公开(公告)号：US20180073120A1

公开(公告)日：2018-03-15

申请号：US15685642

申请日：2017-08-24

申请人： ROLLS-ROYCE plc

发明人： John H BOSWELL

IPC分类号： C22F1/10 ,  B24C1/10

CPC分类号： C22F1/10 ,  B22D27/045 ,  B24C1/08 ,  B24C1/10 ,  C21D7/06 ,  F01D5/286 ,  F05D2230/10 ,  F05D2230/211 ,  F05D2230/26 ,  F05D2230/42 ,  F05D2250/621 ,  F05D2250/63

摘要： A method of manufacturing a component from a nickel-based superalloy comprises the steps of: providing a vacuum induction casting furnace; positioning a component mould onto a chill plate within the furnace; casting a component blank; peening the surface of the component blank; applying a surface modification technique to the surface of the component blank; solution heat treating the component blank at or above the γ′-solvus temperature for the superalloy; and precipitation heat treating the component blank.

公开(公告)号：US20170312869A1

公开(公告)日：2017-11-02

申请号：US15652871

申请日：2017-07-18

申请人： Dynamic Metals, LLC

发明人： Bill Buitenhuis ,  Jack Opielka

IPC分类号： B23P15/00 ,  B21F37/00 ,  B21D5/08 ,  B21D53/20

CPC分类号： B23P15/00 ,  B21D5/08 ,  B21D53/20 ,  B21F37/00 ,  F01D11/005 ,  F05D2220/32 ,  F05D2230/26 ,  F05D2240/55 ,  F05D2250/73 ,  F05D2250/75 ,  F16J15/0887

摘要： A process of forming a turbine engine seal includes the steps of: providing a flat strip of material; roll forming the flat strip of material forming an asymmetric profile in the flat strip of material; coiling the formed asymmetric profile into an overlapping ring shape; cutting the circular shape to a predetermined length; and joining ends of the predetermined length forming the seal. The seal includes at least two peaks that are formed on opposing sides of a gap. The at least two peaks contact opposing sides of a U shaped profile at a zero radius. The asymmetric profile includes a circular shape and the ends are joined.

公开(公告)号：US09011011B2

公开(公告)日：2015-04-21

申请号：US13041898

申请日：2011-03-07

申请人： Max Fiedler

发明人： Max Fiedler

IPC分类号： F16C35/02 ,  F01D25/14 ,  F01D25/16

CPC分类号： F01D25/14 ,  F01D25/162 ,  F05D2220/40 ,  F05D2230/24 ,  F05D2230/25 ,  F05D2230/26 ,  F05D2230/50 ,  F05D2260/20 ,  Y10T29/49826

摘要： A bearing housing cover for a bearing housing of a charging device is presented. The housing cover is formed of metal by a mechanisms of at least one of internal high-pressure forming (IHU), deep-drawing, forging and roller burnishing.

摘要翻译： 提出了一种用于充电装置的轴承座的轴承座盖。 壳体盖通过内部高压成形（IHU），深冲压，锻造和滚筒抛光中的至少一种的机构由金属形成。

公开(公告)号：US20140367921A1

公开(公告)日：2014-12-18

申请号：US14303231

申请日：2014-06-12

申请人： Karl-Heinz KONIGS ,  Gerome SONOIS ,  Philippe MARTIN

发明人： Karl-Heinz KONIGS ,  Gerome SONOIS ,  Philippe MARTIN

IPC分类号： F01D11/12 ,  B32B38/00 ,  B32B37/18

CPC分类号： F01D11/125 ,  B29C70/342 ,  B29C70/86 ,  B29L2031/7504 ,  B32B37/18 ,  B32B38/00 ,  B32B2038/0076 ,  B32B2307/50 ,  F01D11/122 ,  F01D11/127 ,  F01D25/24 ,  F05D2230/21 ,  F05D2230/26 ,  F05D2230/50 ,  F05D2240/11 ,  F05D2300/44 ,  F05D2300/6012 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/672 ,  Y10T156/1002

摘要： A segment of an abradable ring seal for a turbomachine, includes: a reinforcing support; a composite fabric including fibres impregnated with polymerised resin, and a track of abradable material. The composite fabric is interposed between the reinforcing support 71 and the track of abradable material and is bonded to the reinforcing support, on the one side, and to the track of abradable material, on the other side. The segment of an abradable ring seal has a resistance to tearing in a direction perpendicular to the interface between the track of abradable material and the composite fabric, on the one hand, and between the composite fabric and the reinforcing support, on the other hand, greater than 5.106 newtons per square meter. A process for the manufacture of such a segment is also described.

