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1. 发明申请

US20090053037A1 TURBINE VANES WITH AIRFOIL-PROXIMATE COOLING SEAM 失效
标题翻译：涡轮风扇与空气 - 接近冷却海绵
公开(公告)号：US20090053037A1
公开(公告)日：2009-02-26
申请号：US11494178
申请日：2006-07-27
申请人： Bonnie D. Marini , Anthony L. Schiavo
发明人： Bonnie D. Marini , Anthony L. Schiavo
IPC分类号： F01D1/18
CPC分类号： F01D5/147 , F01D5/081 , F01D9/041 , F01D11/005 , F05D2240/81
摘要： Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.
摘要翻译：本发明的方面涉及一种涡轮叶片，其中内平台和外平台基本上完全位于翼型的压力侧或吸力侧上。当多个这样的叶片安装在涡轮机中时，由内平台和外平台的周向端部和相邻叶片的翼型的一部分形成接缝。在发动机操作期间，向至少一个平台供应高压冷却剂。冷却液可能通过接缝泄漏。因为接缝位于翼型附近，所以通过接缝的冷却剂泄漏可以有效地用于冷却叶片平台和翼型之间的过渡区域。除了这样的冷却效果之外，本发明的方面可以导致发动机效率以及部件寿命的潜在增加。

2. 发明授权

US07488157B2 Turbine vane with removable platform inserts 失效
标题翻译：涡轮叶片带有可移动平台插入件
公开(公告)号：US07488157B2
公开(公告)日：2009-02-10
申请号：US11494177
申请日：2006-07-27
申请人： Bonnie D. Marini , Anthony L. Schiavo
发明人： Bonnie D. Marini , Anthony L. Schiavo
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/18 , F01D25/12 , F05D2230/80 , F05D2230/90 , F05D2240/80 , F05D2240/81 , F05D2300/21 , F05D2300/603 , F05D2300/611
摘要： Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.
摘要翻译：本发明的方面涉及涡轮叶片组件，其中至少一个平台装备有一个或多个可移除的平台插入件。这些插入件可以用于已知发生故障或损坏的平台的其他位置的那些区域。如果在发动机运行期间插入件损坏或损坏，则可以方便地更换插入件，并可以重新使用平台框架和翼型件。结果，叶片的整体寿命可以延长。此外，与已知的涡轮叶片相比，插入件可以由能够降低冷却要求的材料制成，从而允许将冷却空气用于发动机中的其它用途。

3. 发明申请

US20080025838A1 Ring seal for a turbine engine 审中-公开
标题翻译：涡轮发动机的环形密封
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。

4. 发明申请

US20080025842A1 Turbine vane with removable platform inserts 失效
标题翻译：涡轮叶片带有可移动平台插入件
公开(公告)号：US20080025842A1
公开(公告)日：2008-01-31
申请号：US11494177
申请日：2006-07-27
申请人： Bonnie D. Marini , Anthony L. Schiavo
发明人： Bonnie D. Marini , Anthony L. Schiavo
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , F01D5/18 , F01D25/12 , F05D2230/80 , F05D2230/90 , F05D2240/80 , F05D2240/81 , F05D2300/21 , F05D2300/603 , F05D2300/611
摘要： Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.
摘要翻译：本发明的方面涉及涡轮叶片组件，其中至少一个平台装备有一个或多个可移除的平台插入件。这些插入件可用于已知发生故障或损坏的平台的其他位置的那些区域。如果在发动机运行期间插入件损坏或损坏，则可以方便地更换插入件，并可以重新使用平台框架和翼型件。结果，叶片的整体寿命可以延长。此外，与已知的涡轮叶片相比，插入件可以由能够降低冷却要求的材料制成，从而允许将冷却空气用于发动机中的其它用途。

5. 发明授权

US07581924B2 Turbine vanes with airfoil-proximate cooling seam 失效
标题翻译：涡轮叶片与翼面靠近的冷却缝
公开(公告)号：US07581924B2
公开(公告)日：2009-09-01
申请号：US11494178
申请日：2006-07-27
申请人： Bonnie D. Marini , Anthony L. Schiavo
发明人： Bonnie D. Marini , Anthony L. Schiavo
IPC分类号： F01D9/02
CPC分类号： F01D5/147 , F01D5/081 , F01D9/041 , F01D11/005 , F05D2240/81
摘要： Aspects of the invention relate to a turbine vane in which the inner and outer platforms are located substantially entirely on either the pressure side or the suction side of the airfoil. When a plurality of such vanes are installed in the turbine, a seam is formed by the circumferential end of the inner and outer platforms and a portion of the airfoil of a neighboring vane. During engine operation, a high pressure coolant is supplied to at least one of the platforms. The coolant can leak through the seam. Because the seam is located proximate the airfoil, the coolant leakage through the seam can be productively used to cool the transition region between the vane platforms and the airfoil. In addition to such cooling benefits, aspects of the invention can result in a potential increase in engine efficiency as well as component life.
摘要翻译：本发明的方面涉及一种涡轮叶片，其中内平台和外平台基本上完全位于翼型的压力侧或吸力侧上。当多个这样的叶片安装在涡轮机中时，由内平台和外平台的周向端部和相邻叶片的翼型的一部分形成接缝。在发动机操作期间，向至少一个平台供应高压冷却剂。冷却液可能通过接缝泄漏。因为接缝位于翼型附近，所以通过接缝的冷却剂泄漏可以有效地用于冷却叶片平台和翼型之间的过渡区域。除了这样的冷却效果之外，本发明的方面可以导致发动机效率以及部件寿命的潜在增加。

