公开(公告)号：EP3178601A1

公开(公告)日：2017-06-14

申请号：EP15198596.7

申请日：2015-12-09

申请人： General Electric Technology GmbH

发明人： Pesce, Michele ,  Hoffmann, Jürgen Gerhard

IPC分类号： B23P6/00 ,  F01D5/00 ,  F01D5/30 ,  F04D29/32 ,  F04D29/34

CPC分类号： F04D29/34 ,  B23P6/005 ,  F01D15/10 ,  F04D29/325 ,  F04D29/38 ,  F05D2220/32 ,  F05D2230/80 ,  F05D2250/281 ,  H02K9/06

摘要： The present disclosure refers to a method for repairing a blade (10) connection of a generator rotor (16) comprising an internally threaded hole (17) formed in the generator rotor (16) and an externally threaded blade root (14). The method comprising the steps of removing the blade (10) from the generator rotor (16), removing material of a first section (11) of the root (14) extending from an end of the root (14) closest to the airfoil (15), and screwing the blade (10) back into the threaded hole (17).
Besides the method a reworked blade (10) and a reworked blade generator rotor (16) connection is disclosed.

摘要翻译： 本发明涉及一种用于修复发电机转子（16）的叶片（10）连接的方法，该发电机转子包括形成在发电机转子（16）中的内螺纹孔（17）和外螺纹叶片根部（14）。 所述方法包括以下步骤：从发电机转子（16）移除叶片（10），移除根部（14）的第一部分（11）的材料，所述第一部分从最接近翼型的根部（14） 15），并将刀片（10）拧回到螺纹孔（17）中。 除了该方法之外，还公开了一种再加工刀片（10）和再加工刀片发生器转子（16）的连接。

公开(公告)号：EP2842868B1

公开(公告)日：2017-04-26

申请号：EP14002860.6

申请日：2014-08-18

申请人： Airbus Helicopters

发明人： Gaffiero, Jacques ,  Amari, André

IPC分类号： B64C11/28 ,  B64C27/50

CPC分类号： B64C27/50 ,  B64C27/48 ,  F04D29/34 ,  F04D29/36

公开(公告)号：EP3140551A1

公开(公告)日：2017-03-15

申请号：EP15788951.0

申请日：2015-05-01

申请人： Horton, Inc.

发明人： CAHILL, Kevin ,  STRAUSS, Eric ,  BURCHETT, Doug ,  DIDANDEH, Hooshang ,  SHOGREN, Charles Mark

IPC分类号： F04D29/26 ,  F04D25/08

CPC分类号： F04D29/34 ,  F04D29/023 ,  F04D29/329 ,  F04D29/384 ,  F04D29/388 ,  F04D29/646 ,  F05D2260/941 ,  F05D2300/603 ,  F05D2300/61

摘要： The present invention relates to a composite blade (24; 24') for a modular axial flow fan (20), the blade comprising a tip (24-1) a root end (24-2) opposite the tip, wherein a blade length (L) is defined between the root end and the tip a mounting pad (30) located adjacent to the root end, a working portion (34) adjoining the tip, wherein the working portion defines an aerodynamic profile, a transition zone (32) between the mounting pad and the working portion; and a reinforcement skin localized about the root end along the blade length, wherein the reinforcement skin extends through the mounting pad and the transition zone and into the working portion.

摘要翻译： 制造模块化风扇的方法包括将叶片的安装垫定位在中心轮毂组件的两个板之间，使叶片对准，使得安装垫位于两个板中的至少一个的外边缘的径向内侧，以及 将两个板中的至少一个板的外边缘与外边缘处的叶片间隔开。

公开(公告)号：EP2697517B1

公开(公告)日：2016-03-16

申请号：EP12721327.0

申请日：2012-04-05

申请人： PELLENC (Société Anonyme)

发明人： PELLENC, Roger ,  GILBERT, Philippe

IPC分类号： F04D29/32 ,  F04D29/38 ,  F04D29/64 ,  F04D29/02

CPC分类号： F04D29/329 ,  F04D29/023 ,  F04D29/34 ,  F04D29/384 ,  F04D29/388 ,  F04D29/64 ,  F04D29/646 ,  F05D2230/23 ,  F05D2300/12 ,  F05D2300/43

