公开(公告)号：US6103993A

公开(公告)日：2000-08-15

申请号：US337858

申请日：1999-06-21

申请人： Jurgen Wortmann

发明人： Jurgen Wortmann

IPC分类号： B22D27/04 ,  B23K26/38 ,  B23P15/02 ,  F01D5/18 ,  F01D5/28 ,  B23K26/00

CPC分类号： F01D5/28 ,  B22D27/045 ,  B23K26/382 ,  B23K26/389 ,  B23K26/40 ,  B23P15/02 ,  F01D5/186 ,  B23K2203/50

摘要： A hollow structural part having an internal hollow space, preferably a blade for a turbodrive, is made of a metal alloy with a columnar structure solidified in an oriented manner with longitudinally extending grain boundaries. A series of holes are laser drilled in the blade to connect the outer surface of the blade with the hollow space. The blade is formed with a single crystal column in the region where the series of holes are formed so that the holes are away from the grain boundaries. Such structural parts are preferably used as the blade of a rotor and the laser drilled holes serve for supply of cooling air to the leading edge or pressure region of the blade or for influencing the position of the boundary layer on the suction side of the blade, or the laser-drilled holes are shaped as outflow openings for air to intensify a cooling film for increasing the blade efficiency.

摘要翻译： 具有内部中空空间，优选用于涡轮驱动的叶片的中空结构部件由具有以纵向延伸的晶界定向的柱状结构的金属合金制成。 在叶片中激光钻一系列孔，以将叶片的外表面与中空空间连接。 叶片在形成有一系列孔的区域中由单晶柱形成，使得孔远离晶界。 这种结构部件优选用作转子的叶片，并且激光钻孔用于向叶片的前缘或压力区域供应冷却空气或用于影响叶片的吸入侧上的边界层的位置， 或者激光钻孔形成为用于空气的流出开口，以增强冷却膜以提高叶片效率。

公开(公告)号：US5700743A

公开(公告)日：1997-12-23

申请号：US814446

申请日：1997-03-10

申请人： Franz Puchinger ,  Axel Rossman ,  Siegfried Sikorski ,  Gerhard Wydra

发明人： Franz Puchinger ,  Axel Rossman ,  Siegfried Sikorski ,  Gerhard Wydra

IPC分类号： B29C70/08 ,  B32B18/00 ,  B32B33/00 ,  B64C11/20 ,  B64D45/02 ,  C04B41/52 ,  C04B41/89 ,  F01D5/28 ,  B32B5/16

CPC分类号： C04B41/009 ,  B29C70/088 ,  B32B18/00 ,  B32B33/00 ,  B64C11/205 ,  B64D45/02 ,  C04B41/52 ,  C04B41/89 ,  F01D5/288 ,  B29K2105/0023 ,  B29K2995/0005 ,  B29K2995/0087 ,  C04B2111/2038 ,  C04B2237/385 ,  Y02T50/67 ,  Y02T50/672 ,  Y10T428/266 ,  Y10T428/269 ,  Y10T442/3504 ,  Y10T442/3813 ,  Y10T442/3846 ,  Y10T442/699

摘要： A structural component which consists of a fiber-reinforced, composite material is provided with a protective coating against erosion. The protective coating includes an adhesion-promoting, intermediate layer on the component, an electrically insulating baked, inorganic lacquer layer for protection against erosion and an electrically conducting covering layer, for protection against lightning strikes. The covering layer consists of a baked and compressed inorganic lacquer and the lacquer of the lacquer layer and of the covering layer is baked on the component below the temperature which causes damage to the structural component or below the softening or decomposition temperature of the component. The protective layer is advantageously used for the external components of propulsion units, such as housings, nose cones or fan blades.

摘要翻译： 由纤维增强的复合材料组成的结构部件具有防止侵蚀的保护层。 保护涂层包括部件上的粘附促进中间层，用于防止侵蚀的电绝缘烘烤的无机漆层和用于防止雷击的导电覆盖层。 覆盖层由烘烤和压缩的无机漆组成，漆层和覆盖层的漆在组件上烘烤，低于导致结构组分损坏或低于组分的软化或分解温度的温度。 保护层有利地用于推进单元的外部部件，例如外壳，鼻锥或风扇叶片。

公开(公告)号：US5403629A

公开(公告)日：1995-04-04

申请号：US60419

申请日：1993-05-11

申请人： Wolfgang Eichmann ,  Horst Pillhofer ,  Martin Thoma ,  Peter Adam

发明人： Wolfgang Eichmann ,  Horst Pillhofer ,  Martin Thoma ,  Peter Adam

IPC分类号： C23C10/02 ,  C23C14/16 ,  B05D3/06 ,  C23C14/00

CPC分类号： C23C14/165 ,  C23C10/02 ,  Y02T50/67

摘要： A process for vapor depositing a metallic interlayer on the surface of a metal component, for example, by sputtering and thereafter depositing an aluminum diffusion coating on the interlayer. The metallic interlayer is vapor deposited on the surface of the component in a noble gas atmosphere, more than one-half of which, in per cent by weight, is composed of noble gases which are heavier than argon. Advantageously, the noble gases can be krypton or xenon. The process can be used with particular advantage for applying protective aluminum diffusion coatings on turbine blades.

