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91. 发明授权

US08961114B2 Integrated variable geometry flow restrictor and heat exchanger 有权
标题翻译：集成可变几何形状流量限制器和热交换器
公开(公告)号：US08961114B2
公开(公告)日：2015-02-24
申请号：US12951178
申请日：2010-11-22
申请人： Michael Anthony Ruthemeyer
发明人： Michael Anthony Ruthemeyer
IPC分类号： F01D25/12 , F01D5/14 , F02C3/13 , F02C7/08 , F02C7/14 , F02C7/18 , F02K1/06 , F02K1/08 , F02K1/12 , F02K3/075 , F28D11/04 , F28F1/02 , F28F13/08 , F01D5/18 , F01D17/16 , F02C7/143 , F02C9/18
CPC分类号： F01D25/12 , F01D5/146 , F01D5/18 , F01D17/162 , F01D17/165 , F02C3/13 , F02C7/08 , F02C7/14 , F02C7/143 , F02C7/185 , F02C9/18 , F02K1/06 , F02K1/08 , F02K1/1207 , F02K3/075 , F05D2260/56 , F28D11/04 , F28F1/02 , F28F13/08 , Y02T50/673 , Y02T50/676
摘要： One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.
摘要翻译：安装在管道中的一个或多个热交换器在其中具有热传递冷却通道，并且可变几何形状流量限制器与每个热交换器是一体的。在管道内可轴向平移的环形滑阀可操作以打开和关闭或改变热交换器与界定管道的内壳体和外壳之间的可变区域。热交换器可以围绕环形管周向分布并且包括径向或周向弯曲的传热管或叶片。

92. 发明申请

US20150044052A1 Geared Turbofan With Fan Blades Designed To Achieve Laminar Flow 审中-公开
标题翻译：具有风扇叶片的齿轮涡轮风设计用于实现层流
公开(公告)号：US20150044052A1
公开(公告)日：2015-02-12
申请号：US14079688
申请日：2013-11-14
申请人： United Technologies Corporation
发明人： Edwin M. Worth , Thomas G. Tillman , Frederick M. Schwarz
IPC分类号： F01D5/18 , F01D5/22
CPC分类号： F01D5/18 , F01D5/141 , F01D5/145 , F01D5/147 , F01D5/225 , F01D5/28 , F02C7/36 , F04D29/023 , F04D29/324 , F05D2220/36 , F05D2240/31 , F05D2250/181 , F05D2250/311 , F05D2250/321 , F05D2250/322 , F05D2250/62 , F05D2300/173 , F05D2300/174 , F05D2300/516 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： A fan blade comprises a main body having an airfoil extending between a leading edge and a trailing edge. The fan blade has at least one of a channel closed by a cover, and an end cap covering at least one of the leading and trailing edges. At least one of a cover and an end cap has a pair of opposed ends. A step is defined extending from at least one of a suction wall and a pressure wall of the airfoil, to an outer surface of the one of a cover and an end cap at one of the opposed ends, and the step being less than or equal to about 0.010 inch (0.0254 centimeter) in dimension.
摘要翻译：风扇叶片包括具有在前缘和后缘之间延伸的翼型件的主体。风扇叶片具有由盖封闭的通道和覆盖前缘和后缘中的至少一个的端盖中的至少一个。盖和端盖中的至少一个具有一对相对的端部。从机翼的吸力壁和压力壁中的至少一个到相对端中的一个的盖和端盖中的一个的外表面延伸的步骤被限定，该步骤小于或等于到约0.010英寸（0.0254厘米）的尺寸。

93. 发明授权

US08944141B2 Drill to flow mini core 有权
标题翻译：钻迷你核心
公开(公告)号：US08944141B2
公开(公告)日：2015-02-03
申请号：US12975404
申请日：2010-12-22
申请人： Tracy A. Propheter-Hinckley , Stephanie Santoro
发明人： Tracy A. Propheter-Hinckley , Stephanie Santoro
IPC分类号： B22C9/10 , B22C9/24 , F01D5/18 , F01D9/04
CPC分类号： F01D5/18 , B22C9/103 , B22C9/24 , B22D25/02 , F01D5/186 , F01D9/041 , F05D2250/185 , F05D2260/202 , F05D2260/204 , Y10T29/49337
摘要： A core for forming a cooling microcircuit has at least one row of metering/tripping features configured to form at least one row of protrusions in the cooling microcircuit, a plurality of teardrop features configured to form a plurality of fluid passageways in the cooling microcircuit, and a terminal edge. The plurality of teardrop features includes a central teardrop feature having a trailing edge which is spaced from the terminal edge and a first teardrop feature located on a first side of and spaced from the central teardrop feature. The first teardrop feature has a longitudinal axis and is non-symmetrical about the longitudinal axis. A process of using the core and a turbine engine component formed thereby are described.
摘要翻译：用于形成冷却微电路的芯具有配置成在冷却微电路中形成至少一排突起的至少一排计量/跳闸特征，多个泪滴特征，被配置为在冷却微电路中形成多个流体通道，以及终端边缘。多个泪滴特征包括中心泪滴特征，其具有与终端边缘间隔开的后缘和位于中心泪珠特征的第一侧并与中心泪滴特征间隔开的第一泪滴特征。第一泪滴特征具有纵轴并且关于纵向轴线是不对称的。描述了使用该芯体的方法和由此形成的涡轮发动机部件。