摘要翻译： 用于涡轮机的可磨损环形密封件的一部分包括：加强支撑件; 包括浸渍有聚合树脂的纤维的复合织物和可磨损材料的轨道。 复合织物插入在加强支撑件71和可磨损材料的轨道之间，并且在另一侧上结合到一侧的加强支撑件和可磨损材料的轨道。 可磨损环形密封件的一部分在另一方面具有在与耐磨材料的轨道和复合织物之间以及复合织物和加强支撑件之间的界面垂直的方向上的撕裂性， 大于5.106牛顿每平方米。 还描述了制造这种片段的方法。

公开(公告)号：US08888448B2

公开(公告)日：2014-11-18

申请号：US13060748

申请日：2009-09-03

申请人： Laurent Ferrer ,  Claude Marcel Mons

发明人： Laurent Ferrer ,  Claude Marcel Mons

IPC分类号： F01D25/24 ,  F04D29/52 ,  F04D29/02 ,  F01D25/08 ,  B21K3/00 ,  B32B15/01 ,  B23P15/00 ,  F02C7/25 ,  B21D26/051

CPC分类号： B23P15/00 ,  B21D26/051 ,  B21K3/00 ,  B32B15/013 ,  F01D25/08 ,  F01D25/24 ,  F02C7/25 ,  F04D29/023 ,  F04D29/526 ,  F05D2230/23 ,  F05D2230/25 ,  F05D2230/26 ,  F05D2300/133 ,  F05D2300/171 ,  F05D2300/174 ,  F05D2300/175 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/675 ,  Y10T29/49636 ,  Y10T29/49805

摘要： A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A circular blank made of steel, or steel alloy, or superalloy which is incombustible in the presence of a titanium fire is hydroformed against a circular blank made from titanium or titanium alloy.

摘要翻译： 一种耐钛火（耐燃钛）的压缩机壳体的制造方法。 由钛或钛合金制成的圆形坯料对由钢或钢合金制成的圆形坯料或在钛火存在下不可燃的超耐热合金进行加氢成形。

公开(公告)号：US08715556B2

公开(公告)日：2014-05-06

申请号：US12934339

申请日：2009-03-27

申请人： Tsutomu Murakami ,  Hideo Morita ,  Takahiro Ogi ,  Ikuo Okumura ,  Katsuyoshi Moriya

发明人： Tsutomu Murakami ,  Hideo Morita ,  Takahiro Ogi ,  Ikuo Okumura ,  Katsuyoshi Moriya

IPC分类号： B23P15/02

CPC分类号： F01D5/282 ,  B29C70/30 ,  B29C70/46 ,  B29D99/0025 ,  B29K2105/0872 ,  B29L2031/082 ,  B29L2031/087 ,  F01D5/141 ,  F04D29/023 ,  F04D29/324 ,  F04D29/388 ,  F05D2230/26 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49336

摘要： A gas turbine engine blade for aircraft which has a 3-dimensional blade surface shape twisted around a center line at an angle of 45 degrees or more and 70 degrees or less, wherein the aforementioned blade is provided with multiple composite material prepregs which contain reinforced fiber and which are integrally molded after being laminated in the thickness direction, and the aforementioned reinforced fiber runs continuously without interruption within each layer of the aforementioned composite material prepregs.

摘要翻译： 一种用于飞行器的燃气涡轮发动机叶片，其具有以45度以上且70度以下的角度绕中心线扭转的3维叶片表面形状，其中，所述刀片设置有多个复合材料预浸料，其包含增强纤维 并且在厚度方向层叠后一体成型，上述复合材料预浸料的各层内的上述增强纤维连续地不间断地延伸。

公开(公告)号：US20110268566A1

公开(公告)日：2011-11-03

申请号：US13060726

申请日：2009-09-03

申请人： Laurent Ferrer ,  Claude Marcel Mons

发明人： Laurent Ferrer ,  Claude Marcel Mons

IPC分类号： F01D25/24 ,  B23P17/04

CPC分类号： B23P15/00 ,  B21C37/154 ,  B21H1/06 ,  B32B15/013 ,  F01D25/08 ,  F01D25/24 ,  F02C7/25 ,  F04D29/023 ,  F04D29/526 ,  F05D2230/14 ,  F05D2230/23 ,  F05D2230/25 ,  F05D2230/26 ,  F05D2300/133 ,  F05D2300/171 ,  F05D2300/174 ,  F05D2300/175 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/675 ,  Y10T29/49229

摘要： A method for manufacture of a compressor housing which is resistant to a titanium fire (burning titanium). A ring made of steel, steel alloy, or superalloy which is incombustible in the presence of a titanium fire is ring roll-bonded with a ring made from titanium or titanium alloy.

