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公开(公告)号：US07753643B2
公开(公告)日：2010-07-13
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
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。
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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
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。
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公开(公告)号：US07686577B2
公开(公告)日：2010-03-30
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： F01D25/26
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。
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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
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。
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公开(公告)号：US07722317B2
公开(公告)日：2010-05-25
申请号：US11698232
申请日：2007-01-25
IPC分类号： F01D25/26
CPC分类号： F01D25/246 , F05D2300/21 , F05D2300/603 , Y10T29/49321
摘要： A CMC wall (20F) may be attached to a metal wall (22F) by a plurality of bolts (28A, 28B, 28C) passing through respective holes (24A, 24B, 24C) in the CMC wall (20F) and holes in the metal wall (22F), clamping the walls (20F, 22F) together with a force that allows sliding thermal expansion but does not allow vibrational shifting. Distal ones of the holes (24A, 24B) in the CMC wall (20F) or in the metal wall (22F) are elongated toward a central one of the bolts (24C) or at alternate angles to guide differential thermal expansion (20T) of the CMC wall (20F) versus the metal wall (22F) between desired cold and hot geometries. A second CMC wall (20R) may be mounted similarly to a second metal wall (22R) by pins (39A, 39B, 39C) that allow expansion of the CMC component (201) in a direction normal to the walls (20F, 20R).
摘要翻译： 通过穿过CMC壁（20F）中的相应孔（24A，24B，24C）的多个螺栓（28A，28B，28C）将CMC壁（20F）连接到金属壁（22F）上， 金属壁（22F），通过允许滑动热膨胀但不允许振动移动的力将壁（20F，22F）夹紧在一起。 在CMC壁（20F）或金属壁（22F）中的孔中的远端（24A，24B）朝向螺栓（24C）的中心一个或相互交替的角度拉长，以引导差动热膨胀（20T） CMC壁（20F）与期望的冷和热几何之间的金属壁（22F）相对。 第二CMC壁（20R）可以通过销（39A，39B，39C）与第二金属壁（22R）类似地安装，该销（39A，39B，39C）允许CMC部件（201）沿垂直于壁（20F，20R）的方向膨胀， 。
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公开(公告)号：US08292580B2
公开(公告)日：2012-10-23
申请号：US12479047
申请日：2009-06-05
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。
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公开(公告)号：US20080178465A1
公开(公告)日：2008-07-31
申请号：US11698232
申请日：2007-01-25
IPC分类号： B21K25/00
CPC分类号： F01D25/246 , F05D2300/21 , F05D2300/603 , Y10T29/49321
摘要： A CMC wall (20F) may be attached to a metal wall (22F) by a plurality of bolts (28A, 28B, 28C) passing through respective holes (24A, 24B, 24C) in the CMC wall (20F) and holes in the metal wall (22F), clamping the walls (20F, 22F) together with a force that allows sliding thermal expansion but does not allow vibrational shifting. Distal ones of the holes (24A, 24B) in the CMC wall (20F) or in the metal wall (22F) are elongated toward a central one of the bolts (24C) or at alternate angles to guide differential thermal expansion (20T) of the CMC wall (20F) versus the metal wall (22F) between desired cold and hot geometries. A second CMC wall (20R) may be mounted similarly to a second metal wall (22R) by pins (39A, 39B, 39C) that allow expansion of the CMC component (201) in a direction normal to the walls (20F, 20R).
摘要翻译： CMC壁（20F）可以通过多个通过CMC中的相应孔（24A，24B，24C）的螺栓（28A，28B，28C）附接到金属壁（22F） 壁（20F）和金属壁（22F）中的孔，通过允许滑动热膨胀但不允许振动移动的力将壁（20F，22F）夹紧在一起。 在CMC壁（20F）或金属壁（22F）中的孔中的远端（24A，24B）朝着中心的一个螺栓（24C）或交替的角度被拉长以引导差热 在所需的冷和热几何形状之间的CMC壁（20F）与金属壁（22F）的膨胀（20T）。 第二CMC壁（20R）可以通过销（39A，39B，39C）类似于第二金属壁（22 R）安装，其允许CMC部件（201）沿垂直于壁的方向膨胀 （20F，20R）。
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公开(公告)号：US20100068034A1
公开(公告)日：2010-03-18
申请号：US12479047
申请日：2009-06-05
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。
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公开(公告)号：US20080025838A1
公开(公告)日：2008-01-31
申请号：US11492589
申请日：2006-07-25
申请人： Bonnie D. Marini , Douglas A. Keller , David C. Radonovich , Gary B. Merrill , Steven J. Vance , Anthony L. Schiavo
发明人： Bonnie D. Marini , Douglas A. Keller , David C. Radonovich , Gary B. Merrill , Steven J. Vance , Anthony L. Schiavo
IPC分类号： F01D5/20
CPC分类号： F01D25/246 , F05D2300/21 , F05D2300/6033
摘要： Aspects of the invention are directed to a ceramic matrix composite ring seal segment. The ring seal segment according to aspects of the invention includes a relatively simple body that is circumferentially curved. At least a portion of the hot gas path surface of the ring seal segment can be coated with a thermal insulating. material. In one embodiment, each ring seal segment can be operatively connected to a stationary support structure, such as by way of isolation rings. The ring seal segments and/or the isolation rings can be configured so as to restrain the ring seal segments in the axial, radial and/or circumferential directions. The ring seal segments can be attached to the isolation rings so that the support points act opposite the operating pressure loads. Thus, the ring seal segments carry these loads in compression, a strong direction of the CMC fibers.
摘要翻译： 本发明的方面涉及一种陶瓷基复合环密封段。 根据本发明的方面的环形密封段包括周向弯曲的相对简单的主体。 环形密封段的热气体路径表面的至少一部分可以被涂覆绝热。 材料。 在一个实施例中，每个环形密封段可以可操作地连接到固定的支撑结构，例如通过隔离环。 环形密封段和/或隔离环可以构造成在轴向，径向和/或圆周方向上限制环形密封段。 环形密封段可以连接到隔离环，使得支撑点与操作压力负载相反。 因此，环形密封段承受这些负载在CMC纤维的强力方向的压缩。
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公开(公告)号：US07534086B2
公开(公告)日：2009-05-19
申请号：US11418863
申请日：2006-05-05
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。
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