公开(公告)号：US06820335B2

公开(公告)日：2004-11-23

申请号：US09981100

申请日：2001-10-16

申请人： Henry R. Schwartz

发明人： Henry R. Schwartz

IPC分类号： B21D5378

CPC分类号： C09J5/02 ,  B23P15/04 ,  C09J2400/166 ,  F01D25/002 ,  F05D2230/23 ,  F05D2230/90 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49885 ,  Y10T29/49995

摘要： A method for bonding metal components includes the steps of providing metal components to be bonded together at contacting surfaces, the contacting surfaces having an oxide layer; washing the components with an alkali solution to provide alkali-washed components; washing the alkali-washed components with water to provide water-washed components; and bonding the components together at the surfaces.

摘要翻译： 接合金属部件的方法包括以下步骤：在接触表面处提供要结合在一起的金属部件，所述接触表面具有氧化物层; 用碱溶液洗涤组分以提供碱洗组分; 用水洗涤碱洗组分以提供水洗组分; 并将部件在表面粘合在一起。

公开(公告)号：US06467167B2

公开(公告)日：2002-10-22

申请号：US09759529

申请日：2001-01-16

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： B21D5378

CPC分类号： F01D5/189 ,  B23P15/04 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339

摘要： A hollow liner (14) for fitting in the interior of a aerofoil vane (10) is crimped prior to fitting within the vane (10). Following fitting, the liner (14) is expanded so as to fit snugly within the vane (10). The technique permits the insertion of liners (14) into vanes (10) that are so configured as to preclude the insertion of conventional liners.

摘要翻译： 用于安装在翼型叶片（10）的内部的空心衬套（14）在装配在叶片（10）之前被卷曲。 在安装之后，衬套（14）膨胀以便紧密地配合在叶片（10）内。 这种技术允许将衬垫（14）插入叶片（10），叶片（10）被配置成阻止常规衬垫的插入。

公开(公告)号：US06354797B1

公开(公告)日：2002-03-12

申请号：US09626980

申请日：2000-07-27

申请人： John Peter Heyward ,  Gregory Alan White ,  Richard Hartley Pugh

发明人： John Peter Heyward ,  Gregory Alan White ,  Richard Hartley Pugh

IPC分类号： B21D5378

CPC分类号： F01D9/04 ,  B23K1/0018 ,  B23K1/20 ,  B23K2101/001 ,  Y10T29/49341

摘要： A turbine nozzle includes a plurality of airfoils and integral hubs brazed into corresponding seats of outer and inner bands. The hubs have brazeless fillets blending the bands to the airfoils.

摘要翻译： 涡轮喷嘴包括钎焊到外带和内带的相应座中的多个翼型件和一体式轮毂。 这些枢纽有无边的鱼片将乐队混合到翼型上。

公开(公告)号：US06802122B2

公开(公告)日：2004-10-12

申请号：US10141819

申请日：2002-05-10

申请人： Richard G Milburn

发明人： Richard G Milburn

IPC分类号： B21D5378

CPC分类号： B23P15/04 ,  B23K9/044 ,  B23K20/02 ,  B23K2101/001 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49805

摘要： A gas turbine engine (10) fan outlet guide vane (34) is manufactured by diffusion bonding titanium alloy sheet metal workpieces (52, 54) together to form an in integral structure (66). A titanium alloy is weld deposited at predetermined positions (70, 72) and in a predetermined shape to build up bosses (42, 44) at the radially outer end (40) of the hollow integral structure (68). The integral structure (66) is inflated at high temperature to form a hollow integral structure (68) of predetermined aerofoil shape. Apertures (46, 48) are drilled through the bosses (42, 44) to enable the radially outer end (40) of the fan outlet guide vane (34) to be attached to a fan casing (32) of the gas turbine engine (10).

摘要翻译： 燃气涡轮发动机（10）风扇出口导叶（34）通过将钛合金板金属工件（52,54）扩散接合在一起以形成一体结构（66）而制造。 钛合金在预定位置（70,72）处以预定形状焊接沉积，以在中空整体结构（68）的径向外端（40）处形成凸起（42,44）。 整体结构（66）在高温下充气以形成具有预定机翼形状的中空整体结构（68）。 通过凸台（42,44）钻出孔（46,48），以使风扇出口导叶（34）的径向外端（40）能够附接到燃气涡轮发动机的风扇壳体（32） 10）。

