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81. 发明授权

US07402022B2 Rotor blade containment assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的转子叶片容纳组件
公开(公告)号：US07402022B2
公开(公告)日：2008-07-22
申请号：US11088179
申请日：2005-03-24
申请人： Cedric Brett Harper , Ian Graham Martindale
发明人： Cedric Brett Harper , Ian Graham Martindale
IPC分类号： F01D21/00
CPC分类号： F01D21/045 , F05B2260/301 , F05D2260/30 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/211 , F05D2300/2261 , F05D2300/2283 , F05D2300/614 , F05D2300/702 , Y02T50/672
摘要： A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, casing (40). The casing (40) having at least one member (54) and the member (54) has a first portion (53) extending radially from the casing (40) and a second portion (55) extending axially from the first portion (53) of the member (54). At least one cassette (80) being provided and one or more liner panels (74) being arranged in each cassette (80). A first end (84) of each cassette (80) being locatable on the second portion (55) of the member (54) and the first end (84) of each cassette (80) being shaped to correspond to the shape of the first and second portions (53,55) of the at least one member (54) to protect the first and second portions (53,55) of the at least one member (54). The second end (86) of each cassette (80) having at least one axially extending member (96) removably securable to the casing (40).
摘要翻译：一种燃气涡轮发动机转子叶片容纳组件（38），其包括大致圆柱形或截头圆锥形的壳体（40）。具有至少一个构件（54）和构件（54）的壳体（40）具有从壳体（40）径向延伸的第一部分（53）和从第一部分（53）轴向延伸的第二部分（55）的成员（54）。设置至少一个盒（80）并且每个盒（80）中布置有一个或多个衬板（74）。每个盒（80）的第一端（84）可定位在构件（54）的第二部分（55）上，并且每个盒（80）的第一端（84）成形为对应于第一和所述至少一个构件（54）的第二部分（53,55），以保护所述至少一个构件（54）的第一和第二部分（53,55）。每个盒（80）的第二端（86）具有可拆卸地固定到壳体（40）的至少一个轴向延伸构件（96）。

82. 发明申请

US20080124512A1 CMC ARTICLES HAVING SMALL COMPLEX FEATURES 有权
标题翻译：具有小复杂特征的CMC文章
公开(公告)号：US20080124512A1
公开(公告)日：2008-05-29
申请号：US11563747
申请日：2006-11-28
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： B32B18/00 , B32B5/00
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 ceramic matrix composite (CMC) component for gas turbine engines, the component having fine features such as thin edges with thicknesses of less than about 0.030 inches and small radii of less that about 0.030 inches formed using the combination of prepreg plies layed up with non-ply ceramic inserts. 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：用于燃气涡轮发动机的陶瓷基体复合材料（CMC）组件，该组件具有细小的特征，例如厚度小于约0.030英寸的薄边缘和小于约0.030英寸的小半径，使用非预制片 - 陶瓷插件。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层嵌入物，导致更少的缺陷，例如皱纹，和更好的尺寸控制。

83. 发明申请

US20070148000A1 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：US20070148000A1
公开(公告)日：2007-06-28
申请号：US11315552
申请日：2005-12-22
申请人： Mark Williard Marusko , Suresh Subramanian
发明人： Mark Williard Marusko , Suresh Subramanian
IPC分类号： F01D11/00
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，由此平台预成型件和翼型坯预成型件的配合表面并列。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。

84. 发明授权

US07223465B2 SiC/SiC composites incorporating uncoated fibers to improve interlaminar strength 有权
标题翻译： SiC / SiC复合材料包含未涂覆的纤维，以提高层间强度
公开(公告)号：US07223465B2
公开(公告)日：2007-05-29
申请号：US11025510
申请日：2004-12-29
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： B32B17/12 , B32B15/04 , B32B11/00 , C04B35/00
CPC分类号： C04B35/573 , C04B35/565 , C04B35/62868 , C04B35/62871 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/806 , C04B2235/421 , C04B2235/524 , C04B2235/5244 , F01D5/282 , F01D5/284 , F05D2300/2261 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249928 , Y10T428/249929 , Y10T428/249931 , Y10T428/30 , Y10T442/2975
摘要： The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.
摘要翻译：本发明是一种陶瓷基体复合涡轮发动机部件，其中该部件在正常的发动机运转期间具有期望的较高的层间应力的区域。该组件包括一起布置成预选形式的涂覆的纤维束和未涂覆的纤维束，其中未涂覆的纤维束位于预期的高层间应力的预定区域。本发明还包括制造诸如复合涡轮发动机部件的CMC的方法，其中所述部件在发动机操作期间具有期望的较高的层间应力的区域。

