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1. 发明申请

US20090162674A1 TAPES COMPRISING BARRIER COATING COMPOSITIONS AND COMPONENTS COMPRISING THE SAME 审中-公开
标题翻译：包含障碍物涂料组合物的组合物和包含其的组分
公开(公告)号：US20090162674A1
公开(公告)日：2009-06-25
申请号：US11960762
申请日：2007-12-20
申请人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
发明人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
IPC分类号： B32B15/09
CPC分类号： C23C28/042 , C04B41/009 , C04B41/4501 , C04B41/81 , F01D5/288 , F05D2230/80 , F05D2300/2112 , F05D2300/2261 , F05D2300/2283 , Y10T428/31663 , C04B35/565 , C04B35/806 , C04B35/584 , C04B35/10 , C04B35/803 , C04B35/14 , C04B35/185 , C04B35/597 , C04B41/0072 , C04B41/4572 , C04B41/5024 , C04B41/5037 , C04B41/5096 , C04B41/5042 , C04B41/5044 , C04B41/5046 , C04B41/5032
摘要： Tapes including a carrier film, and at least one barrier coating composition applied to the carrier film where the barrier coating composition is an environmental barrier coating composition or a thermal barrier coating composition.
摘要翻译：包含载体膜的胶带以及施加到载体膜上的至少一种阻隔涂料组合物，其中阻隔涂料组合物是环境屏障涂料组合物或热障涂料组合物。

2. 发明申请

US20090162539A1 METHODS FOR REPAIRING BARRIER COATINGS 有权
标题翻译：修复遮瑕涂层的方法
公开(公告)号：US20090162539A1
公开(公告)日：2009-06-25
申请号：US11960764
申请日：2007-12-20
申请人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
发明人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
IPC分类号： B05D3/00
CPC分类号： B23P6/005 , C04B41/009 , C04B41/4501 , C04B41/81 , C23C26/00 , C23C28/042 , F01D5/005 , F01D5/284 , F01D5/288 , F05D2300/21 , F05D2300/2102 , F05D2300/2112 , F05D2300/2118 , C04B41/0072 , C04B41/4572 , C04B41/5032 , C04B41/53 , C04B41/5046 , C04B41/5044 , C04B41/5042 , C04B41/5096 , C04B41/5037 , C04B41/5024 , C04B35/565 , C04B35/806 , C04B35/584 , C04B35/10 , C04B35/803 , C04B35/14 , C04B35/185 , C04B35/597
摘要： Methods for repairing barrier coatings involving providing a component having a barrier coating including at least one damaged portion, removing the damaged portion of the barrier coating leaving a void, applying a replacement tape cast barrier coating to the void of the component, and sintering the component having the replacement tape cast barrier coating layer.
摘要翻译：用于修复阻挡涂层的方法，包括提供具有阻挡涂层的部件，所述阻挡涂层包括至少一个损伤部分，去除所述阻挡涂层的损坏部分留下空隙，向所述部件的空隙施加替代的带状阻挡涂层，以及烧结所述部件具有替代的带状阻挡涂层。

3. 发明授权

US08173206B2 Methods for repairing barrier coatings 有权
标题翻译：修补阻隔涂层的方法
公开(公告)号：US08173206B2
公开(公告)日：2012-05-08
申请号：US11960764
申请日：2007-12-20
申请人： Brett Allen Boutwell , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
发明人： Brett Allen Boutwell , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
IPC分类号： B05C13/00
CPC分类号： B23P6/005 , C04B41/009 , C04B41/4501 , C04B41/81 , C23C26/00 , C23C28/042 , F01D5/005 , F01D5/284 , F01D5/288 , F05D2300/21 , F05D2300/2102 , F05D2300/2112 , F05D2300/2118 , C04B41/0072 , C04B41/4572 , C04B41/5032 , C04B41/53 , C04B41/5046 , C04B41/5044 , C04B41/5042 , C04B41/5096 , C04B41/5037 , C04B41/5024 , C04B35/565 , C04B35/806 , C04B35/584 , C04B35/10 , C04B35/803 , C04B35/14 , C04B35/185 , C04B35/597
摘要： Methods for repairing barrier coatings involving providing a component having a barrier coating including at least one damaged portion, removing the damaged portion of the barrier coating leaving a void, applying a replacement tape cast barrier coating to the void of the component, and sintering the component having the replacement tape cast barrier coating layer.
摘要翻译：用于修复阻挡涂层的方法，包括提供具有阻挡涂层的部件，所述阻挡涂层包括至少一个损伤部分，去除所述阻挡涂层的损坏部分留下空隙，向所述部件的空隙施加替代的带状阻挡涂层，以及烧结所述部件具有替代的带状阻挡涂层。