摘要翻译： 一种用于在金属部件的表面上气相沉积金属中间层的方法，例如通过溅射，然后在中间层上沉积铝扩散涂层。 金属中间层在惰性气体气氛中气相沉积在组分的表面上，其中一半以上重量百分比由比氩重的惰性气体组成。 有利地，惰性气体可以是氪或氙。 该方法可以特别有利于在涡轮叶片上施加保护性铝扩散涂层。

公开(公告)号：US5318110A

公开(公告)日：1994-06-07

申请号：US981132

申请日：1992-11-24

申请人： William Wei

发明人： William Wei

IPC分类号： F28D7/08 ,  F28F9/013 ,  F28F9/26 ,  F28F9/22

CPC分类号： F28F9/26 ,  F28D7/08 ,  F28F9/013 ,  F28F2265/26

摘要： Spacer supports are connected to a matrix of heat exchange tubes of a heat exchanger to maintain the heat exchange tubes in spaced relation and resist overheating by hot fluid flowing around the tubes and the spacer supports. The spacer supports are in the form of hollow tubular bodies in which the heat exchange tubes are supported in spaced relation. The heat exchange tubes communicate with the interior of the hollow bodies so that flow of a heatable fluid in the heat exchange tubes is conveyed through the hollow body to wet the interior thereof and cool the same.

摘要翻译： 隔板支撑件连接到热交换器的热交换管的矩阵，以使热交换管保持间隔的关系，并通过围绕管和间隔件支撑件流动的热流体抵抗过热。 间隔件支撑件是中空管状体的形式，其中热交换管以间隔的关系支撑。 热交换管与中空体的内部连通，使得热交换管中的可加热流体的流动通过中空体输送以润湿其内部并将其冷却。

公开(公告)号：US5274999A

公开(公告)日：1994-01-04

申请号：US907129

申请日：1992-07-01

申请人： Alois Rohra ,  Helmut A. Geidel

发明人： Alois Rohra ,  Helmut A. Geidel

IPC分类号： F02C3/067 ,  F02K3/06 ,  F02K3/072 ,  F02K3/02

CPC分类号： F02C3/067 ,  F02K3/06 ,  F02K3/072

摘要： A turbofan engine includes two oppositely rotating fan rotors which are arranged upstream of the core engine, and has a booster with two contra-rotating coaxial rotors. The radially exterior booster rotor is arranged between the rearward fan rotor and the low-pressure turbine in a torque-transmitting manner. The gearless construction permits an almost uniform loading of the low-pressure shafts.

摘要翻译： 涡轮风扇发动机包括两个相对旋转的风扇转子，其布置在核心发动机的上游，并具有带有两个反转同轴转子的增压器。 径向外部的增压转子以扭矩传递方式布置在后风扇转子和低压涡轮机之间。 无齿轮构造允许低压轴几乎均匀地装载。

公开(公告)号：US5226598A

公开(公告)日：1993-07-13

申请号：US881342

申请日：1992-05-11

申请人： Bernhard Woehrl

发明人： Bernhard Woehrl

IPC分类号： F02K1/82 ,  F02K9/97

CPC分类号： F02K9/972 ,  F02K1/822 ,  Y10T29/49346

摘要： A nozzle wall for two-dimensional (2D) hot gas nozzles of rocket or jet engines has a multilayer structure, in which a thermally conductive layer is flexibly connected to a support structure and a sliding layer is arranged between them to permit parallel movement of the thermally conductive layer. Also, a manufacturing method for the nozzle wall allows successive operations to be automatic to allow quality control inspections between these operations.

摘要翻译： 用于火箭或喷气发动机的二维（2D）热气喷嘴的喷嘴壁具有多层结构，其中导热层柔性地连接到支撑结构，并且滑动层布置在它们之间，以允许平行移动 导热层。 此外，喷嘴壁的制造方法允许连续的操作是自动的，以允许这些操作之间的质量控制检查。

公开(公告)号：US5215434A

公开(公告)日：1993-06-01

申请号：US825919

申请日：1992-01-27

申请人： Christian Greune ,  Helmut Gross ,  Georg Zotz

发明人： Christian Greune ,  Helmut Gross ,  Georg Zotz

IPC分类号： F01D17/16 ,  F02C9/22

CPC分类号： F01D17/162

摘要： Apparatus for the support and adjustment of stator blades of a gas turbine, in which an adjusting ring is connected to the stator blades by adjustment levers disposed outside the turbine housing. The adjusting ring is supported for rotation in the circumferential direction on a support ring, which has elastic resilience in the radial direction, the support ring being suspended on and centered in a movable manner on radial pins fixed in an outer housing of the turbine. The connection of the adjusting ring and the support ring is achieved by a ball-bearing which is pre-stressed. When the adjusting ring is displaced circumferentially, the stator blades are pivoted around suspension shafts by levers fixed to the shafts and connected to the adjusting ring for universal pivotal movement.