85. 发明申请

US20070003416A1 Niobium silicide-based turbine components, and related methods for laser deposition 审中-公开
标题翻译：基于铌硅化物的涡轮机组件以及相关的激光沉积方法
公开(公告)号：US20070003416A1
公开(公告)日：2007-01-04
申请号：US11172390
申请日：2005-06-30
申请人： Bernard Patrick Bewlay , Magdi Azer , Laurent Cretegny , Ann Melinda Ritter , Craig Douglas Young
发明人： Bernard Patrick Bewlay , Magdi Azer , Laurent Cretegny , Ann Melinda Ritter , Craig Douglas Young
IPC分类号： F03B3/12 , B05D3/00 , B05D1/36 , B05D7/00
CPC分类号： F01D5/288 , B22F5/009 , B22F5/04 , B22F2998/00 , B23K26/144 , B23K26/32 , B23K26/34 , B23K35/327 , B23K2101/001 , B23K2103/08 , B23K2103/18 , B23K2103/26 , B23K2103/50 , B23P6/007 , B23P15/02 , C22C27/02 , C22C29/18 , C23C24/10 , F01D5/005 , F01D5/28 , F05D2230/13 , F05D2230/31 , F05D2230/80 , F05D2230/90 , F05D2300/2261 , B22F2207/01
摘要： A turbine component formed from a niobium silicide-based composition is described. The component can be compositionally-graded through at least a portion of its structure. A turbine blade formed from a composition which includes a niobium silicide alloy is also described. The blade includes an airfoil; an airfoil tip region; a platform on which the airfoil is mounted; and a dovetail root attached to an underside of the platform. The niobium silicide alloy in at least one portion of the turbine blade is compositionally different from the niobium silicide alloy in another portion of the blade. Processes for fabricating a niobium silicide-based turbine article are also described, using laser cladding techniques. Repair methods are also set forth in the application.
摘要翻译：描述了由基于硅化铌的组合物形成的涡轮机部件。组分可以通过其结构的至少一部分成分分级。还描述了由包括硅化铌合金的组合物形成的涡轮机叶片。叶片包括翼型件; 机翼尖端区域; 安装翼型的平台; 以及连接到平台下侧的燕尾根。涡轮叶片的至少一部分中的铌硅化物合金在组成上不同于叶片的另一部分中的铌硅化物合金。还描述了使用激光熔覆技术制造硅化铌基涡轮制品的方法。修理方法也在本申请中列出。

86. 发明申请

US20060141257A1 SiC/SiC composites incorporating uncoated fibers to improve interlaminar strength 有权
标题翻译： SiC / SiC复合材料包含未涂覆的纤维，以提高层间强度
公开(公告)号：US20060141257A1
公开(公告)日：2006-06-29
申请号：US11025510
申请日：2004-12-29
申请人： Suresh Subramanian , James Steibel , Douglas Carper
发明人： Suresh Subramanian , James Steibel , Douglas Carper
IPC分类号： B32B9/00
CPC分类号： C04B35/573 , C04B35/565 , C04B35/62868 , C04B35/62871 , C04B35/62873 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B35/806 , C04B2235/421 , C04B2235/524 , C04B2235/5244 , F01D5/282 , F01D5/284 , F05D2300/2261 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y10T428/249928 , Y10T428/249929 , Y10T428/249931 , Y10T428/30 , Y10T442/2975
摘要： The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.
摘要翻译：本发明是一种陶瓷基体复合涡轮发动机部件，其中该部件在正常的发动机运转期间具有期望的较高的层间应力的区域。该组件包括一起布置成预选形式的涂覆的纤维束和未涂覆的纤维束，其中未涂覆的纤维束位于预期的高层间应力的预定区域。本发明还包括制造诸如复合涡轮发动机部件的CMC的方法，其中所述部件在发动机操作期间具有期望的较高的层间应力的区域。

87. 发明申请

US20060140771A1 Ceramic composite with integrated compliance/wear layer 有权
公开(公告)号：US20060140771A1
公开(公告)日：2006-06-29
申请号：US11025222
申请日：2004-12-29
申请人： Douglas Carper , Suresh Subramanian
发明人： Douglas Carper , Suresh Subramanian
IPC分类号： F03B3/12
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.

88. 发明申请

US20060029814A1 Thermal resistant environmental barrier coating 有权
标题翻译：耐热环保屏障涂层
公开(公告)号：US20060029814A1
公开(公告)日：2006-02-09
申请号：US10915158
申请日：2004-08-09
申请人： Tania Bhatia , Harry Eaton , Ellen Sun , Thomas Lawton
发明人： Tania Bhatia , Harry Eaton , Ellen Sun , Thomas Lawton
IPC分类号： B32B17/06 , B32B9/00 , B32B19/00 , B05D5/06
CPC分类号： F01D5/288 , C04B41/009 , C04B41/5024 , C04B41/52 , C23C4/10 , C23C28/042 , C23C28/048 , F05D2230/313 , F05D2230/314 , F05D2230/90 , F05D2300/222 , F05D2300/2261 , F05D2300/611 , C04B41/5027 , C04B41/4582 , C04B41/5042 , C04B41/5045 , C04B41/5041 , C04B41/5035 , C04B41/5037 , C04B41/5051 , C04B35/565 , C04B35/584 , C04B35/806
摘要： A process for preparing a silicon based substrate with a protective coating having improved thermal resistance at temperature up to at least 1500° C., and the resulting article.
摘要翻译：一种制备具有保护涂层的硅基基材的方法，其具有在至多1500℃的温度下具有改善的耐热性，以及所得制品。

