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1. 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。

2. 发明申请

US20080087021A1 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：US20080087021A1
公开(公告)日：2008-04-17
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
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。

3. 发明授权

US6013592A High temperature insulation for ceramic matrix composites 失效
标题翻译：陶瓷基复合材料的高温绝缘
公开(公告)号：US6013592A
公开(公告)日：2000-01-11
申请号：US49328
申请日：1998-03-27
申请人： Gary B. Merrill , Jay Alan Morrison
发明人： Gary B. Merrill , Jay Alan Morrison
IPC分类号： C04B28/34 , C04B38/08
CPC分类号： C04B28/34
摘要： A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composite comprises a plurality of hollow oxide-based spheres of varios dimentions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substates are also provided.
摘要翻译：提供陶瓷组合物以在高温，高热通量环境下绝缘陶瓷基质复合材料。复合材料包括多个空心氧化物基的球形球体，磷酸盐粘合剂和至少一种氧化物填料粉末，由此磷酸盐粘合剂部分填充球体和填料粉末之间的间隙。球体位于磷酸盐粘合剂和填料粉末中，使得每个球体与至少一个其它球体接触。球体可以是莫来石球体，氧化铝球体或稳定的氧化锆球体的任何组合。填料粉末可以是氧化铝，莫来石，二氧化铈或哈夫尼亚的任何组合。优选地，磷酸盐粘合剂是正磷酸铝。还提供了制造陶瓷绝缘组合物的方法及其在CMC基底上的应用。

4. 发明授权

US06197424B1 Use of high temperature insulation for ceramic matrix composites in gas turbines 失效
标题翻译：在燃气轮机中使用高温绝缘陶瓷基复合材料
公开(公告)号：US06197424B1
公开(公告)日：2001-03-06
申请号：US09049369
申请日：1998-03-27
申请人： Jay Alan Morrison , Gary Brian Merrill , Evan McNeil Ludeman , Jay Edgar Lane
发明人： Jay Alan Morrison , Gary Brian Merrill , Evan McNeil Ludeman , Jay Edgar Lane
IPC分类号： B32B516
CPC分类号： F01D11/12 , C04B28/344 , C04B38/08 , C04B2111/00482 , C04B2111/28 , Y02T50/67 , Y02T50/672 , Y10T428/2982 , C04B14/30 , C04B14/301 , C04B38/0038
摘要： A ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere and the arrangement of spheres is such that the composition is dimensionally stable and chemically stable at a temperature of approximately 1600° C. A stationary vane of a gas turbine comprising the composition of the present invention bonded to the outer surface of the vane is provided. A combustor comprising the composition bonded to the inner surface of the combustor is provided. A transition duct comprising the insulating coating bonded to the inner surface of the transition is provided. Because of abradable properties of the composition, a gas turbine blade tip seal comprising the composition also is provided. The composition is bonded to the inside surface of a shroud so that a blade tip carves grooves in the composition so as to create a customized seal for the turbine blade tip.
摘要翻译：提供了一种陶瓷组合物，用于燃气轮机的由陶瓷基复合材料制成的绝缘部件。该组合物包括多个尺寸为多个中空氧化物基球体，磷酸盐粘合剂和至少一种氧化物填料粉末，由此磷酸盐粘合剂部分地填充球体和填料粉末之间的间隙。球体位于磷酸盐粘合剂和填料粉末中，使得每个球体与至少一个其它球体接触，并且球体的排列使得组合物在约1600℃的温度下尺寸稳定和化学稳定。提供了一种燃气轮机的固定叶片，其包括结合到叶片的外表面的本发明的组合物。提供了包含结合到燃烧器的内表面的组合物的燃烧器。提供了一种过渡管，其包括结合到过渡的内表面的绝缘涂层。由于组合物的耐磨特性，还提供了包含该组合物的燃气轮机叶片尖端密封件。组合物结合到护罩的内表面，使得叶片尖端在组合物中雕刻凹槽，以便为涡轮叶片尖端产生定制的密封。