6. 发明授权

US07722317B2 CMC to metal attachment mechanism 有权
标题翻译： CMC到金属附件机构
公开(公告)号：US07722317B2
公开(公告)日：2010-05-25
申请号：US11698232
申请日：2007-01-25
申请人： Anthony L. Schiavo , Douglas A. Keller , Malberto F. Gonzalez , David C. Radonovich
发明人： Anthony L. Schiavo , Douglas A. Keller , Malberto F. Gonzalez , David C. Radonovich
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，。

7. 发明授权

US07686577B2 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：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。

8. 发明申请

US20090071160A1 Wavy CMC Wall Hybrid Ceramic Apparatus 有权
标题翻译：波纹CMC墙混合陶瓷设备
公开(公告)号：US20090071160A1
公开(公告)日：2009-03-19
申请号：US11855623
申请日：2007-09-14
申请人： Douglas A. Keller , Anthony L. Schiavo , Jay A. Morrison
发明人： Douglas A. Keller , Anthony L. Schiavo , Jay A. Morrison
IPC分类号： F01D25/24 , F02C7/24
CPC分类号： F01D9/023 , F23R3/007 , Y10T428/1317
摘要： A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a distal surface (242) that may define a hot gas passage (250, 550, 650) or otherwise be in proximity to a source of elevated temperature. In various embodiments, the waves (216, 537, 637) of the CMC wall (214, 532, 603, 609) may conform to the following parameters: a thickness (222) between 1 and 10 millimeters; an amplitude (224) between one and 2.5 times the thickness; and a period (226) between one and 20 times the amplitude. The uninsulated backside surface (218) of the CMC wall (214) provides a desired stiffness and strength and enhanced cooling surface area. In various embodiments the amplitude (224), excluding the thickness (222), may be at least 2 mm.
摘要翻译：一种陶瓷混合结构（207,502,602,608），其包括与陶瓷绝缘层（230,538,604,610）接合的波纹陶瓷基复合材料（CMC）壁（214,532,603,609），其具有远端表面（242），其可以限定热气体通道（250,550,650）或以其它方式接近升高的温度源。在各种实施例中，CMC壁（214,532,603,609）的波浪（216,537,637）可以符合以下参数：1和10毫米之间的厚度（222）; 幅度（224）为厚度的1至2.5倍; 以及振幅的1到20倍之间的周期（226）。 CMC壁（214）的未绝缘的背侧表面（218）提供期望的刚度和强度以及增强的冷却表面积。在各种实施例中，不包括厚度（222）的振幅（224）可以至少为2mm。

9. 发明授权

US08096758B2 Circumferential shroud inserts for a gas turbine vane platform 有权
标题翻译：用于燃气轮机叶片平台的环形护罩插件
公开(公告)号：US08096758B2
公开(公告)日：2012-01-17
申请号：US12203397
申请日：2008-09-03
申请人： Anthony L. Schiavo
发明人： Anthony L. Schiavo
IPC分类号： F01D1/02 , F01D9/00 , F03B1/04 , F03B3/16 , F03D1/04 , F03D11/00 , F03D3/04 , F04D29/44 , F04D29/54
CPC分类号： F01D5/147 , F01D9/04 , F05D2240/11 , F05D2240/81 , F05D2300/21 , F05D2300/5024 , F05D2300/603
摘要： Protective insert plates (54, 56) installed on a working gas face (42) of a turbine vane platform (26) provide replaceable portions of a turbine shroud for improved maintenance. The plates act as tiles, and may be formed of ceramic materials for thermal protection. Two cages (58, 60) in the vane platform slidably receive the two insert plates (54, 56) from opposite circumferential sides (36, 38) of the platform. The plates slide into the cages up to the pressure and suction sides (32, 34) of the vane airfoil (22). The plates may have proximal edges (62, 64) shaped to fit the respective pressure and suction sides of the vane airfoil. A retainer plate 66 may be attached to a flange (72) on the cooled face (48) of each platform, and may contact each insert plate with a locking device (74, 76) to prevent sliding of the plate in the cage.
摘要翻译：安装在涡轮叶片平台（26）的工作气体表面（42）上的保护性插入板（54,56）提供涡轮机罩的可更换部分以改善维护。板用作瓷砖，并且可以由用于热保护的陶瓷材料形成。叶片平台中的两个笼子（58,60）可从平台的相对的周向侧面（36,38）滑动地容纳两个插入板（54,56）。板滑入笼子直到叶片翼型件（22）的压力和吸力侧（32,34）。板可以具有成形为适合叶片翼型的相应的压力侧和吸力侧的近侧边缘（62,64）。保持板66可以附接到每个平台的冷却面（48）上的凸缘（72）上，并且可以用锁定装置（74,76）接触每个插入板，以防止板在壳体中的滑动。

10. 发明授权

US08292580B2 CMC vane assembly apparatus and method 有权
标题翻译： CMC叶片装配装置及方法
公开(公告)号：US08292580B2
公开(公告)日：2012-10-23
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： F01D5/08 , F01D5/18
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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