94. 发明授权

US08926289B2 Blade pocket design 有权
标题翻译：刀口袋设计
公开(公告)号：US08926289B2
公开(公告)日：2015-01-06
申请号：US13415005
申请日：2012-03-08
申请人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
发明人： Loc Quang Duong , Xiaolan Hu , Nagamany Thayalakhandan , Gao Yang
IPC分类号： F01D5/18
CPC分类号： F01D5/14 , F01D5/18
摘要： An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.
摘要翻译：翼型件包括其中具有凹穴凹部的叶片，以及设置在凹槽内的一个或多个特征。该一个或多个特征被配置为破坏袋凹部内的压力振荡。在另一个实施例中，公开了一种具有第一壁和第二壁的叶片。第一壁设置在叶片的吸力侧，第二壁设置在叶片的压力侧。第二壁在叶片的前缘连接到第一壁。第一壁和第二壁一起形成凹部凹部的一部分，并且凹部凹部相对于叶片的弧形线不对称地设置。

95. 发明申请

US20150003975A1 COOLED WALL 有权
标题翻译：冷却墙
公开(公告)号：US20150003975A1
公开(公告)日：2015-01-01
申请号：US14491040
申请日：2014-09-19
申请人： ALSTOM Technology Ltd
发明人： Sergey SHCHUKIN , Robert MARMILIC
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/18 , F01D5/187 , F01D25/12 , F05D2240/127 , F05D2260/2212 , F05D2260/22141
摘要： The disclosure pertains to a cooled wall for separating a hot gas flow path of a gas turbine from a cooling flow including at least one turbulator rib extending from the wall into the cooling flow, and having a height, a width for providing heat transfer enhancement for the cooled wall. The turbulator rib has filets at its root with a filet radius. In order to increase the heat transfer enhancement of the turbulator rib, the filet at the downstream side of turbulator rib is extending into the cooled wall with a penetration depth. Further, the disclosure relates to specific embodiments in which the cooled wall with turbulator ribs is configured as the sidewall of an airfoil, a combustor wall or a heat shield.
摘要翻译：本发明涉及一种用于将燃气涡轮机的热气体流路与冷却流分离的冷却壁，所述冷却流包括从壁延伸到冷却流中的至少一个湍流肋，并且具有高度，用于提供热传递增强的宽度冷却的墙壁。湍流肋在其根部具有锉刀半径。为了增加湍流肋的传热增强，在湍流肋的下游侧的file口延伸到具有穿透深度的冷却壁中。此外，本公开涉及其中具有湍流肋的冷却壁被构造为翼型，燃烧器壁或隔热罩的侧壁的具体实施例。

96. 发明申请

US20140349065A1 MODIFIED INTERFACE AROUND A HOLE 有权
标题翻译：孔改良界面
公开(公告)号：US20140349065A1
公开(公告)日：2014-11-27
申请号：US14356464
申请日：2012-09-14
申请人： Christian Amann , Thomas Beck , Bjorn Beckmann , Andreas Böttcher , Winfried Esser , Giuseppe Gaio , Rudolf Küperkoch , Eckart Schumann , Rostislav Teteruk
发明人： Christian Amann , Thomas Beck , Bjorn Beckmann , Andreas Böttcher , Winfried Esser , Giuseppe Gaio , Rudolf Küperkoch , Eckart Schumann , Rostislav Teteruk
IPC分类号： F01D5/18 , F01D5/28
CPC分类号： F01D5/186 , F01D5/18 , F01D5/28 , F01D5/288 , F05D2230/90 , F05D2260/22141 , Y02T50/676 , Y10T428/24273 , Y10T428/24322
摘要： A layer system including a substrate and a layer is provided. The layer system has a hole at least in the layer, and wherein at least one recess is present in a surface of the layer in a vicinity around the hole or directly adjoining a boundary line of the hole.
摘要翻译：提供了包括衬底和层的层系统。层系统至少在该层中具有孔，并且其中至少一个凹部存在于该孔周围的附近的表面中或者直接邻接该孔的边界线。