公开(公告)号：US06279228B1

公开(公告)日：2001-08-28

申请号：US09634986

申请日：2000-08-08

申请人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

发明人： Takashi Kobayashi ,  Michihiko Banno ,  Kazuaki Amaoka

IPC分类号： B21D5378

CPC分类号： B64D15/04 ,  B21D26/055 ,  B21D26/059 ,  B21D53/92 ,  B64C3/28 ,  B64F5/10 ,  Y10T29/49336 ,  Y10T29/49339 ,  Y10T29/49622

摘要： A leading edge structure of an aircraft airfoil comprises an outer skin, a front wall extended in the spanwise direction of the leading edge structure in a front section of the space defined by the outer skin so as to form an anti-icing duct together with a front part of the outer skin, and a plurality of ribs disposed in the space defined by the outer skin so as to form hot air passages. A laminar structure is formed by superposing upper and lower sheets of a superplastic titanium alloy, inserting a pair of core sheets of a superplastic titanium alloy between the upper and the lower sheet, and forming release agent layers in predetermined regions between the sheets. A structure having at least the outer skin, the front wall and ribs is formed by joining together parts of the superposed sheets corresponding to regions not coated with the release agent layers by diffusion bonding or welding, heating the laminar structure in a forming mold, supplying a superplastic forming gas into spaces between parts of the superposed sheets corresponding to regions coated with the release agent layers to subject the same parts of the superposed sheets to superplastic deformation and to press the upper sheet and the lower sheet against the forming surface of the forming mold.

摘要翻译： 飞机机翼的前缘结构包括外皮，在外皮的空间前部的前缘结构的翼展方向上延伸的前壁，以便与外皮形成防冰导管， 外皮的前部，以及设置在由外皮限定的空间中的多个肋，以便形成热空气通道。 层叠结构通过将超塑性钛合金的上下板叠合，在上下板之间插入一对超塑性钛合金芯片，并在片材之间的预定区域中形成剥离剂层而形成。 至少具有外皮，前壁和肋骨的结构通过扩散粘合或焊接将对应于未涂覆有脱模剂层的区域的重叠片材的部分接合在一起而形成，在成型模具中加热层状结构， 将超塑性成形气体输送到叠加片的部分之间的空间中，所述空间对应于涂覆有脱模剂层的区域，以使叠加的片材的相同部分经受超塑性变形，并将上部片材和下部片材压靠在成形 模子。

公开(公告)号：US06470544B1

公开(公告)日：2002-10-29

申请号：US09460562

申请日：1999-12-14

申请人： Patrick Boschet ,  Daniel Brunner ,  André Amari

发明人： Patrick Boschet ,  Daniel Brunner ,  André Amari

IPC分类号： B21D5378

CPC分类号： B23P19/04 ,  B23P6/00 ,  Y10T29/37 ,  Y10T29/49318 ,  Y10T29/49332 ,  Y10T29/49757 ,  Y10T29/4978 ,  Y10T29/49821 ,  Y10T29/49822 ,  Y10T29/53439 ,  Y10T156/1911 ,  Y10T156/1961

摘要： In order to remove a plate made from a material that can be heated by electromagnetic induction and retained on a supporting member by a heat-fusible adhesive, an inductor is displaced facing at least one strip of the plate in order to heat the strip by induction and heat the adhesive by conduction until the adhesive softens, and a tearing tool is driven so as to tear out the heated strip by hot-peeling. The inductor and the tearing tool are displaced jointly relative to the plate and the supporting member by means of a mobile frame, which is displaced on a stationary frame on which the supporting member and the plate are fixed.

摘要翻译： 为了除去由可通过电磁感应加热并由热熔粘合剂保持在支撑构件上的材料制成的板，电感器朝向板的至少一个带移位，以便通过感应加热带 并通过传导加热粘合剂，直到粘合剂软化，并且驱动撕裂工具，以便通过热剥离撕开加热的条带。 电感器和撕裂工具通过移动框架相对于板和支撑构件共同位移，移动框架在支撑构件和板被固定的固定框架上移位。

公开(公告)号：US06178633B2

公开(公告)日：2001-01-30

申请号：US09399184

申请日：1999-09-20

申请人： Fujio Yamane

发明人： Fujio Yamane

IPC分类号： B21D5378

CPC分类号： F01C21/0809 ,  Y10T29/49245 ,  Y10T29/49336

摘要： The vane 1 is substantially in a flat rectangular parallelepiped shape having (a) two wide side surfaces 1c, 1c′ opposing in the thickness direction and being slidable in each guide groove 12 of a rotor 11 of an actuator, (b) two narrow side surfaces 1d, 1d′ opposing in the width direction, (c) an as-cold-worked top surface 1a having an arcuately projecting cross section in a plane perpendicular to the width direction and being in slidable contact with a cam surface 14 of the actuator 13 for sealing, and (d) a bottom end surface 1e opposing the top surface 1a, both ends of said top surface 1a in the width direction being bulging toward the cam surface 14.

