构强度。

25. 发明申请

US20100322760A1 Interlocked CMC Airfoil 有权
标题翻译：联锁CMC翼型
公开(公告)号：US20100322760A1
公开(公告)日：2010-12-23
申请号：US12486180
申请日：2009-06-17
申请人： Jay A. Morrison , Anthony L. Schiavo
发明人： Jay A. Morrison , Anthony L. Schiavo
IPC分类号： F01D9/04 , F04D29/54
CPC分类号： F04D29/023 , F01D5/147 , F01D5/282 , F01D5/284 , F04D29/542 , F05D2230/23 , F05D2300/6033 , F05D2300/608 , Y10T29/49339
摘要： A ceramic matrix composite (CMC) airfoil assembled from a pressure side wall (42) and a suction side wall (52) joined by interlocking joints (18, 19) at the leading and trailing edges (22, 24) of the airfoil to produce a tapered thin trailing edge. The trailing edge (24) is thinner than a combined thicknesses of the airfoil walls (42, 52). One or both of the interlocking joints (18, 19) may be formed to allow only a single direction of assembly, as exemplified by a dovetail joint. Each joint (18, 19) includes keys (44F, 54F, 56F, 46F) on one side and respective keyways (44K, 54K, 56K, 46K) on the other side. Each keyway may have a ramp (45) that eliminates indents in the airfoil outer surface that would otherwise result from the joint.
摘要翻译：由压力侧壁（42）和吸力侧壁（52）组装的陶瓷基体复合材料（CMC）翼型件，其通过翼型件的前缘和后缘（22,24）处的互锁接头（18,19）连接，以产生锥形细的后缘。后缘（24）比翼型件壁（42,52）的组合厚度薄。互锁接头（18,19）中的一个或两个可以形成为仅允许组装的单个方向，如燕尾接头所例示。每个接头（18,19）包括一侧的键（44F，54F，56F，46F）和另一侧的键槽（44K，54K，56K，46K）。每个键槽可以具有斜面（45），其消除了否则从接头产生的翼型件外表面中的凹痕。

26. 发明申请

US20100183435A1 Gas Turbine Vane Platform Element 有权
标题翻译：燃气轮机平台元件
公开(公告)号：US20100183435A1
公开(公告)日：2010-07-22
申请号：US12479082
申请日：2009-06-05
申请人： Christian X. Campbell , Anthony L. Schiavo , Jay A. Morrison
发明人： Christian X. Campbell , Anthony L. Schiavo , Jay A. Morrison
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/189 , F01D5/282 , F01D5/284 , F05D2300/21 , F05D2300/603 , Y10T29/49323
摘要： A gas turbine CMC shroud plate (48A) with a vane-receiving opening (79) that matches a cross-section profile of a turbine vane airfoil (22). The shroud plate (48A) has first and second curved circumferential sides (73A, 74A) that generally follow the curves of respective first and second curved sides (81, 82) of the vane-receiving opening. Walls (75A, 76A, 77A, 78A, 80, 88) extend perpendicularly from the shroud plate forming a cross-bracing structure for the shroud plate. A vane (22) may be attached to the shroud plate by pins (83) or by hoop-tension rings (106) that clamp tabs (103) of the shroud plate against bosses (105) of the vane. A circular array (20) of shroud plates (48A) may be assembled to form a vane shroud ring in which adjacent shroud plates are separated by compressible ceramic seals (93).
摘要翻译：具有与涡轮机叶片（22）的横截面轮廓匹配的叶片接收开口（79）的燃气轮机CMC护罩板（48A）。护罩板（48A）具有通常沿着叶片接收开口的相应的第一和第二弯曲侧面（81,82）的曲线的第一和第二弯曲周向侧面（73A，74A）。壁（75A，76A，77A，78A，80,88）从罩板垂直延伸，形成用于护罩板的交叉支撑结构。叶片（22）可以通过销（83）或环形张力环（106）附接到护罩板，所述环向张力环将护罩板的突片（103）夹紧在叶片的凸台（105）上。护罩板（48A）的圆形阵列（20）可以组装成形成叶片护罩环，相邻的护板通过可压缩的陶瓷密封件（93）分开。

27. 发明申请

US20100150703A1 STACKED LAMINATE BOLTED RING SEGMENT 有权
标题翻译：堆叠层压板环
公开(公告)号：US20100150703A1
公开(公告)日：2010-06-17
申请号：US11526256
申请日：2006-09-22
申请人： Malberto F. Gonzalez , David C. Radonovich , Anthony L. Schiavo , Jay A. Morrison , Steven J. Vance
发明人： Malberto F. Gonzalez , David C. Radonovich , Anthony L. Schiavo , Jay A. Morrison , Steven J. Vance
IPC分类号： F01D11/08 , F04D29/02 , F04D29/40 , B23P17/00
CPC分类号： F01D9/04 , F01D11/08 , F01D25/246 , F05D2300/21 , Y10T29/49236
摘要： A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression.
摘要翻译：用于涡轮发动机的陶瓷环段，其可用作一种或多种金属组分的替代物。陶瓷环段可以由多个陶瓷板形成，例如陶瓷基复合板，其使用强化机构连接在一起以加强陶瓷板，同时允许所得的陶瓷制品用作涡轮机部件的替代品通常是金属的系统，从而利用由陶瓷材料提供的性质。加强机构可以包括螺栓或多个螺栓，其被设计成在使用时防止陶瓷板在通过保持陶瓷板压缩时分层。

