-
公开(公告)号：US06739838B1
公开(公告)日：2004-05-25
申请号：US10388476
申请日：2003-03-17
申请人： Craig Allen Bielek , Robert Alan Brittingham , Jeff Brian Thompson , Benjamin Arnette Lagrange , Robert Walter Coign
发明人： Craig Allen Bielek , Robert Alan Brittingham , Jeff Brian Thompson , Benjamin Arnette Lagrange , Robert Walter Coign
IPC分类号： F01D514
CPC分类号： F01D5/141 , F01D5/225 , F05D2240/301 , F05D2240/80 , Y10S416/05
摘要： Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.060 inches in directions normal to the surface of the airfoil.
摘要翻译： 第三级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的机翼型材，其中X和Y值为英寸，Z值为从0到1的可转换为Z距离的无量纲值 将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。 X，Y和Z距离可以作为相同常数或数字的函数来缩放，以提供用于铲斗的放大或缩小的翼型部分。 由X，Y和Z距离给出的额定翼型在垂直于翼面表面的方向上处于±0.060英寸的包络内。
-
公开(公告)号：US20120121415A1
公开(公告)日：2012-05-17
申请号：US12948361
申请日：2010-11-17
IPC分类号： F01D5/08
CPC分类号： F01D9/02 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.
摘要翻译： 涡轮机包括壳体和布置在壳体内的至少一个涡轮叶片。 至少一个涡轮叶片包括可操作地连接到翼型部分的平台部分。 在平台部分形成冷却腔。 冷却腔包括第一壁，与第一壁相对布置的第二壁，连接第一壁和第二壁的第三壁和连接第一壁和第二壁并与第三壁相对定位的第四壁。 冲击冷却板延伸到冷却腔中并限定内腔部分和外腔部分。 所述冲击冷却板包括至少一个冲击冷却通道，所述至少一个冲击冷却通道被构造和设置成将冲击冷却流引导到所述冷却腔的所述第一，第二，第三和第四壁中的至少一个上。
-
公开(公告)号：US08851845B2
公开(公告)日：2014-10-07
申请号：US12948361
申请日：2010-11-17
CPC分类号： F01D9/02 , F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/201 , F05D2260/202
摘要： A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.
摘要翻译： 涡轮机包括壳体和布置在壳体内的至少一个涡轮叶片。 至少一个涡轮叶片包括可操作地连接到翼型部分的平台部分。 在平台部分形成冷却腔。 冷却腔包括第一壁，与第一壁相对布置的第二壁，连接第一壁和第二壁的第三壁和连接第一壁和第二壁并与第三壁相对定位的第四壁。 冲击冷却板延伸到冷却腔中并限定内腔部分和外腔部分。 所述冲击冷却板包括至少一个冲击冷却通道，所述至少一个冲击冷却通道被构造和设置成将冲击冷却流引导到所述冷却腔的所述第一，第二，第三和第四壁中的至少一个上。
-
公开(公告)号：US20120051924A1
公开(公告)日：2012-03-01
申请号：US12872901
申请日：2010-08-31
CPC分类号： F01D5/147 , F05D2230/61 , F05D2230/64 , Y10T29/49321
摘要： A blade assembly for a rotor includes an attachment section operably connectable to a rotor, and an airfoil section. At least one retainer extends in a substantially tangential direction at least partially through the airfoil section and the attachment section to secure the airfoil section to the attachment section. A method of assembling a rotor assembly includes inserting at least one retainer in a substantially tangential direction at least partially through an attachment section of a blade assembly and an airfoil section of the blade assembly, thereby securing the airfoil section to the attachment section. The blade assembly is then secured to a rotor.
摘要翻译： 用于转子的叶片组件包括可操作地连接到转子的附接部分和翼型部分。 至少一个保持器至少部分地穿过翼型部分和连接部分沿基本上切向的方向延伸，以将翼型部分固定到附接部分。 组装转子组件的方法包括至少部分地穿过叶片组件的附接部分和叶片组件的翼型部分沿基本上切向的方向插入至少一个保持器，从而将翼型部分固定到附接部分。 然后将叶片组件固定到转子上。
-
公开(公告)号：US07976280B2
公开(公告)日：2011-07-12
申请号：US11987163
申请日：2007-11-28
CPC分类号： F01D5/225 , F01D5/147 , F05D2250/70 , F05D2250/74 , F05D2260/94 , F05D2260/941 , Y02T50/671 , Y02T50/673
摘要： A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.
摘要翻译： 一种涡轮机桶，包括具有中空尖端护罩的桶形翼片，该空心尖端护罩具有基本上按照表I所示的X，Y和Z的笛卡尔坐标值的英寸的标称轮廓的中空芯，其中， 核心部分由分布在护罩的每个表面周围的点所组成的云定义，并且尖端护罩的完整中空部分可以通过在列出的点上限定光滑的片材表面而构成。
-
6.发明申请公开(公告)号：US20090304520A1
公开(公告)日：2009-12-10
申请号：US11447910
申请日：2006-06-07
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/225 , F05B2240/33 , F05D2240/81 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/22141 , Y02T50/671 , Y02T50/676
摘要： A serpentine cooling circuit is formed in a gas turbine blade to cool portions of the tip shroud, primarily the fillet between the airfoil and the tip shroud and the shroud edges.