4. 发明申请

US20090162556A1 METHODS FOR MAKING TAPE CAST BARRIER COATINGS, COMPONENTS COMPRISING THE SAME AND TAPES MADE ACCORDING TO THE SAME 审中-公开
标题翻译：用于制造带状阻挡层涂层的方法，包括其的组件和根据其制成的胶带
公开(公告)号：US20090162556A1
公开(公告)日：2009-06-25
申请号：US11960763
申请日：2007-12-20
申请人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
发明人： BRETT ALLEN BOUTWELL , Glen Harold Kirby , Jessica Lee Licardi , Jeffrey Allan Pfaendtner , James Dale Steibel
IPC分类号： B05D3/12 , B05D3/02 , C09D1/00
CPC分类号： C23C26/00 , C23C28/042
摘要： Methods for making tape cast barrier coatings involving making a slurry including at least a solvent and a barrier coating composition, depositing the slurry onto a carrier film in a tape casting machine to produce a cast slurry, evaporating the solvent from the cast slurry to produce a tape including the carrier film, and the barrier coating composition, and removing the carrier film from the tape to produce a tape cast barrier coating.
摘要翻译：制造带状阻挡涂层的方法包括制备至少包括溶剂和阻挡涂层组合物的浆料，将浆料沉积在带铸机中的载体膜上以产生铸造浆料，从铸浆中蒸发溶剂以产生胶带和阻隔涂料组合物，并从胶带上除去载体膜以制备带状阻挡涂层。

5. 发明申请

US20110229337A1 HYBRID CERAMIC MATRIX COMPOSITE TURBINE BLADES FOR IMPROVED PROCESSIBILITY AND PERFORMANCE AND PROCESS FOR PRODUCING HYBRID TURBINE BLADES 审中-公开
标题翻译：混合陶瓷基体复合涡轮叶片，用于改进混合涡轮叶片的可行性和性能及工艺
公开(公告)号：US20110229337A1
公开(公告)日：2011-09-22
申请号：US12828266
申请日：2010-06-30
申请人： Douglas Melton Carper , Suresh Subramanian , Richard William Jendrix , James Dale Steibel
发明人： Douglas Melton Carper , Suresh Subramanian , Richard William Jendrix , James Dale Steibel
IPC分类号： F01D5/14 , C03B29/00
CPC分类号： C04B35/565 , B32B18/00 , B32B2311/22 , B32B2315/02 , C04B35/62863 , C04B35/62868 , C04B35/62871 , C04B35/62873 , C04B2235/422 , C04B2235/428 , C04B2235/5244 , C04B2235/5248 , C04B2235/5256 , C04B2235/5268 , C04B2235/616 , C04B2235/80 , C04B2237/361 , C04B2237/363 , C04B2237/365 , C04B2237/368 , C04B2237/38 , C04B2237/61 , F01D5/282 , F01D5/284 , F05D2300/2261 , F05D2300/603 , Y02T50/67 , Y02T50/672
摘要： The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using a melt infiltration (MI) process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.
摘要翻译：本发明是一种混合陶瓷基复合涡轮发动机部件，其包括外壳部分和内芯部分，其中外壳部分和内芯部分使用熔融渗透（MI）工艺。外壳部分包括使用选自淤浆浇铸MI工艺和预浸料MI工艺的工艺制造的SiC / SiC材料。内芯部分包括选自Si / SiC复合材料和单块陶瓷材料的材料。 Si / SiC复合材料可以使用Silcomp工艺制造。本发明可以是高压涡轮叶片，高压涡轮叶片，低压涡轮叶片或低压涡轮叶片。本发明也是制造混合陶瓷基复合涡轮发动机部件的方法。