公开(公告)号：EP2752581A3

公开(公告)日：2016-02-24

申请号：EP13155207.7

申请日：2013-02-14

申请人： Acer Incorporated

发明人： Kuo, Chun-Chih ,  Lin, Che-Wei

IPC分类号： F04D27/00 ,  F04D29/38

CPC分类号： F04D29/30 ,  F04D27/002 ,  F04D29/281 ,  F04D29/282 ,  F04D29/34 ,  F04D29/38 ,  F04D29/382 ,  G06F1/20 ,  H05K7/20136

摘要： A fan module including a first fan, a second fan and a actuator is provided. The first fan has a first pivot portion and a plurality of first fan blades. Each first fan blade has a first blade face. The second fan has a second pivot portion and a plurality of second fan blades corresponding to the first fan blades. Each second fan blade has a second blade face. The second pivot portion is slidably disposed at a containing cavity of the first pivot portion. The actuator is adapted to drive the first fan to rotate. The first fan is adapted to drive the second fan to rotate. When the second pivot portion protrudes out of the containing cavity, a part of each of the second blade faces does not overlap with the corresponding first blade face along a direction perpendicular to the corresponding first blade face.

公开(公告)号：EP2427653A4

公开(公告)日：2016-01-06

申请号：EP10772674

申请日：2010-05-04

申请人： OLESON RICHARD A ,  FIZER RICHARD W ,  KIDD H KEITH

发明人： OLESON RICHARD A ,  FIZER RICHARD W ,  KIDD H KEITH

IPC分类号： F03B13/00 ,  F04D25/08 ,  F04D27/00 ,  F04D29/34 ,  F04D29/36 ,  H05B39/08

CPC分类号： F04D25/088 ,  F04D27/002 ,  F04D27/004 ,  F04D27/007 ,  F04D29/34 ,  F04D29/36 ,  H05B39/08

摘要： A fan comprises a hub, fan blades, and inserts. The hub comprises outwardly extending mounting tabs that lie along a common horizontal plane. The fan blades are hollow, such that each mounting tab is inserted in the hollow interior of a corresponding fan blade. Each insert is positioned in the hollow interior of each fan blade, between each mounting tab of the hub and the interior surface of the corresponding fan blade. Each insert is configured to position and maintain the chord line of each corresponding fan blade at an oblique angle relative to the horizontal plane of the hub. A kit may include several insert sets to choose from to provide adjustable angle of attack. A fan control system includes a dimmer switch and a control module, which allows the dimmer switch to be used to infinitely adjust the speed of a fan motor within a range.

公开(公告)号：EP2865849A1

公开(公告)日：2015-04-29

申请号：EP14188731.5

申请日：2014-10-14

申请人： Rolls-Royce plc

发明人： Jevons, Matthew

IPC分类号： F01D5/30 ,  F01D5/32

CPC分类号： F04D29/34 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/326 ,  F04D19/002 ,  F05D2260/30 ,  F05D2300/6012 ,  F05D2300/603

摘要： A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is formed from fibre-reinforced composite material, at least a portion of the composite material being reinforced by 3D-woven fibre tows.

摘要翻译： 提供了一种保持板，用于将燃气涡轮发动机的风扇叶片的燕尾根保持在风扇盘的边缘中的对应的轴向延伸槽中。 在使用中，板位于形成在槽的端部处的空腔中，使得板的第一侧布置成与燕尾根的轴向端面接触，并且板的相对的第二侧被布置成与 空腔的邻接表面以限制根部沿着槽的轴向运动。 保持板由纤维增强复合材料形成，复合材料的至少一部分由3D织物纤维束加强。

公开(公告)号：EP2738392A3

公开(公告)日：2014-12-24

申请号：EP13194497.7

申请日：2013-11-26

申请人： Pratt & Whitney Canada Corp.