摘要翻译： 用于支撑和调节燃气轮机的定子叶片的装置，其中调节环通过设置在涡轮壳体外部的调节杆连接到定子叶片。 调节环支撑在圆周方向上在支撑环上旋转，支撑环在径向方向上具有弹性回弹力，支撑环悬挂在固定在涡轮机外壳中的径向销上并以可移动方式居中。 调节环和支撑环的连接通过预应力的滚珠轴承实现。 当调节环沿圆周方向移动时，定子叶片通过固定在轴上并连接到调节环的杠杆绕悬挂轴枢转，用于通用的枢转运动。

公开(公告)号：US5073459A

公开(公告)日：1991-12-17

申请号：US469781

申请日：1990-01-24

申请人： Wilfried Smarsly ,  Wolfgang Track

发明人： Wilfried Smarsly ,  Wolfgang Track

IPC分类号： B22F3/11 ,  C22C1/04 ,  F01D5/28

CPC分类号： C22C1/0433 ,  B22F3/1112 ,  C22C1/0491 ,  F01D5/28 ,  B22F2999/00 ,  Y02T50/671 ,  Y10T428/12042 ,  Y10T428/2982

摘要： A sintered metallic light-weight structural material consists of spherical voids and lattice-type webs of intermetallic compounds. Owing to its weight-specific strength, which is superior to that of conventional super-alloys, this material is suited especially for application in aircraft and turbine engine construction.

摘要翻译： 烧结的金属轻质结构材料由球形空隙和晶格型的金属间化合物组成。 由于其重量比强度优于常规超合金，因此该材料特别适用于飞机和涡轮发动机的施工。

公开(公告)号：US5027604A

公开(公告)日：1991-07-02

申请号：US293574

申请日：1989-01-03

申请人： Wolfgang Krueger

发明人： Wolfgang Krueger

IPC分类号： F01D5/18 ,  F01D5/28 ,  F01D11/24 ,  F01D21/04 ,  F23R3/00 ,  F23R3/04 ,  F23R3/06 ,  F23R3/42

CPC分类号： F01D11/24 ,  F01D21/045 ,  F01D5/187 ,  F01D5/28 ,  F23R3/002 ,  F23R3/007 ,  F05B2260/3011 ,  F05D2260/201 ,  F23R2900/03044 ,  Y02T50/676

摘要： A hot gas overheat protection device is provided for gas turbine engines and the like. An outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall. A thin metal skin is provided between the metal wall and the wall elements defining intermediate spaces communicating with cooling air ports in the metal wall. The thin metal skin has a melting point equal to or lower than that of the metal wall so as to provide for fusion or rupture of the thin metal skin in the event the insulating wall elements are locally ruptured, whereby the cooling air is provided through the cooling air ports in a direction against the flow of hot gases to thereby mitigate the effects of the rupture and protect the metal wall.

摘要翻译： 为燃气轮机发动机等提供热气体过热保护装置。 通过设置与金属壁间隔开的耐高温衬里壁元件，具有从外部通过冷却孔供应的具有冷却空气的外部金属壁被阻止热气流。 在金属壁和壁元件之间提供薄金属表层，其限定与金属壁中的冷却空气端口连通的中间空间。 薄金属皮具的熔点等于或低于金属壁的熔点，以便在绝缘壁元件局部破裂的情况下提供薄金属表皮的熔化或破裂，从而通过 冷却空气端口沿着热气流的方向，从而减轻破裂的影响并保护金属壁。

公开(公告)号：US5026252A

公开(公告)日：1991-06-25

申请号：US396354

申请日：1989-08-21

申请人： Herbert Hoffelner

发明人： Herbert Hoffelner

IPC分类号： F16J15/3288 ,  F16J15/44

CPC分类号： F16J15/3288 ,  F16J15/441 ,  F05B2220/302

摘要： A sealing device is provided, specifically between engine spaces which fluidically are acted upon by a different pressure, particularly for turbo-engines, such as gas turbo-engines. The sealing device includes at least one brush sealing device non-rotatably anchored at the stator side, the free bristle ends of this brush sealing device being guided in the direction toward an engine rotor. In this case, the brush sealing device is to be constructed as a radial sliding ring sealing device. The free ends of the bristles, while forming a secondary sealing, are guided in a circumferential groove of a sliding ring which is separated at least at one circumferential point, and which, on the side facing away from the bristles, forms a self-centering primary sealing at the engine rotor.

摘要翻译： 特别是提供了一种密封装置，特别是在流体上被不同压力作用的发动机空间之间，特别是涡轮发动机，例如燃气涡轮发动机。 密封装置包括至少一个不可旋转地锚定在定子侧的刷子密封装置，该刷子密封装置的自由刷毛端部朝向发动机转子的方向被引导。 在这种情况下，电刷密封装置将被构造为径向滑环密封装置。 刷毛的自由端在形成二次密封的同时被引导至至少在一个圆周点分开的滑动环的圆周槽中，并且在背离刷毛的一侧形成自定心 发动机转子主要密封。