公开(公告)号：US20170268378A1

公开(公告)日：2017-09-21

申请号：US15450143

申请日：2017-03-06

申请人： MTU Aero Engines AG

发明人： Alexander KLOETZER

IPC分类号： F01D25/00 ,  F01D25/24 ,  F01D9/04 ,  F01D17/16

CPC分类号： F01D17/162 ,  F01D5/28 ,  F05D2230/10 ,  F05D2230/232 ,  F05D2230/237 ,  F05D2230/239 ,  F05D2240/12

摘要： Disclosed is an adjustable guide vane for a turbomachine, especially for a turbine stage or compressor stage of a gas turbine, which comprises a vane airfoil for deflecting a working fluid of the turbomachine and which is produced at least partially from a second material, and at least one first vane section which is produced from a first material which is different from the second material.

公开(公告)号：US20170204877A1

公开(公告)日：2017-07-20

申请号：US15326618

申请日：2015-07-13

申请人： Safran Aero Boosters S.A.

发明人： Francois Hindryckx

IPC分类号： F04D29/54 ,  B29C53/36 ,  B23K20/24 ,  B29C65/06 ,  B23K20/12 ,  B23K20/233

CPC分类号： F04D29/542 ,  B23K20/12 ,  B23K20/129 ,  B23K20/233 ,  B23K20/24 ,  B23K20/26 ,  B23K2101/001 ,  B23K2103/14 ,  B23K2103/42 ,  B23P15/006 ,  B29C53/36 ,  B29C65/0609 ,  B29C65/0618 ,  B29C65/0636 ,  B29C66/532 ,  B29C66/61 ,  B29C66/73921 ,  B29K2101/12 ,  B29L2031/08 ,  F01D9/044 ,  F04D29/023 ,  F05D2230/239

摘要： The invention relates to a method of producing a low-pressure compressor stator for an axial turbine engine. The stator comprises an external shroud with stubs and an annular row of stator blades extending radially towards the inside from the stubs. The method comprises the following stages: supply or production of a starting bar; bending of the bar so that it makes a circle, in order to form an unwrought external shroud; turning to form an axial annular wall delimited by annular fixing flanges; orbital friction-welding of a row of blades onto the stubs of the external shroud. The stubs are realized during a milling stage of the bar or of the external shroud, the milling being carried out before or after the bending stage. The shroud and the blades can be produced in titanium or in a thermoplastic polymer.

公开(公告)号：US20170022827A1

公开(公告)日：2017-01-26

申请号：US14806933

申请日：2015-07-23

申请人： HONEYWELL INTERNATIONAL INC.

发明人： David R. Waldman ,  Don Mittendorf ,  Mark C. Morris ,  Michael Vinup

IPC分类号： F01D5/30 ,  B23K20/12 ,  B23K20/22 ,  B23K20/02 ,  B23K20/14 ,  B23K20/08 ,  B23K9/167 ,  B23K9/23 ,  B23K5/14 ,  B23K5/00 ,  B23K10/02 ,  B23K15/00 ,  B23K26/32 ,  B23K26/21 ,  F01D5/02

CPC分类号： F01D5/3061 ,  B23K20/1205 ,  B23K20/16 ,  B23K2101/001 ,  F01D5/082 ,  F01D5/34 ,  F01D11/006 ,  F05D2230/239 ,  F05D2300/606 ,  F05D2300/607 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

摘要： Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery; providing a plurality of turbine blades, each of which comprising an airfoil portion and a shank portion, the shank portion having a base surface; metallurgically bonding a compliant alloy material layer to either or both of the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks; and linear friction welding the plurality of blades to the turbine disk so as to form a bond plane between the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks, the compliant alloy material layer being disposed at the bond plane.

摘要翻译： 提供混合式涡轮转子及其制造方法。 一种混合式混合涡轮机转子的制造方法，包括以下步骤：提供涡轮盘，该涡轮盘具有边缘部分，该边缘部分包括周向连续材料的活边缘和在涡轮盘的外周中的多个带状轮缘切口， 限定外周的附接表面; 提供多个涡轮叶片，每个涡轮叶片包括翼型部分和柄部分，所述柄部分具有基部表面; 将柔性合金材料层冶金结合到涡轮盘的凸起刀片附件表面中的一个或两个以及刀片柄的基座表面; 并且将所述多个叶片线性摩擦焊接到所述涡轮盘，以便在所述涡轮盘的所述凸起的叶片附接表面与所述叶片柄的基底表面之间形成接合平面，所述柔性合金材料层设置在所述接合平面处。

公开(公告)号：US20160238022A1

公开(公告)日：2016-08-18

申请号：US15052178

申请日：2016-02-24

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Karl Heikurinen ,  Peter Townsend

IPC分类号： F04D29/38 ,  F04D29/34 ,  F04D29/64 ,  F04D29/32

CPC分类号： F04D29/384 ,  B23K20/129 ,  B23K2101/001 ,  F01D5/14 ,  F01D5/3061 ,  F01D5/34 ,  F02K3/06 ,  F04D29/023 ,  F04D29/321 ,  F04D29/324 ,  F04D29/329 ,  F04D29/34 ,  F04D29/388 ,  F04D29/644 ,  F05D2230/239 ,  F05D2260/40 ,  Y10T29/49245

摘要： A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.