发明人： Heikurinen, Karl ,  Townsend, Peter

IPC分类号： F04D29/02 ,  F04D29/32 ,  F01D5/30 ,  F01D5/34 ,  B23K20/12

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 (12) for a turbofan gas turbine engine comprises a rotor hub (36) and a plurality of radially extending fan blades (20) integral with the hub (36) to form an integrally bladed rotor. Each fan blade (20) defines a leading edge (34). A hub radius (R HUB ) is the radius of the leading edge (34) at the hub (36) relative to a centerline of the fan. A tip radius (R TIP ) is the radius of the leading edge (34) at a tip (40) of the fan blade (20) relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R HUB /R TIP ) is at least 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 or equal to 0.25.

摘要翻译： 用于涡轮风扇燃气涡轮发动机的风扇（12）包括转子毂（36）和与毂（36）一体形成整体叶片转子的多个径向延伸的风扇叶片（20）。 每个风扇叶片（20）限定前缘（34）。 轮毂半径（RHUB）是轮毂（36）处的前缘（34）相对于风扇中心线的半径。 尖端半径（RTIP）是风扇叶片（20）的末端（40）处的前缘（34）相对于风扇中心线的半径。 轮毂半径与末端半径之比（RHUB / RTIP）至少小于0.29。 在一个特定的实施例中，这个比率在0.25和0.29之间。 在另一个特定实施例中，该比率小于或等于0.25。

公开(公告)号：EP1884624A3

公开(公告)日：2012-10-24

申请号：EP07112070.3

申请日：2007-07-09

申请人： GENERAL ELECTRIC COMPANY

发明人： MOLLMANN, Daniel E. ,  HENNING, Thomas R. ,  CRALL, David W. ,  OAKLAND, Matthew A. ,  DAHLING, Todd M.

IPC分类号： F01D5/30 ,  F01D5/02

CPC分类号： F01D5/027 ,  F01D5/26 ,  F01D5/3007 ,  F04D29/34 ,  F05D2230/60 ,  F05D2260/96 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

摘要： A rotor assembly (100) is provided. The rotor assembly (100) includes a disk (42) including a plurality of circumferentially-spaced blade root slots defined therein, and a plurality of blades (40), each the blade including a root (108), a tip (110), and an airfoil (106) therebetween, each the blade positioned within a pre-determined slot (108) based on a blade map, the blade map generated by a computer system configured to, receive (302) at least one geometric parameter measurement of a plurality of blades in a row of blades, determine (306) a maximum difference between adjacent blades in the row of blades of at the least one received geometric parameter measurement, determine (308) a vector sum of the at least one received geometric parameter measurements, determine (310) a plurality of moment weight vector sums of the plurality of blades in the row of blades, and determine a sequence map of the plurality of blades using the maximum difference of the at least one geometric parameter measurement between adjacent blades in the row of blades, the vector sum of the at least one received geometric parameter measurement, and the plurality of moment weight vector sums.

公开(公告)号：EP2456665A2

公开(公告)日：2012-05-30

申请号：EP10752050.4

申请日：2010-07-20

申请人： Airbus Operations

发明人： LAFONT, Laurent

IPC分类号： B64C11/06 ,  F01D5/30 ,  F04D29/36 ,  F04D29/34

CPC分类号： F01D21/045 ,  B64C11/04 ,  B64C11/48 ,  B64D2027/026 ,  F01D5/3053 ,  F02C6/206 ,  F02K3/025 ,  F04D29/322 ,  F04D29/34 ,  F05D2220/324 ,  Y02T50/66 ,  Y02T50/673

摘要： The invention relates to an aircraft turbine engine propeller, comprising a plurality of blades (1) mounted on a hub (2) that is rotatable about a rotational axis (I-I) of the propeller, the aim of the invention being to reduce the risks of losing the blade after impact from a foreign body. To accomplish the aim, the blade includes a recess (30) leading radially inside at the root (20) thereof. A blade-retaining device (50) includes movable retaining means (53A, 53B) located in said recess (30) and movable from a retracted position to a deployed position for retaining the blade, and vice versa.