5. 发明授权

US06984277B2 Bond enhancement for thermally insulated ceramic matrix composite materials 有权
标题翻译：绝缘陶瓷基复合材料的粘结强化
公开(公告)号：US06984277B2
公开(公告)日：2006-01-10
申请号：US10631277
申请日：2003-07-31
申请人： Jay Alan Morrison , Gary Brian Merrill , Thomas Barrett Jackson
发明人： Jay Alan Morrison , Gary Brian Merrill , Thomas Barrett Jackson
IPC分类号： B32B31/10 , B32B31/12
CPC分类号： C04B37/005 , B32B2315/02 , C04B2235/5224 , C04B2235/5228 , C04B2235/5236 , C04B2235/528 , C04B2237/062 , C04B2237/064 , C04B2237/068 , C04B2237/34 , C04B2237/36 , C04B2237/38 , C04B2237/592 , C04B2237/66 , Y10T428/25
摘要： A composite structure (62) having a bond enhancement member (76) extending across a bond joint (86) between a ceramic matrix composite (CMC) material (80) and a ceramic insulation material (82), and a method of fabricating such a structure. The bond enhancement member may extend completely through the CMC material to be partially embedded in a core material (84) bonded to the CMC material on an opposed side from the insulation material. A mold (26) formed of a fugitive material having particles (18) of a bond enhancement material may be used to form the CMC material. A two-piece mold (38, 46) may be used to drive a bond enhancement member partially into the CMC material. A compressible material (56) containing the bond enhancement member may be compressed between a hard tool (60) and the CMC material to drive a bond enhancement member partially into the CMC material. A surface (98) of a ceramic insulation material (92) having a bond enhancement member (96) extending therefrom may be used as a mold for laying up a CMC material.
摘要翻译：具有穿过陶瓷基体复合材料（CMC）材料（80）和陶瓷绝缘材料（82）之间的接合接头（86）延伸的结合强化构件（76）的复合结构（62），以及制造这种结构体。粘结增强构件可以完全延伸穿过CMC材料，以部分地嵌入在与绝缘材料相对的一侧上结合到CMC材料的芯材料（84）中。由具有粘结增强材料的颗粒（18）的缓冲材料形成的模具（26）可用于形成CMC材料。可以使用两件式模具（38,46）来将粘结增强部件部分地驱动到CMC材料中。含有粘结增强部件的可压缩材料（56）可以在硬质工具（60）和CMC材料之间被压缩，以将粘合增强部件部分地驱动到CMC材料中。陶瓷绝缘材料（92）的表面（98）可以用作用于堆放CMC材料的模具，所述陶瓷绝缘材料（92）的表面（98）具有从其延伸的粘结增强部件（96）。

6. 发明授权

US06641907B1 High temperature erosion resistant coating and material containing compacted hollow geometric shapes 有权
标题翻译：耐高温侵蚀涂层和含有压实中空几何形状的材料
公开(公告)号：US06641907B1
公开(公告)日：2003-11-04
申请号：US09467237
申请日：1999-12-20
申请人： Gary Brian Merrill , Jay Alan Morrison
发明人： Gary Brian Merrill , Jay Alan Morrison
IPC分类号： B32B300
CPC分类号： C04B38/0038 , C04B38/08 , C04B2111/00482 , C04B2111/28 , C23C30/00 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/125 , F05D2250/241 , F05D2300/2112 , F05D2300/2118 , F05D2300/2261 , F05D2300/2262 , F05D2300/2263 , F05D2300/2283 , F05D2300/2285 , F05D2300/603 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249974 , Y10T428/249977 , Y10T428/249985 , Y10T428/252 , C04B14/30
摘要： A material system (60) contains close packed hollow shapes (50, 70) having a dense wall structure (52, 66), which are bonded together and which may contain a matrix binder material (56) between the shapes, where the system has a stable porosity, and is abradable and thermally stable at temperatures up to possibly 1700° C., where such systems are useful in turbine apparatus.
摘要翻译：材料系统（60）包含具有致密壁结构（52,66）的紧密堆积的中空形状（50,70），它们结合在一起，并且可以在形状之间包含基体粘合剂材料（56），其中系统具有稳定的孔隙度，并且在高达可能的1700℃的温度下是可磨损和热稳定的，其中这种系统可用于涡轮机设备中。