摘要翻译： 在燃气轮机叶片中形成蛇形冷却回路，以冷却尖端罩的部分，主要是翼型件与尖端护罩之间的圆角和护罩边缘。
-
公开(公告)号：US20090142195A1
公开(公告)日：2009-06-04
申请号：US11987315
申请日：2007-11-29
CPC分类号： F01D5/3007 , F05D2250/74 , Y02T50/673
摘要： A turbine includes a turbine wheel having a plurality of buckets, each of the buckets including a bucket airfoil, a bucket dovetail to connect the bucket to a turbine wheel and a shank shape to connect the airfoil to the bucket dovetail, the shank having an uncoated nominal profile including a concave, pressure side, substantially in accordance with Cartesian values of X, Y and Z′ set forth in Table I wherein the Z′ values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by shank height in inches, and a convex, suction side, substantially in accordance with Cartesian values of X, Y and Z′ set forth in Table II wherein the Z′ values are non-dimensional values in a range from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by the shank height in inches. The X and Y are distances in inches which, when connected by smooth continuing arcs, define a shank profile section at each distance Z, the profile sections being joined smoothly with one another to form a complete shank shape.
摘要翻译： 涡轮机包括具有多个铲斗的涡轮机叶轮，每个铲斗包括铲斗翼型件，将铲斗连接到涡轮机叶轮的铲斗燕尾榫和将翼型件连接到铲斗燕尾榫的柄形状，柄部具有未涂覆的 标称轮廓包括基本上根据表I中列出的X，Y和Z'的笛卡尔值的凹形压力侧，其中Z'值是0至1范围内的可变换为Z距离（以英寸为单位）的无量纲值 通过将Z'值乘以柄高度（英寸）和基本上按照表II所示的X，Y和Z'的笛卡尔值的凸吸吸侧，其中Z'值是范围内的无量纲值 从0到1可以通过将Z'值乘以柄高度（英寸）来以英寸计算Z距离。 X和Y是以英寸为单位的距离，当通过平滑连续的圆弧连接时，在每个距离Z处限定一个柄型材部分，轮廓部分彼此平滑地连接以形成完整的柄形。
-
公开(公告)号：US06722851B1
公开(公告)日：2004-04-20
申请号：US10385438
申请日：2003-03-12
IPC分类号： F01D514
CPC分类号： F01D5/147 , F01D5/141 , F05D2250/20 , F05D2250/70 , F05D2260/202 , Y10S416/02
摘要： First stage turbine buckets have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the bucket in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.039 inches in directions normal to any internal core surface location.
摘要翻译： 第一级涡轮机叶片具有基本上根据表I所示的X，Y和Z的笛卡尔坐标值的内部芯轮廓，其中X和Y值以英寸为单位，Z值是从0到1可转换成Z距离的无量纲值 以英寸乘以Z值乘以桶的高度（英寸）。 X和Y值是当通过光滑连续弧连接时，在每个距离Z处限定内部芯轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的内部芯轮廓。 X，Y和Z距离可以是可扩展的，作为相同常数或数字的函数，以提供按比例放大或缩小的内核配置文件。 由X，Y和Z距离给出的标称内芯型材在垂直于任何内芯表面位置的方向上在±0.039英寸的包络内。
-
9.发明授权Locking spacer assembly for a circumferential entry airfoil attachment system 有权用于圆周入口机翼连接系统的锁定间隔件组件公开(公告)号：US08523529B2
公开(公告)日：2013-09-03
申请号：US12616320
申请日：2009-11-11
IPC分类号： F01D5/32
CPC分类号： F04D29/322 , F01D5/3038 , F01D5/32 , F05B2260/301 , F05D2260/30
摘要： A locking spacer assembly for insertion in a circumferential attachment slot includes a first end piece and a second end piece. The first and second end pieces each comprise an outer surface and an inner surface, the inner surfaces generally facing towards each other when the end pieces are inserted into the attachment slot. An actuator is movable between the inner surfaces and a spacer block is configured to be inserted between the inner surfaces. A fastener is configured to secure the spacer block to the actuator. The actuator is configured to engage the inner surfaces such that the end pieces move toward each other and lock the assembly within the attachment slot.
摘要翻译： 用于插入圆周附接槽中的锁定间隔件组件包括第一端件和第二端件。 第一和第二端片各自包括外表面和内表面，当端件插入附接槽中时，内表面大体上彼此面对。 致动器可在内表面之间移动，间隔块构造成插入在内表面之间。 紧固件被构造成将间隔块固定到致动器。 致动器构造成接合内表面，使得端件朝向彼此移动并将组件锁定在附接槽内。
-
公开(公告)号：US20120318448A1
公开(公告)日：2012-12-20
申请号：US13161549
申请日：2011-06-16
IPC分类号： B32B38/04
CPC分类号： C04B35/82 , B32B3/266 , B32B18/00 , C04B35/62868 , C04B2235/5212 , C04B2235/5248 , C04B2237/30 , C04B2237/32 , C04B2237/341 , C04B2237/348 , C04B2237/36 , C04B2237/363 , C04B2237/365 , C04B2237/368 , C04B2237/385 , C04B2237/40 , C04B2237/62 , C04B2237/68 , C04B2237/704 , Y10T156/1056
摘要： A method for manufacturing a composite includes perforating an outer ply to create perforations through the outer ply and inserting a filler material into the perforations. The method further includes laminating the outer ply to an inner ply.
摘要翻译： 制造复合材料的方法包括穿孔外层以通过外层产生穿孔并将填充材料插入穿孔中。 该方法还包括将外层层压到内层。
-
-
-
-
-
-
-
-
-
搜索结果
23 条记录 (耗时 0.023 秒)
