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11. 发明申请

US20090261508A1 MANUFACTURE OF CMC ARTICLES HAVING SMALL COMPLEX FEATURES 审中-公开
标题翻译：具有小复杂特征的CMC制品的制造
公开(公告)号：US20090261508A1
公开(公告)日：2009-10-22
申请号：US12372368
申请日：2009-02-17
申请人： James D. STEIBEL , Stephen M. WHITEKER , Douglas M. CARPER , Suresh SUBRAMANIAN
发明人： James D. STEIBEL , Stephen M. WHITEKER , Douglas M. CARPER , Suresh SUBRAMANIAN
IPC分类号： C04B35/622
CPC分类号： F01D5/284 , B32B18/00 , C04B35/573 , C04B35/62863 , C04B35/62868 , C04B35/806 , C04B2235/5244 , C04B2235/5256 , C04B2235/5268 , C04B2237/32 , C04B2237/363 , C04B2237/365 , C04B2237/38 , C04B2237/61 , C04B2237/704 , F01D5/282 , F01D5/288 , F05C2203/0839 , F05D2230/90 , F05D2250/312 , F05D2300/2261 , F05D2300/2283 , F05D2300/611 , Y02T50/67 , Y02T50/672 , Y10T428/249928 , Y10T428/249929
摘要： The present invention is ceramic matrix composite gas turbine engine component comprising a plurality of cured ceramic matrix composite plies, each ply comprising ceramic fiber tows, each ceramic fiber tow comprising a plurality of ceramic fibers, the tows in each ply lying adjacent to one another such that each ply has a unidirectional orientation. The component further comprises a layer of a coating on the ceramic fibers. The component further comprises a ceramic matrix material lying in interstitial regions between the fibers and tows of each ply and the interstitial region between the plurality of plies, wherein at least a portion of the component is no greater than about 0.021 inch thick. The present invention is also a method for making such a ceramic matrix composite component.
摘要翻译：本发明是一种陶瓷基复合燃气轮机发动机零件，它包括多个固化的陶瓷基体复合层，每个层包括陶瓷纤维丝束，每个陶瓷纤维丝束包括多个陶瓷纤维，每个帘布层中的丝束彼此相邻，如每个帘布层都具有单向取向。该组件还包括在陶瓷纤维上的一层涂层。该组件还包括位于每个帘布层的纤维和丝束之间的间隙区域中的陶瓷基质材料和多个层之间的间隙区域，其中该组分的至少一部分不大于约0.021英寸厚。本发明也是制造这种陶瓷基复合材料成分的方法。

12. 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。

13. 发明授权

US07510379B2 Composite blading member and method for making 有权
标题翻译：复合叶片及其制造方法
公开(公告)号：US07510379B2
公开(公告)日：2009-03-31
申请号：US11315552
申请日：2005-12-22
申请人： Mark Willard Marusko , Suresh Subramanian
发明人： Mark Willard Marusko , Suresh Subramanian
IPC分类号： F03D11/02
CPC分类号： F01D5/282 , F05D2230/23 , F05D2300/2261 , F05D2300/603 , Y10T29/49336 , Y10T29/49337
摘要： A composite blading member includes an airfoil and a base of composite material layers and a platform of composite material layers interfused with the airfoil and base. The platform comprises a platform shelf and a plurality of spaced-apart platform supports integral with the platform shelf and interfused with surfaces of the base. Such blading member was made by providing a partially cured airfoil-base preform and a platform preform, including an airfoil shaped opening therethrough and preforms of the platform supports. The airfoil-base preform was inserted through the airfoil shaped opening whereby cooperating surfaces of the platform preform and airfoil-base preform were in juxtaposition. The preforms were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms under conditions to substantially fully cure the structures.
摘要翻译：复合叶片构件包括翼型件和复合材料层的基部以及与翼型件和基座相互连接的复合材料层的平台。该平台包括平台架和与平台架一体的多个间隔开的平台支架，并与底座的表面相互连接。通过提供部分固化的翼型坯预成型件和平台预成型件，包括通过其的翼型形状的开口和平台支撑件的预制件来制造这种叶片构件。将翼型坯预成型件插入通过翼型形状的开口，由此平台预制件和翼型坯预制件的配合表面并列。将预成型件加热以将它们部分固化在一起。然后在与基体完全固化结构的条件下，将它们与与预型件的材料相容的粘合剂进行混合。