摘要翻译： 公开了一种具有低轮毂与尖端比率的涡轮风扇燃气涡轮发动机的风扇。 风扇包括转子毂和多个径向延伸的风扇叶片。 每个风扇叶片限定轮毂半径（RHUB），其是轮毂相对于风扇的中心线的前缘的半径，以及尖端半径（RTIP），其是前端的前端的半径 风扇叶片相对于风扇的中心线。 轮毂半径与顶端半径（RHUB / RTIP）的比值小于0.29。 在一个具体实施方案中，该比率在0.25和0.29之间。 在另一具体实施方案中，该比例小于0.25。

公开(公告)号：US20160237834A1

公开(公告)日：2016-08-18

申请号：US14622344

申请日：2015-02-13

申请人： United Technologies Corporation

发明人： Jordan J. Franklin

IPC分类号： F01D5/30 ,  B23K20/12 ,  F04D29/32 ,  F04D29/64 ,  F01D5/00 ,  F01D5/02

CPC分类号： F01D5/3061 ,  B23K20/1205 ,  B23K20/129 ,  B23K2101/001 ,  F01D5/005 ,  F01D5/02 ,  F01D5/34 ,  F04D29/322 ,  F04D29/644 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/232 ,  F05D2230/236 ,  F05D2230/239 ,  F05D2240/30

摘要： Systems and methods are provided related to manufacturing, repairing or otherwise providing an integrally bladed rotor. In one method, a set of preform rotor blades are arranged relative to a rotor disk. The preform rotor blades are concurrently bonded to the rotor disk.

摘要翻译： 提供了与制造，修理或以其他方式提供整体叶片转子有关的系统和方法。 在一种方法中，相对于转子盘布置一组预制件转子叶片。 预型转子叶片同时结合到转子盘上。

公开(公告)号：US09114481B1

公开(公告)日：2015-08-25

申请号：US14185997

申请日：2014-02-21

申请人： Siemens Energy, Inc.

发明人： Gerald J. Bruck ,  Ahmed Kamel

IPC分类号： B23K20/12 ,  B23K28/02

CPC分类号： B23K20/12 ,  B23K20/129 ,  B23K2101/001 ,  B23P6/005 ,  F01D5/06 ,  F01D5/063 ,  F05D2230/239

摘要： A method of friction welding. A cutout (35) is formed in an edge (34) of a wall such as a turbine blade platform (24). The cutout has a concave surface of rotation of up to 180 degrees in angular extent that is open to the wall edge The circumference (40) of a rotating disk (36) of additive material is pressed into the cutout. Surface friction creates heat that fuses the disk into the surface of the cutout Scrap material is then trimmed flush with the wall surfaces. Two such processes may be performed on opposite edges (34A, 34B) of a wall, balancing the inward pressing forces (42A, 42B) of two disks. The disk may be rotary oscillated (56), such as plus and minus 5 degrees, thereby allowing a non-contacting part of the disk circumference to be eliminated Thin walls may be supported by incompressible fugitive material (70).

摘要翻译： 一种摩擦焊接方法。 在诸如涡轮叶片平台（24）的壁的边缘（34）中形成切口（35）。 切口具有向壁边缘开口的角度范围内的至多180度的旋转凹面。添加剂材料的旋转盘（36）的圆周（40）被压入切口中。 表面摩擦产生热量，将磁盘熔化到切割表面上。然后将废料与墙壁表面齐平。 可以在壁的相对边缘（34A，34B）上执行两个这样的过程，平衡两个盘的向内的压力（42A，42B）。 磁盘可以是旋转振荡（56），例如正负5度，从而允许消除磁盘圆周的非接触部分。薄壁可以由不可压缩的缓冲材料（70）支撑。

公开(公告)号：US08784065B2

公开(公告)日：2014-07-22

申请号：US13114177

申请日：2011-05-24

申请人： Nan Yang ,  Jeff A. Jensen ,  Jesus G. Chapa Cabrera

发明人： Nan Yang ,  Jeff A. Jensen ,  Jesus G. Chapa Cabrera

IPC分类号： F01D5/02

CPC分类号： F01D5/025 ,  B23K20/129 ,  B23K20/233 ,  B23K2103/24 ,  F05D2220/40 ,  F05D2230/239 ,  F05D2230/25 ,  F05D2300/174 ,  F05D2300/182

摘要： A frictional welding process for joining a titanium aluminide turbine to a titanium alloy shaft is disclosed. The disclosed process includes preheating the turbine to a designated temperature, providing a specially-designed joining interface geometry at the distal end of the shaft and optimizing the frictional welding parameters. The frictional welding is carried out in multiple steps but, while the shaft is being spun by a rotating chuck, two different pressures and two different time periods are used until the narrower portions of the distal end of the shaft have been fused onto the welding surface of the turbine. Then, an additional forging step with yet another engagement pressure between the shaft and the turbine is carried out without rotation of the shaft.