89. 发明申请

US20050271503A1 Rotor blade containment assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的转子叶片容纳组件
公开(公告)号：US20050271503A1
公开(公告)日：2005-12-08
申请号：US11088179
申请日：2005-03-24
申请人： Cedric Harper , Ian Martindale
发明人： Cedric Harper , Ian Martindale
IPC分类号： F01D21/04 , F01D25/24 , F01D21/00
CPC分类号： F01D21/045 , F05B2260/301 , F05D2260/30 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/211 , F05D2300/2261 , F05D2300/2283 , F05D2300/614 , F05D2300/702 , Y02T50/672
摘要： A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, casing (40). The casing (40) having at least one member (54) and the member (54) has a first portion (53) extending radially from the casing (40) and a second portion (55) extending axially from the first portion (53) of the member (54). At least one cassette (80) being provided and one or more liner panels (74) being arranged in each cassette (80). A first end (84) of each cassette (80) being locatable on the second portion (55) of the member (54) and the first end (84) of each cassette (80) being shaped to correspond to the shape of the first and second portions (53,55) of the at least one member (54) to protect the first and second portions (53,55) of the at least one member (54). The second end (86) of each cassette (80) having at least one axially extending member (96) removably securable to the casing (40).
摘要翻译：一种燃气涡轮发动机转子叶片容纳组件（38），其包括大致圆柱形或截头圆锥形的壳体（40）。具有至少一个构件（54）和构件（54）的壳体（40）具有从壳体（40）径向延伸的第一部分（53）和从第一部分（53）轴向延伸的第二部分（55）的成员（54）。设置至少一个盒（80）并且每个盒（80）中布置有一个或多个衬板（74）。每个盒（80）的第一端（84）可定位在构件（54）的第二部分（55）上，并且每个盒（80）的第一端（84）成形为对应于第一和所述至少一个构件（54）的第二部分（53,55），以保护所述至少一个构件（54）的第一和第二部分（53,55）。每个盒（80）的第二端（86）具有可拆卸地固定到壳体（40）的至少一个轴向延伸构件（96）。

90. 发明授权

US06893214B2 Shroud segment and assembly with surface recessed seal bridging adjacent members 有权
标题翻译：护罩段和组件，其表面凹入密封桥接相邻构件
公开(公告)号：US06893214B2
公开(公告)日：2005-05-17
申请号：US10325779
申请日：2002-12-20
申请人： Mary Ellen Alford , Toby George Darkins , Mark Eugene Noe
发明人： Mary Ellen Alford , Toby George Darkins , Mark Eugene Noe
IPC分类号： F01D5/28 , F01D9/02 , F01D9/04 , F01D11/00 , F01D11/10 , F02C7/00 , F02C7/18 , F02C7/28 , F16J15/10 , F01D11/08
CPC分类号： F01D11/005 , F01D9/04 , F05C2203/0839 , F05D2240/11 , F05D2250/131 , F05D2300/21 , F05D2300/2261 , F05D2300/2283 , F05D2300/50 , F05D2300/603
摘要： A turbine engine shroud segment is provided with a radially outer surface including a pair of spaced apart, opposed first and second edge portion surface depressions, for example spaced circumferentially, having a seal surface shaped to receive, in a surface depression formed between assembled adjacent segments in a shroud assembly, or axially assembled adjacent segments and engine members, a radially outer fluid seal member. The depression portions of a shroud segment are joined with the radially outer surface of the shroud segment through an arcuate transition surface. Stresses generated during engine operation in the shroud material are reduced, enabling practical use of a low ductility material, for example a ceramic matrix composite. The edge portion surface depressions are provided with a first shape and the fluid seal member, disposed at the depression, is provided with a surface of a second shape matched in shape with the first shape.
摘要翻译：涡轮发动机护罩段设置有径向外表面，该径向外表面包括一对间隔开的相对的第一和第二边缘部分表面凹陷，例如周向间隔开，具有密封表面，该密封表面成形为在组合的相邻段之间形成的表面凹陷中在护罩组件中，或轴向组装的相邻节段和发动机构件，径向外部流体密封构件。护罩段的凹陷部分通过弓形过渡表面与护罩段的径向外表面接合。在护罩材料中的发动机运行期间产生的应力减小，使得可以实际使用低延展性材料，例如陶瓷基体复合材料。边缘部分表面凹陷设置有第一形状，并且设置在凹部处的流体密封构件设置有与第一形状匹配的第二形状的表面。

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