14. 发明授权

US07329101B2 Ceramic composite with integrated compliance/wear layer 有权
标题翻译：陶瓷复合材料具有一体化/耐磨层
公开(公告)号：US07329101B2
公开(公告)日：2008-02-12
申请号：US11025222
申请日：2004-12-29
申请人： Douglas Melton Carper , Suresh Subramanian
发明人： Douglas Melton Carper , Suresh Subramanian
IPC分类号： F01D5/30
CPC分类号： C04B35/62863 , C04B35/565 , C04B35/573 , C04B35/58 , C04B35/58092 , C04B35/583 , C04B35/62868 , C04B35/62871 , C04B35/62884 , C04B35/62894 , C04B35/806 , C04B2235/3826 , C04B2235/386 , C04B2235/3873 , C04B2235/404 , C04B2235/421 , C04B2235/428 , C04B2235/5244 , C04B2235/5256 , C04B2235/75 , C04B2235/80 , F01D5/282 , F01D5/284 , F01D5/3092 , F05D2300/222 , F05D2300/2261 , Y02T50/672 , Y10T29/49236
摘要： The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.
摘要翻译：整体层为涡轮发动机部件的附接位置提供延性界面，其中金属表面邻近附接位置。韧性层通过复合材料在附着位置提供有利的载荷分布，并且不需要金属垫片。

15. 发明申请

US20070175535A1 ORTHOGONAL WEAVING FOR COMPLEX SHAPE PREFORMS 审中-公开
标题翻译：正交形状复合形状预制
公开(公告)号：US20070175535A1
公开(公告)日：2007-08-02
申请号：US11550838
申请日：2006-10-19
申请人： Timothy KOSTAR , Douglas CARPER , Suresh SUBRAMANIAN
发明人： Timothy KOSTAR , Douglas CARPER , Suresh SUBRAMANIAN
IPC分类号： D03D3/00
CPC分类号： C04B35/83 , B28B19/00 , C04B35/573 , C04B2235/5224 , C04B2235/5228 , C04B2235/5244 , C04B2235/5256 , D03D25/005 , D03D41/004 , Y10T442/3195
摘要： An orthogonal stitch-weave method and fiber architecture. The architecture allows near-net-shape composite preforms to be fabricated, thereby reducing costs associated with complex preform shapes and increasing desired strengths of the composite.
摘要翻译：正交缝编织法和纤维架构。该结构允许制造近净形复合预成型件，从而降低与复合预成型件形状相关联的成本并增加复合材料的期望强度。

16. 发明申请

US20070072007A1 HYBRID CERAMIC MATRIX COMPOSITE TURBINE BLADES FOR IMPROVED PROCESSIBILITY AND PERFORMANCE 审中-公开
标题翻译：混合陶瓷基体复合涡轮叶片改进的可行性和性能
公开(公告)号：US20070072007A1
公开(公告)日：2007-03-29
申请号：US11425723
申请日：2006-06-22
申请人： Douglas Carper , Suresh Subramanian , Richard Jendrix , James Steibel
发明人： Douglas Carper , Suresh Subramanian , Richard Jendrix , James Steibel
IPC分类号： F03B3/12 , B32B9/00
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 an 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 MI过程。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。

17. 发明申请

US20060147688A1 Functionally gradient SiC/SiC ceramic matrix composites with tailored properties for turbine engine applications 有权
公开(公告)号：US20060147688A1
公开(公告)日：2006-07-06
申请号：US11027403
申请日：2004-12-30
申请人： Suresh Subramanian , James Steibel , Douglas Carper , Toby Darkins
发明人： Suresh Subramanian , James Steibel , Douglas Carper , Toby Darkins
IPC分类号： D04H1/00
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.