7. 发明授权

US07198462B2 High temperature erosion resistant coating and material containing compacted hollow geometric shapes 有权
标题翻译：耐高温侵蚀涂层和含有压实中空几何形状的材料
公开(公告)号：US07198462B2
公开(公告)日：2007-04-03
申请号：US10648922
申请日：2003-08-27
申请人： Gary Brian Merrill , Jay Alan Morrison
发明人： Gary Brian Merrill , Jay Alan Morrison
IPC分类号： B23B3/00
CPC分类号： C04B38/0038 , C04B38/08 , C04B2111/00482 , C04B2111/28 , C23C30/00 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/125 , F05D2250/241 , F05D2300/2112 , F05D2300/2118 , F05D2300/2261 , F05D2300/2262 , F05D2300/2263 , F05D2300/2283 , F05D2300/2285 , F05D2300/603 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249974 , Y10T428/249977 , Y10T428/249985 , Y10T428/252 , C04B14/30
摘要： A material system (60) contains close packed hollow shapes (50, 70) having a dense wall structure (52, 66), which are bonded together and which may contain a matrix binder material (56) between the shapes, where the system has a stable porosity, and is abradable and thermally stable at temperatures up to possibly 1700° C., where such systems are useful in turbine apparatus.
摘要翻译：材料系统（60）包含具有致密壁结构（52,66）的紧密堆积的中空形状（50,70），它们结合在一起，并且可以在形状之间包含基体粘合剂材料（56），其中系统具有稳定的孔隙度，并且在高达可能的1700℃的温度下是可磨损和热稳定的，其中这种系统可用于涡轮机设备中。

8. 发明授权

US06676783B1 High temperature insulation for ceramic matrix composites 有权
标题翻译：陶瓷基复合材料的高温绝缘
公开(公告)号：US06676783B1
公开(公告)日：2004-01-13
申请号：US09507794
申请日：2000-02-22
申请人： Gary B. Merrill , Jay Alan Morrison
发明人： Gary B. Merrill , Jay Alan Morrison
IPC分类号： B32B3100
CPC分类号： C04B28/34 , C04B2111/28 , C04B14/30 , C04B20/004
摘要： A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substrates are also provided.
摘要翻译：提供陶瓷组合物以在高温，高热通量环境下绝缘陶瓷基质复合材料。该组合物包括多个尺寸为多个中空氧化物基球体，磷酸盐粘合剂和至少一种氧化物填料粉末，由此磷酸盐粘合剂部分地填充球体和填料粉末之间的间隙。球体位于磷酸盐粘合剂和填料粉末中，使得每个球体与至少一个其它球体接触。球体可以是莫来石球体，氧化铝球体或稳定的氧化锆球体的任何组合。填料粉末可以是氧化铝，莫来石，二氧化铈或哈夫尼亚的任何组合。优选地，磷酸盐粘合剂是正磷酸铝。还提供了制造陶瓷绝缘组合物的方法及其在CMC基片上的应用。

9. 发明授权

US06287511B1 High temperature insulation for ceramic matrix composites 有权
标题翻译：陶瓷基复合材料的高温绝缘
公开(公告)号：US06287511B1
公开(公告)日：2001-09-11
申请号：US09428197
申请日：1999-10-27
申请人： Gary B. Merrill , Jay Alan Morrison
发明人： Gary B. Merrill , Jay Alan Morrison
IPC分类号： C04B3808
CPC分类号： C04B28/34 , C04B14/30 , C04B14/301 , C04B14/303 , C04B20/0076
摘要： A ceramic composition is provided to insulate ceramic matrix composites under high temperature, high heat flux environments. The composition comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the phosphate binder partially fills gaps between the spheres and the filler powders. The spheres are situated in the phosphate binder and the filler powders such that each sphere is in contact with at least one other sphere. The spheres may be any combination of Mullite spheres, Alumina spheres, or stabilized Zirconia spheres. The filler powder may be any combination of Alumina, Mullite, Ceria, or Hafnia. Preferably, the phosphate binder is Aluminum Ortho-Phosphate. A method of manufacturing the ceramic insulating composition and its application to CMC substrates are also provided.
摘要翻译：提供陶瓷组合物以在高温，高热通量环境下绝缘陶瓷基质复合材料。该组合物包括多个尺寸为多个中空氧化物基球体，磷酸盐粘合剂和至少一种氧化物填料粉末，由此磷酸盐粘合剂部分地填充球体和填料粉末之间的间隙。球体位于磷酸盐粘合剂和填料粉末中，使得每个球体与至少一个其它球体接触。球体可以是莫来石球体，氧化铝球体或稳定的氧化锆球体的任何组合。填料粉末可以是氧化铝，莫来石，二氧化铈或哈夫尼亚的任何组合。优选地，磷酸盐粘合剂是正磷酸铝。还提供了制造陶瓷绝缘组合物的方法及其在CMC基片上的应用。

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