28. 发明申请

US20100068034A1 CMC Vane Assembly Apparatus and Method 有权
标题翻译： CMC叶片装配和方法
公开(公告)号：US20100068034A1
公开(公告)日：2010-03-18
申请号：US12479047
申请日：2009-06-05
申请人： Anthony L. Schiavo , Malberto F. Gonzalez , Kuangwei Huang , David C. Radonovich
发明人： Anthony L. Schiavo , Malberto F. Gonzalez , Kuangwei Huang , David C. Radonovich
IPC分类号： F01D25/12 , F01D9/02 , B23P11/00
CPC分类号： F01D9/041 , F01D5/189 , F01D5/282 , F01D5/284 , F05D2300/21 , F05D2300/603 , Y10T29/49323
摘要： A metal vane core or strut (64) is formed integrally with an outer backing plate (40). An inner backing plate (38) is formed separately. A spring (74) with holes (75) is installed in a peripheral spring chamber (76) on the strut. Inner and outer CMC shroud covers (46, 48) are formed, cured, then attached to facing surfaces of the inner and outer backing plates (38, 40). A CMC vane airfoil (22) is formed, cured, and slid over the strut (64). The spring (74) urges continuous contact between the strut (64) and airfoil (66), eliminating vibrations while allowing differential expansion. The inner end (88) of the strut is fastened to the inner backing plate (38). A cooling channel (68) in the strut is connected by holes (69) along the leading edge of the strut to peripheral cooling paths (70, 71) around the strut. Coolant flows through and around the strut, including through the spring holes.
摘要翻译：金属叶片芯或支柱（64）与外背板（40）整体形成。内侧背板（38）分别形成。具有孔（75）的弹簧（74）安装在支柱上的周边弹簧室（76）中。内部和外部CMC护罩罩（46,48）形成，固化，然后连接到内侧和外侧背板（38,40）的相对表面。形成CMC叶片翼型件（22），固化并滑过支柱（64）。弹簧（74）促使支柱（64）和翼型件（66）之间的连续接触，消除振动，同时允许不同的膨胀。支柱的内端（88）固定在内背板（38）上。支柱中的冷却通道（68）通过沿着支柱的前缘的孔（69）连接到围绕支柱的周边冷却路径（70,71）。冷却液通过支柱和其周围流动，包括通过弹簧孔。

29. 发明申请

US20100054928A1 GAS TURBINE TRANSITION DUCT APPARATUS 有权
标题翻译：气体涡轮转换导管装置
公开(公告)号：US20100054928A1
公开(公告)日：2010-03-04
申请号：US12198413
申请日：2008-08-26
申请人： Anthony L. Schiavo
发明人： Anthony L. Schiavo
IPC分类号： F01D25/24
CPC分类号： F01D25/243 , F01D9/023 , F05D2240/57
摘要： A gas turbine transition duct is provided comprising a generally tubular main body having first and second ends, the first end being adapted to be positioned adjacent to a combustor unit and the second end being adapted to be positioned adjacent to a turbine and a collar coupled to the main body second end. The collar may have upper, lower and side portions. At least one of the side portions may be provided with a notched section.
摘要翻译：提供了一种燃气轮机过渡管道，其包括具有第一和第二端的大体上管状的主体，第一端适于邻近燃烧器单元定位，并且第二端适于邻近涡轮定位，主体第二端。套环可以具有上部，下部和侧部。侧部中的至少一个可以设置有切口部。

30. 发明申请

US20090081033A1 Stacked Lamellae Ceramic Gas Turbine Ring Segment Component 有权
标题翻译：堆叠薄膜陶瓷燃气轮机环段组件
公开(公告)号：US20090081033A1
公开(公告)日：2009-03-26
申请号：US11928407
申请日：2007-10-30
申请人： Anthony L. Schiavo , Gary B. Merrill , Thomas B. Jackson , Todd Willis
发明人： Anthony L. Schiavo , Gary B. Merrill , Thomas B. Jackson , Todd Willis
IPC分类号： F01D9/04
CPC分类号： F01D11/08 , F05D2240/11
摘要： A gas turbine ring segment (10) for use in gas turbine engines made from a ceramic matrix composite (CMC) material is disclosed. The ring segment includes a stacked multiplicity of CMC thin-sheet lamellae (25a, 25b) each comprising a peripheral surface collectively defining a cross-section profile of the ring segment. The lamellae collectively define a channel (11) formed in the center thereof for receiving a bow-tie member (27). The bow-tie member is disposed in the channel for holding together the stacked lamellae in a through thickness direction, and the in-plane strength of the bow-tie member is perpendicular to the in-plane strength of the lamellae. A stem portion (33) of the assembly may be further secured with a wrap (38) of CMC ribbon.
摘要翻译：公开了一种用于由陶瓷基体复合材料（CMC）材料制成的燃气涡轮发动机的燃气轮机环段（10）。环段包括堆叠的多个CMC薄片薄片（25a，25b），每个薄片片层包括共同限定环形部分的横截面轮廓的外围表面。薄片共同限定形成在其中心的通道（11），用于接收弓形构件（27）。蝴蝶结构件设置在通道中，用于将堆叠的薄片沿着厚度方向保持在一起，并且蝴蝶结构件的面内强度垂直于薄片的面内强度。组件的杆部分（33）可以用CMC带的包裹物（38）进一步固定。

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