摘要翻译： 叶片1基本上是平坦的长方体形状，其具有（a）在厚度方向上相对的两个宽的侧表面1c，1c'，并且可在致动器的转子11的每个引导槽12中滑动，（b）两个窄边 在宽度方向上相对的表面1d，1d'，（c）在垂直于宽度方向的平面中具有弓形突出横截面并与致动器的凸轮表面14滑动接触的冷冷加工顶表面1a 13，用于密封，（d）与顶面1a相对的底面1e，上表面1a的宽度方向的两端向凸轮面14突出。

公开(公告)号：US06763560B2

公开(公告)日：2004-07-20

申请号：US10310849

申请日：2002-12-06

申请人： Dwight McGee ,  Mike Tessier ,  Gary Senecal ,  Kiernan Francis Ryan

发明人： Dwight McGee ,  Mike Tessier ,  Gary Senecal ,  Kiernan Francis Ryan

IPC分类号： B21D5378

CPC分类号： F01D5/225 ,  F01D25/285 ,  F05D2230/60 ,  F05D2230/68 ,  Y10T29/37 ,  Y10T29/49318 ,  Y10T29/49321 ,  Y10T29/53683 ,  Y10T29/537 ,  Y10T29/53896 ,  Y10T29/53909

摘要： A bucket spreading tool is disclosed for separating covers of adjacent turbine buckets, the tool includes: an arm for extending a head of the tool between adjacent turbine wheels and for positioning the head between the adjacent buckets of a wheel, wherein the head includes an attachment to an end of the arm and a forward portion having a front side surface shaped to engage a first bucket of said adjacent buckets, and a rear side surface shaped to engage a second bucket of said adjacent buckets.

摘要翻译： 公开了一种用于分离相邻涡轮机叶片的盖的铲斗伸展工具，该工具包括：用于将工具的头部延伸在相邻的涡轮机叶轮之间并用于将头部定位在轮的相邻铲斗之间的臂，其中头部包括附件 到所述臂的一端和具有成形为接合所述相邻铲斗的第一铲斗的前侧表面的前部，以及成形为接合所述相邻铲斗的第二铲斗的后侧表面。

公开(公告)号：US06339879B1

公开(公告)日：2002-01-22

申请号：US09684987

申请日：2000-08-29

申请人： Gary Eugene Wheat ,  Terri Kay Brown ,  Thomas Phillip Schumacher

发明人： Gary Eugene Wheat ,  Terri Kay Brown ,  Thomas Phillip Schumacher

IPC分类号： B21D5378

CPC分类号： B21D53/78 ,  B23P2700/06 ,  C23C10/02 ,  Y10T29/49336 ,  Y10T29/49341 ,  Y10T29/49343

摘要： A method for accurately sizing and forming the cooling holes of an air-cooled gas turbine engine component on which a protective diffusion coating will be deposited. The method generally entails drilling a hole in a surface region of a substrate, and then measuring the thickness of any recast surface region surrounding the hole and created as a result of a portion of the surface region having melted and then resolidified. The thickness of the additive layer of the diffusion coating that will deposit on a corresponding recast surface region of the component is then predicted based on an inverse relationship determined to exist with the thickness of the recast surface region formed during drilling of the cooling hole. An appropriately-oversized hole can then be formed in the component so that, after depositing the diffusion coating on the component, the additive layer grows sufficiently within the hole to yield a cooling hole approximately having the required final diameter.

摘要翻译： 一种用于精确地确定和形成将要沉积保护性扩散涂层的空气冷却燃气涡轮发动机部件的冷却孔的方法。 该方法通常需要在基板的表面区域中钻孔，然后测量由孔的周围的任何重铸表面区域的厚度，并且由于表面区域的一部分已经熔化然后重新固化而产生。 然后基于与冷却孔的钻孔期间形成的重铸表面区域的厚度确定的反比关系来预测将沉积在部件的相应重铸表面区域上的扩散涂层的添加层的厚度。 然后可以在部件中形成适当大小的孔，使得在将扩散涂层沉积在部件上之后，添加剂层在孔内充分生长以产生大致具有所需最终直径的冷却孔。