6. 发明授权

US07837914B2 Process of producing a composite component and intermediate product thereof 有权
标题翻译：复合成分及其中间体的制造方法
公开(公告)号：US07837914B2
公开(公告)日：2010-11-23
申请号：US11566370
申请日：2006-12-04
申请人： Timothy Daniel Kostar , Douglas Melton Carper , Suresh Subramanian , James Dale Steibel
发明人： Timothy Daniel Kostar , Douglas Melton Carper , Suresh Subramanian , James Dale Steibel
IPC分类号： C04B35/00 , B29C44/04
CPC分类号： D03D15/00 , C04B35/80 , C04B2235/5244 , C04B2235/5252 , C04B2235/5264 , C04B2235/5268 , C04B2235/6028 , D03D15/0083 , D03D25/005 , D10B2101/08 , D10B2401/062 , D10B2401/063 , D10B2505/02 , F01D5/284 , F05D2300/2261 , F05D2300/2283 , F05D2300/614 , Y10T428/24058 , Y10T428/24107 , Y10T428/24132 , Y10T428/24149 , Y10T428/24157 , Y10T428/249929 , Y10T428/2973 , Y10T442/3195 , Y10T442/322
摘要： A preform architecture and process for producing composite materials, and particularly CMC components. The process entails producing a composite component having a matrix material reinforced with a three-dimensional preform. The process includes producing first and second sets of tows containing filaments. Each tow of the first set has a predetermined cross-sectional shape and is embedded within a temporary matrix material formed of a material that is not the matrix material or a precursor of the matrix material. The preform is then fabricated from the first and second sets of tows, in which the second set of tows are transverse to the first set of tows, adjacent tows of the second set are spaced apart to define interstitial regions therebetween, and the cross-sectional shapes of the first set of tows are substantially congruent to the cross-sectional shapes of the interstitial regions so as to substantially fill the interstitial regions.
摘要翻译：用于生产复合材料的预型体结构和工艺，特别是CMC组件。该方法需要生产具有用三维预成型体增强的基体材料的复合部件。该方法包括产生含有长丝的第一组和第二组丝束。第一组的每个丝束具有预定的横截面形状，并且嵌入由不是基质材料或基质材料的前体的材料形成的临时基质材料中。然后从第一组和第二组丝束制造预成型件，其中第二组丝束横向于第一组丝束，相邻的第二组丝束间隔开以限定它们之间的间隙区域，并且横截面第一组丝束的形状基本上与间隙区域的横截面形状一致，以便基本上填充间隙区域。

7. 发明授权

US07754126B2 Interlaminar tensile reinforcement of SiC/SiC CMC's using fugitive fibers 有权
标题翻译： SiC / SiC CMC使用逃逸纤维的层间拉伸强化
公开(公告)号：US07754126B2
公开(公告)日：2010-07-13
申请号：US11155190
申请日：2005-06-17
申请人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper
发明人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper
IPC分类号： B29C70/40 , C04B35/64 , F01D5/14
CPC分类号： F01D5/28 , C04B35/573 , C04B35/806 , C04B38/065 , C04B2111/00982 , C04B2235/5212 , C04B2235/5244 , C04B2235/5252 , C04B2235/5256 , C04B2235/5268 , C04B2235/616 , F05D2300/222 , F05D2300/224 , F05D2300/601 , F05D2300/6012 , F05D2300/603 , Y02T50/67 , Y02T50/672 , Y10T29/49337 , C04B38/067 , C04B38/0675
摘要： A method of manufacturing a turbine engine component is disclosed. The method includes the steps of providing a plurality of ceramic cloth plies, each ply having woven ceramic fiber tows and at least one fugitive fiber tow, laying up the plurality of plies in a preselected arrangement to form a turbine engine component shape, oxidizing the fugitive fibers to produce fugitive fiber void regions in the ply, rigidizing the component shape to form a coated component preform using chemical vapor infiltration, partially densifying the coated component preform using carbon-containing slurry, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component having matrix rich regions.
摘要翻译：公开了一种制造涡轮发动机部件的方法。该方法包括以下步骤：提供多个陶瓷布层，每个层具有编织的陶瓷纤维丝束和至少一个短纤维丝束，以预选布置布置多个层以形成涡轮发动机部件的形状，从而氧化该流体纤维以在帘布层中产生短纤维空隙区域，使组分形状硬化，以形成使用化学气相渗透的涂层组分预成型件，使用含碳浆料部分致密化涂覆的组件预成型体，并进一步使至少具有硅的致密化涂层组件预制件形成具有基质富集区域的陶瓷基复合涡轮发动机部件。