97. 发明授权

US08894367B2 Compound cooling flow turbulator for turbine component 有权
标题翻译：用于涡轮机部件的复合式冷却流动紊流器
公开(公告)号：US08894367B2
公开(公告)日：2014-11-25
申请号：US12884464
申请日：2010-09-17
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
摘要翻译：多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。可以在较大的湍流器（50）之间形成第一湍流器。第一个紊流器可以是交替的脊（46）和谷（48）。较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件质量

98. 发明授权

US08882448B2 Cooling system in a turbine airfoil assembly including zigzag cooling passages interconnected with radial passageways 有权
标题翻译：涡轮机翼组件中的冷却系统，包括与径向通道相互连接的曲折冷却通道
公开(公告)号：US08882448B2
公开(公告)日：2014-11-11
申请号：US14048074
申请日：2013-10-08
申请人： Ching-Pang Lee
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/186 , F01D5/187 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2260/202
摘要： An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, a plurality of cooling fluid passages, and a plurality of radial passageways. The outer wall has leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge. The radial passageways interconnect radially adjacent cooling fluid passages.
摘要翻译：燃气涡轮发动机中的翼型件包括外壁，冷却流体腔，多个冷却流体通道和多个径向通道。外壁具有前缘和后缘，压力和吸力侧以及径向内外端。冷却流体腔被限定在外壁中并且接收用于冷却外壁的冷却流体。冷却流体通道与冷却流体腔流体连通，并且包括交替成角度的部分，每个部分都具有径向分量和弦状分量。冷却流体通道从冷却流体腔朝向外壁的后缘延伸，并接收来自冷却流体腔的冷却流体，用于冷却靠近后缘的外壁。径向通道将径向相邻的冷却流体通道相互连接。

99. 发明申请

US20140322028A1 GAS TURBINE BLADE WITH TIP SECTIONS OFFSET TOWARDS THE PRESSURE SIDE AND WITH COOLING CHANNELS 有权
标题翻译：气体涡轮叶片带有提升部分偏移压力侧和冷却通道
公开(公告)号：US20140322028A1
公开(公告)日：2014-10-30
申请号：US14358851
申请日：2012-11-13
申请人： SNECMA
发明人： Regis Grohens , Erwan Daniel Botrel
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/141 , F01D5/18 , F01D5/187 , F01D5/20
摘要： A hollow blade including an airfoil extending along a longitudinal direction, a root, a tip, an internal cooling passage, and an open cavity defined by an end wall and a rim, together with cooling channels connecting the internal cooling passage to a pressure side. The cooling channels slope relative to the pressure side. A stack of airfoil sections of the blade at a level of the rim of the tip of the blade are offset towards the pressure side. The pressure side wall of the airfoil includes a projecting portion and cooling channels arranged in the projecting portion to open out into a terminal face of the projecting portion.
摘要翻译：包括沿纵向方向延伸的翼型件的中空叶片，根部，尖端，内部冷却通道和由端壁和边缘限定的开口腔以及将内部冷却通道连接到压力侧的冷却通道。冷却通道相对于压力侧倾斜。在刀片的尖端的边缘的水平处的叶片的翼型部分的堆叠朝向压力侧偏移。翼型件的压力侧壁包括突出部分和布置在突出部分中的冷却通道，以打开到突出部分的端面中。

100. 发明申请

US20140294598A1 TURBINE BLADE 审中-公开
标题翻译：涡轮叶片
公开(公告)号：US20140294598A1
公开(公告)日：2014-10-02
申请号：US14301577
申请日：2014-06-11
申请人： IHI Corporation
发明人： Kozo NITA , Yoji OKITA , Chiyuki NAKAMATA , Kazuo YONEKURA , Seiji KUBO , Osamu WATANABE
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/186 , F01D9/065 , F05D2240/81 , F05D2250/21 , F05D2250/23 , F05D2260/202 , F05D2260/2212 , F23R2900/03042 , F23R2900/03043 , F23R2900/03045
摘要： The cooling effectiveness of a turbine blade that a gas turbine engine or the like is provided with is further increased by providing a convex portion that is arranged in the inner portion of a cooling air hole and that is provided projecting out from the inner wall surface of the cooling air hole.
摘要翻译：提供燃气涡轮发动机等的涡轮叶片的冷却效果通过设置布置在冷却空气孔的内部的凸部而进一步增大，并且从凸缘部的内壁面突出设置冷却空气孔。

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