摘要翻译： 一种耐钛火（耐燃钛）的压缩机壳体的制造方法。 由钛或钛合金制成的环环形滚轧，由钢，钢合金或超耐热合金制成的环在钛火的存在下不可燃。

公开(公告)号：US4764089A

公开(公告)日：1988-08-16

申请号：US894409

申请日：1986-08-07

申请人： Thomas E. Strangman

发明人： Thomas E. Strangman

IPC分类号： F01D11/08 ,  F01D11/12

CPC分类号： F01D11/122 ,  F05D2230/26 ,  F05D2230/90

摘要： An abradable ceramic coated turbine shroud structure includes a grid of slant-steps isolated by grooves in a superalloy metal shroud substrate. A thin NiCrAlY bonding layer is formed on the machined slant-steps. A stabilized zirconia layer is plasma sprayed on the bonding layer at a sufficiently large spray angle to cause formation of deep shadow gaps in the zirconia layer. The shadow gaps provide a high degree of thermal strain tolerance, avoiding spalling. The exposed surface of the zirconia layer is machined nearly to the shadow gap ends. The turbine blade tips are treated to minimize blade tip wear during initial abrading of the zirconia layer. The procedure results in very close blade tip-to-shroud tolerances after the initial abrading.

摘要翻译： 可磨损的陶瓷涂覆的涡轮机护罩结构包括由超合金金属护罩衬底中的槽隔开的倾斜台栅。 在加工的倾斜台阶上形成薄的NiCrAlY粘结层。 将稳定的氧化锆层以足够大的喷射角度等离子体喷涂在粘合层上，以在氧化锆层中形成深的阴影间隙。 阴影间隙提供高度的热应变耐受性，避免剥落。 氧化锆层的暴露表面几乎加工成阴影间隙端。 处理涡轮叶片尖端以最小化氧化锆层初始研磨期间的叶片尖端磨损。 在初始研磨之后，该过程导致叶片尖端到护罩公差非常接近。

公开(公告)号：US20240060165A1

公开(公告)日：2024-02-22

申请号：US17892541

申请日：2022-08-22

申请人： Raytheon Technologies Corporation

发明人： Andrzej E. Kuczek ,  Tahany El-Wardany ,  Benjamin Bedard ,  Michael A. Klecka ,  Randy P. Salva ,  Krzysztof Barnat

IPC分类号： C22F1/04 ,  F01D5/14

CPC分类号： C22F1/04 ,  F01D5/147 ,  F05D2220/32 ,  F05D2240/30 ,  F05D2230/26

摘要： A system for deep rolling a fan blade including a shaft assembly disposed along a first axis; a hub connected to a distal end of the shaft assembly, the hub having an upper hub portion and a lower hub portion extending along a second axis, the second axis forming an angle relative to a first axis; a roller disk joined to the lower portion of the hub, the roller disk configured to contact a fan blade; a fixture supporting the fan blade; the fixture comprising a body supporting a pivot clamp attached to the body with a pivot; a support attached to the body, the support is configured to engage an airfoil portion of the fan blade; a receiver formed in the body for supporting a root of the fan blade; and a shoulder attached to the body configured to support a platform portion of the fan blade.

公开(公告)号：US20190184443A1

公开(公告)日：2019-06-20

申请号：US16019790

申请日：2018-06-27

申请人： Standex International Corporation

发明人： Richard J. Morganti

IPC分类号： B21D22/14 ,  B21D53/92 ,  F02C7/04 ,  B64D29/00 ,  B64D33/02 ,  B64F5/60

CPC分类号： B21D22/14 ,  B21D53/92 ,  B64D29/00 ,  B64D33/02 ,  B64F5/60 ,  F02C7/04 ,  F05D2220/323 ,  F05D2230/232 ,  F05D2230/26 ,  F05D2230/41

摘要： Method of manufacturing of components used in the field of aviation aircraft and, specifically, an aircraft engine nacelle lipskin. Instead of spinning flat plates, this method uses spinning a cylinder, thus eliminating waste material. It also eliminates the need for rivet lines which results in better laminar flow. Further, there is a reduction of other costs in addition to reducing drag.