8. 发明授权

US07549840B2 Through thickness reinforcement of SiC/SiC CMC's through in-situ matrix plugs manufactured using fugitive fibers 有权
标题翻译：通过SiC / SiC CMC通过使用短效纤维制造的原位基质插塞的厚度增强
公开(公告)号：US07549840B2
公开(公告)日：2009-06-23
申请号：US11155786
申请日：2005-06-17
申请人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper
发明人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper
IPC分类号： F01D9/02 , F01D5/12 , F01D25/12
CPC分类号： F01D5/14 , C04B35/573 , C04B35/62863 , C04B35/62868 , C04B35/62884 , C04B35/62894 , C04B35/806 , C04B38/065 , C04B2111/00982 , C04B2235/422 , C04B2235/5212 , C04B2235/5244 , C04B2235/614 , C04B2235/616 , F01D5/284 , F05C2253/24 , F05D2300/2261 , F05D2300/6012 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , C04B35/565 , C04B38/067 , C04B38/0675
摘要： A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that each fugitive fiber tow passes through a preselected number of ceramic plies, burning off the fugitive fiber tows, the burning producing through-thickness void regions, rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration, and partially densifying the coated component preform using carbon-containing slurry and filling the through thickness void regions, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.
摘要翻译：一种制造涡轮发动机部件的方法，包括以下步骤：提供和铺设多个包括编织陶瓷纤维丝束的陶瓷层，以形成涡轮发动机部件形状，将多个可氧化的短串纤维束插入到部件形状中，使得每根短纤维丝束通过预先选定数量的陶瓷层，烧掉短纤维丝束，燃烧产生厚度的空隙区域，用一层BN和一层SiC硬化组件形状以形成涂层组件预成型件，使用化学气相渗透，并使用含碳浆料部分致密化涂覆的部件预制件，并填充贯穿厚度的空隙区域，并进一步使涂覆的部件预成型件至少具有硅致密化，以形成具有原位陶瓷基体的陶瓷基体复合涡轮发动机部件塞子形成在贯穿厚度的空隙区域的位置。

9. 发明授权

US06316048B1 Methods for providing ceramic matrix composite components with increased thermal capacity 有权
标题翻译：提供具有增加的热容量的陶瓷基复合材料组件的方法
公开(公告)号：US06316048B1
公开(公告)日：2001-11-13
申请号：US09613881
申请日：2000-07-11
申请人： James Dale Steibel , David Alan Utah
发明人： James Dale Steibel , David Alan Utah
IPC分类号： B05D112
CPC分类号： C04B41/009 , C04B35/573 , C04B35/806 , C04B41/5059 , F01D5/284 , F01D5/288 , F05D2240/31 , F05D2260/2212 , F05D2260/2214 , Y02T50/67 , Y02T50/672 , Y02T50/673 , Y02T50/676 , C04B41/4539 , C04B41/5096 , C04B35/565
摘要： A method for enhancing the cooling capability of a turbine component made from a ceramic matrix composite. The method improves the thermal performance of the component by producing a surface having increased cooling capacity, thereby allowing the component to operate at a higher temperature. The method tailors the available surface area on the cooling surface of the composite component by depositing a particulate layer of coarse grained ceramic powders of preselected size onto the surface of the ceramic matrix composite component. The size of the particulate is selectively tailored to match the desired surface finish or surface roughness of the article. The article may be designed to have different surface finishes for different locations, so that the application of different sized powders can provide different cooling capabilities at different locations, if desired. The compositions of the particulates are chemically compatible with the ceramic material comprising the outer surface or portion of the ceramic matrix composite. The particulates are applied using a slurry and incorporated into the article by heating to an elevated temperature without melting the matrix, the particulates or the fiber reinforcement.
摘要翻译：一种用于增强由陶瓷基体复合材料制成的涡轮部件的冷却能力的方法。该方法通过产生具有增加的冷却能力的表面来提高部件的热性能，从而允许部件在较高温度下操作。该方法通过将预选尺寸的粗颗粒陶瓷粉末的颗粒层沉积到陶瓷基复合材料组件的表面上来调整复合组件的冷却表面上的可用表面积。选择性地调整颗粒的尺寸以匹配制品的期望的表面光洁度或表面粗糙度。该制品可以被设计成对于不同的位置具有不同的表面光洁度，使得不同尺寸的粉末的应用可以在不同的位置提供不同的冷却能力，如果需要的话。颗粒的组成与包含陶瓷基质复合材料的外表面或部分的陶瓷材料化学相容。使用浆料施加颗粒并通过加热到升高的温度而不熔化基质，颗粒或纤维增强物而掺入制品中。

