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1. 发明授权

US07247003B2 Stacked lamellate assembly 有权
标题翻译：堆叠层状组件
公开(公告)号：US07247003B2
公开(公告)日：2007-07-24
申请号：US11031797
申请日：2005-01-07
申请人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
发明人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/284 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.
摘要翻译：一种层叠的陶瓷基复合材料层状组件（10），其包括用于抵抗相邻薄片之间的相对滑动运动的剪切力轴承结构（48）。剪切力承载结构可以采取跨层状缝合（50），剪切销（62），薄片中的经线（90），舌状物（104）和凹槽（98）结构的形式， - 绝缘密封件（112）。每个剪切力轴承结构确保薄片的一个子集，其中至少一个薄片在相邻子集之间是共同的，以便固定整个组件。

2. 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。

3. 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。

4. 发明授权

US07124591B2 Method for operating a gas turbine 有权
标题翻译：操作燃气轮机的方法
公开(公告)号：US07124591B2
公开(公告)日：2006-10-24
申请号：US10754195
申请日：2004-01-09
申请人： Joan Mae Baer , Walter Ray Laster , Douglas Allen Keller
发明人： Joan Mae Baer , Walter Ray Laster , Douglas Allen Keller
IPC分类号： F02C6/08 , F02C6/18 , F02C7/26
CPC分类号： F02C7/12 , Y02E20/16
摘要： A gas turbine includes a compressor, a combustor, a turbine, and a flow path diverting an excess portion of the compressed air produced by the compressor around the turbine. The flow path conducts the excess portion into a turbine exhaust gas flow producing a cooled exhaust gas. A method of operating the gas turbine includes opening an inlet guide vane of the compressor to allow the compressor to produce an increased volume of compressed air. The increased volume exceeds a volume of compressed air needed to support combustion. An excess portion of the compressed air is directed into the exhaust gas to produce a cooled exhaust. In a combined cycle power plant, the cooled exhaust from the gas turbine may be used to warm a steam turbine portion to a desired temperature while allowing operation of the gas turbine at a power level that produces exhaust gas at a temperature higher than the desired temperature.
摘要翻译：燃气轮机包括压缩机，燃烧器，涡轮机以及将由压缩机产生的压缩空气的多余部分转向涡轮机的流路。流路将过剩部分导入产生冷却废气的涡轮排气流中。操作燃气涡轮机的方法包括打开压缩机的入口引导叶片，以允许压缩机产生增加的压缩空气体积。体积增加超过支持燃烧所需的压缩空气体积。压缩空气的多余部分被引导到废气中以产生冷却的排气。在联合循环发电厂中，来自燃气涡轮机的冷却的排气可以用于将汽轮机部分加热到所需温度，同时允许燃气轮机在高于期望温度的温度下产生废气的功率水平。

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