18. 发明申请

US20050233151A1 Data storage media 审中-公开
标题翻译：数据存储介质
公开(公告)号：US20050233151A1
公开(公告)日：2005-10-20
申请号：US11151494
申请日：2005-06-13
申请人： Thomas Feist , Wit Bushko , Kevin Dal , Daniel Furlano , Ramesh Hariharan , Kazunao Kubotera , Bernard Landa , Suresh Subramanian , Joseph Woods
发明人： Thomas Feist , Wit Bushko , Kevin Dal , Daniel Furlano , Ramesh Hariharan , Kazunao Kubotera , Bernard Landa , Suresh Subramanian , Joseph Woods
IPC分类号： G11B5/65 , B29C43/02 , B32B1/00 , B32B9/04 , B32B27/00 , G11B5/72 , G11B5/73 , G11B5/84 , G11B7/005 , G11B7/253 , G11B7/257 , G11B7/258 , G11B7/26 , G11B11/105 , G11C13/02
CPC分类号： B82Y30/00 , B29C43/021 , B29C2043/025 , B29D17/005 , B29L2017/005 , B82Y10/00 , G11B5/72 , G11B5/73 , G11B5/7315 , G11B5/84 , G11B5/8404 , G11B5/855 , G11B7/24038 , G11B7/24047 , G11B7/24056 , G11B7/253 , G11B7/2531 , G11B7/2532 , G11B7/2533 , G11B7/2534 , G11B7/2536 , G11B7/2542 , G11B7/2548 , G11B7/2578 , G11B7/258 , G11B7/259 , G11B7/26 , G11B7/263 , G11B11/10582 , G11B11/10584 , G11B11/10586 , G11B2007/25708 , G11B2007/25713 , G11C13/02 , G11C13/025 , Y10T29/49002 , Y10T29/4902 , Y10T29/4903 , Y10T29/49043 , Y10T29/49069 , Y10T29/49158 , Y10T29/49172 , Y10T29/49176 , Y10T156/1002 , Y10T428/24355 , Y10T428/24479 , Y10T428/24967 , Y10T428/265 , Y10T428/266 , Y10T428/31 , Y10T428/3154
摘要： In one embodiment, the data storage media can comprise: a substrate, a data layer, and a reflective layer disposed between the data layer and the substrate. The substrate can comprise a substrate material selected from the group consisting of polyphenylene ether, blends comprising polyphenylene ether, copolymers comprising polyphenylene ether, mixtures comprising polyphenylene ether, reaction products of a compostion comprising polyphenylene ether, and composites comprising polyphenylene ether. The data layer can comprise a material selected from the group consisting of organic dye and inorganic phase change materials. The storage media can comprise imprinted features. In another embodiment, the first surface data storage media can comprise: a substrate, a reflective layer on a first side of the substrate, and a protective layer disposed on a side of the substrate opposite the first side. The protective layer can comprise silicon dioxide. The first surface data storage media comprises imprinted features.
摘要翻译：在一个实施例中，数据存储介质可以包括：衬底，数据层和布置在数据层和衬底之间的反射层。基材可以包括选自聚苯醚，包含聚苯醚的共混物，包含聚苯醚的共聚物，包含聚苯醚的混合物，包含聚苯醚的组合物的反应产物和包含聚苯醚的复合材料的基材。数据层可以包括选自有机染料和无机相变材料的材料。存储介质可以包括压印特征。在另一个实施例中，第一表面数据存储介质可以包括：衬底，在衬底的第一侧上的反射层，以及设置在衬底的与第一侧相对的一侧上的保护层。保护层可以包含二氧化硅。第一表面数据存储介质包括压印特征。