10. 发明授权

US07597838B2 Functionally gradient SiC/SiC ceramic matrix composites with tailored properties for turbine engine applications 有权
标题翻译：功能梯度SiC / SiC陶瓷基体复合材料，适用于涡轮发动机应用
公开(公告)号：US07597838B2
公开(公告)日：2009-10-06
申请号：US11027403
申请日：2004-12-30
申请人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper , Toby George Darkins, Jr.
发明人： Suresh Subramanian , James Dale Steibel , Douglas Melton Carper , Toby George Darkins, Jr.
IPC分类号： B32B17/12 , B32B15/04 , C04B35/00 , C04B33/34 , C04B35/64
CPC分类号： C04B35/806 , C04B35/565 , C04B35/62863 , C04B35/62865 , C04B35/62868 , C04B35/62871 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B2235/522 , C04B2235/5224 , C04B2235/5232 , C04B2235/524 , C04B2235/5244 , C04B2235/5248 , C04B2235/5264 , C04B2235/80 , F01D5/282 , F01D5/284 , F05C2203/0839 , F05D2300/2261 , F05D2300/2283 , F05D2300/603 , Y02T50/672 , Y10T428/2495 , Y10T428/24975 , Y10T428/249924 , Y10T428/249928 , Y10T428/249929 , Y10T428/24993 , Y10T428/249931 , Y10T428/249939 , Y10T428/24994 , Y10T428/249941 , Y10T428/265 , Y10T442/2975
摘要： A ceramic matrix composite with a ceramic matrix and a gradient layering of coating on ceramic fibers. The coating typically improves the performance of the composite in one direction while degrading it in another direction. For a SiC-SiC ceramic matrix composite, a BN coating is layered in a gradient fashion or in a step-wise fashion in different regions of the article comprising the ceramic. The BN coating thickness is applied over the ceramic fibers to produce varying desired physical properties by varying the coating thickness within differing regions of the composite, thereby tailoring the strength of the composite in the different regions. The coating may be applied as a single layer as a multi-layer coating to enhance the performance of the coating as the ceramic matrix is formed or infiltrated from precursor materials into a preform of the ceramic fibers.
摘要翻译：陶瓷基复合陶瓷基体和陶瓷纤维上涂层的梯度分层。涂层通常在一个方向上改善复合材料的性能，同时使其在另一方向上降解。对于SiC-SiC陶瓷基质复合材料，在包含陶瓷的制品的不同区域中，以梯度或逐步的方式层叠BN涂层。通过改变复合材料的不同区域内的涂层厚度，在陶瓷纤维上施加BN涂层厚度以产生变化的所需物理性能，由此调整复合材料在不同区域中的强度。作为多层涂层，可以将涂层作为单层施加，以在陶瓷基体由前体材料形成或从陶瓷纤维的预成型体中渗透时提高涂层的性能。

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