摘要翻译： 公开了一种用于将钛铝合金涡轮机连接到钛合金轴的摩擦焊接方法。 所公开的方法包括将涡轮预热到指定温度，在轴的远端提供特别设计的接合界面几何形状并优化摩擦焊接参数。 摩擦焊接是以多个步骤进行的，但是当轴通过旋转卡盘旋转时，使用两个不同的压力和两个不同的时间段，直到轴的远端的较窄部分已熔合到焊接表面上 的涡轮。 然后，在轴和涡轮之间的另一个接合压力下进行另外的锻造步骤而不转动轴。

公开(公告)号：US08647011B2

公开(公告)日：2014-02-11

申请号：US12855095

申请日：2010-08-12

申请人： Karl Schreiber

发明人： Karl Schreiber

IPC分类号： A47B96/06

CPC分类号： F01D5/02 ,  F01D5/282 ,  F05D2230/239 ,  F05D2300/224 ,  F05D2300/603 ,  F05D2300/614 ,  F16C3/026 ,  F16C2360/23 ,  Y02T50/672 ,  Y10T403/65

摘要： On an engine shaft of hybrid design with an externally toothed power transmission element connected at the ends of a fiber-composite plastic tube, the power transmission element is of a two-part design and includes a toothed part made of steel of a specific hardness and, frontally weldedly connected thereto, a tapering adapter part enclosed by a fiber-composite material to form a scarf-type joint and having a thermal expansion approximately equal to the expansion behavior of the fiber-composite material.

摘要翻译： 在混合设计的发动机轴上，在纤维复合塑料管的端部连接有外齿的动力传递元件，动力传递元件是两部分设计的，包括由具有特定硬度的钢制成的齿形部分， 与前面焊接连接的一个锥形接头部分，由纤维复合材料包围以形成围巾型接头，其热膨胀近似等于纤维复合材料的膨胀行为。

公开(公告)号：US20130323074A1

公开(公告)日：2013-12-05

申请号：US13485676

申请日：2012-05-31

申请人： John E. Matz ,  Timothy M. Hollman ,  Xinwen Xiao ,  Phillip Creed

发明人： John E. Matz ,  Timothy M. Hollman ,  Xinwen Xiao ,  Phillip Creed

IPC分类号： F01D5/02 ,  B23P17/00

CPC分类号： F01D5/026 ,  F01D5/063 ,  F01D5/066 ,  F05D2230/239 ,  F05D2230/25 ,  F05D2260/36 ,  Y10T29/4932

摘要： An assembly for use in a turbine of a gas turbine engine includes a turbine disk and a shaft. The turbine disk comprises a superalloy. The shaft is friction welded to the turbine disk at a shaft interface substantially adjacent the turbine disk.

摘要翻译： 用于燃气涡轮发动机的涡轮机的组件包括涡轮盘和轴。 涡轮盘包括超级合金。 轴在基本上与涡轮盘相邻的轴接口处摩擦焊接到涡轮盘。

公开(公告)号：US20130308419A1

公开(公告)日：2013-11-21

申请号：US13473853

申请日：2012-05-17

申请人： Surendra Singh ,  Frederick William Vensel ,  Robert John Hogan ,  Vincent Chung

发明人： Surendra Singh ,  Frederick William Vensel ,  Robert John Hogan ,  Vincent Chung

IPC分类号： G03B42/06

CPC分类号： G01N29/043 ,  F01D5/34 ,  F05D2230/239 ,  F05D2260/80 ,  G01N29/069 ,  G01N29/262 ,  G01N29/265 ,  G01N29/30 ,  G01N29/4436 ,  G01N2291/267 ,  G01N2291/2693

摘要： The disclosed embodiments generally relate to non-destructive evaluation methods. More particularly, the disclosed embodiments relate to ultrasonic non-destructive evaluation methods for the evaluation of friction welded bladed discs (“blisks”). In an embodiment, a method for non-destructive evaluation of a bladed disc structure includes identifying a region of interest on the bladed disc structure; positioning an ultrasonic transducer and receiver in the region of interest; scanning the region of interest using the ultrasonic transducer and receiver to produce a scan image; and comparing the scan image against a reference image to determine the presence of an anomaly in the region of interest.

摘要翻译： 所公开的实施例通常涉及非破坏性评估方法。 更具体地，所公开的实施例涉及用于评估摩擦焊接叶片盘（“叶片”）的超声波非破坏性评估方法。 在一个实施例中，一种用于对盘形盘结构进行非破坏性评估的方法包括识别刀片​​盘结构上的感兴趣区域; 将超声换能器和接收器定位在感兴趣的区域中; 使用超声波换能器和接收器扫描感兴趣区域以产生扫描图像; 以及将扫描图像与参考图像进行比较以确定感兴趣区域中是否存在异常。