19. 发明授权

US09005382B2 Method of manufacturing CMC articles having small complex features 有权
标题翻译：制造具有小复杂特征的CMC制品的方法
公开(公告)号：US09005382B2
公开(公告)日：2015-04-14
申请号：US12554246
申请日：2009-09-04
申请人： James Dale Steibel , Douglas Melton Carper , Suresh Subramanian , Stephen Mark Whiteker
发明人： James Dale Steibel , Douglas Melton Carper , Suresh Subramanian , Stephen Mark Whiteker
IPC分类号： C03B29/00 , B32B37/00 , F01D5/14 , C04B35/573 , C04B35/628 , F01D5/28 , B29C45/14 , C04B35/622 , C04B35/80 , B32B18/00
CPC分类号： F01D5/147 , B32B18/00 , C04B35/573 , C04B35/62227 , C04B35/62863 , C04B35/62868 , C04B35/62871 , C04B35/80 , C04B35/806 , C04B2235/5252 , C04B2235/526 , C04B2235/5268 , C04B2235/602 , C04B2235/6028 , C04B2235/604 , F01D5/282 , F01D5/284 , F05C2203/0839 , F05D2300/21 , F05D2300/2261 , F05D2300/2283 , F05D2300/44 , F05D2300/603 , F05D2300/6034 , F05D2300/614 , Y02T50/67 , Y02T50/672 , Y10T156/10 , Y10T428/24058 , Y10T428/24124 , Y10T428/249929
摘要： A method for forming a ceramic matrix composite (CMC) component for gas turbine engines. The method contemplates replacing a plurality of plies with insert material. The insert material can be partially cured or pre-cured and applied in place of a plurality of small plies or it may be inserted into cavities of a component in the form of a paste or a ply. The insert material is isotropic, being formed of a combination of matrix material and chopped fibers, tow, cut plies or combinations thereof. The use of the insert material allows for features such as thin edges (650) with thicknesses of less than about 0.030 inches and small radii such as found in corners (680, 710). The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert, resulting in fewer defects, such as wrinkles, and better dimensional control.
摘要翻译：一种用于形成用于燃气涡轮发动机的陶瓷基体复合材料（CMC）组分的方法。该方法考虑用插入材料代替多个层。插入材料可以部分固化或预固化并且施加以代替多个小层，或者其可以插入到糊或层的形式的部件的空腔中。插入材料是各向同性的，由基质材料和短切纤维，丝束，切片或其组合的组合形成。使用插入材料允许诸如厚度小于约0.030英寸的薄边缘（650）和诸如角落（680,710）中发现的小半径的特征。本发明的CMC部件代替切割成尺寸的小层嵌入件以适应轮廓变化或厚度变化的区域，并且用制造的单件不连续增强的复合材料插入件代替小的层叠嵌件，导致较少的缺陷，例如皱纹，和更好的尺寸控制。

20. 发明授权

US08663778B2 Preforms, composite components formed therewith, and processes therefor 有权
标题翻译：预成型件，与其形成的复合部件及其工艺
公开(公告)号：US08663778B2
公开(公告)日：2014-03-04
申请号：US12905244
申请日：2010-10-15
申请人： Timothy Daniel Kostar , Douglas Melton Carper , Suresh Subramanian , James Dale Steible
发明人： Timothy Daniel Kostar , Douglas Melton Carper , Suresh Subramanian , James Dale Steible
IPC分类号： B32B5/12 , C04B35/00 , D03D15/00 , D03D25/00
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 three-dimensional preform, composite components formed with the preform, and processes for producing the preform and composite materials. The three-dimensional preform includes first and second sets of tows containing filaments. Each tow of the first set has a predetermined polygonal cross-sectional shape and is embedded within a temporary matrix. The preform is 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 polygonal 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：三维预制件，与预成型件形成的复合部件，以及用于生产预制件和复合材料的方法。三维预成型件包括第一组和第二组含有长丝的丝束。第一组的每个丝束具有预定的多边形横截面形状并且嵌入在临时矩阵内。预成型件由第一组和第二组丝束制成，其中第二组丝束横向于第一组丝束，第二组的相邻丝束间隔开以限定它们之间的间隙区域，并且多边形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。

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