利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

646 条记录 (耗时 0.022 秒)

    Rotor with improved balancing features
    124.
    发明授权
    Rotor with improved balancing features 有权
    转子具有改进的平衡特性

    公开(公告)号：US09453413B2

    公开(公告)日：2016-09-27

    申请号：US13675276

    申请日：2012-11-13

    申请人： Pratt & Whitney Canada Corp.

    发明人： David Denis ,  Amir Maria

    IPC分类号： F01D5/10 ,  F01D5/02 ,  F04D29/66 ,  G01M1/32 ,  B23P15/00

    CPC分类号： F01D5/027 ,  B23P15/006 ,  F01D5/10 ,  F04D29/662 ,  F05B2260/966 ,  F05D2260/96 ,  G01M1/32 ,  Y10T29/49234 ,  Y10T29/49316

    摘要： A rotor assembly for a gas turbine engine including a circumferential array of regularly spaced apart features provided on the disk which are each configured for receiving a balancing weight. The circumferential array of features has an angular orientation relative to the circumferential array of blades such that the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent blade.

    摘要翻译： 一种用于燃气涡轮发动机的转子组件，其包括设置在盘上的规则间隔的特征的周向阵列，每个构造成用于接收平衡重。 特征的圆周阵列具有相对于圆周阵列的叶片的角度取向，使得特征各自位于与相应相邻叶片的堆叠线至少基本相同的偏移角。

    METHOD OF PRODUCING AN INTEGRALLY BLADED ROTOR FOR A TURBOMACHINE
    125.
    发明申请
    METHOD OF PRODUCING AN INTEGRALLY BLADED ROTOR FOR A TURBOMACHINE 有权
    生产用于涡轮机的整体叶片转子的方法

    公开(公告)号：US20160175983A1

    公开(公告)日：2016-06-23

    申请号：US14943675

    申请日：2015-11-17

    申请人： ROLLS-ROYCE PLC

    发明人： Nigel James David CHIVERS

    IPC分类号： B23K26/00 ,  B23P15/00 ,  B23K26/342

    CPC分类号： B23K26/0093 ,  B22F5/04 ,  B22F2998/10 ,  B23K26/144 ,  B23K26/342 ,  B23K2101/001 ,  B23K2103/14 ,  B23K2103/26 ,  B23P15/006 ,  F01D5/147 ,  F01D5/18 ,  F01D5/3061 ,  F01D5/34 ,  F05D2230/31 ,  Y02P10/295 ,  B22F3/1055 ,  B22F3/17

    摘要： There is proposed a method of producing an integrally bladed rotor, preferably a so-called “blisk” for a turbomachine, the method including the steps of: providing a rotor disc having a plurality of spaced-apart radial protrusions formed integrally around its perimeter; and forming a respective aerofoil-shaped blade extending radially generally outwardly from each of the protrusions via laser deposition. Each protrusion preferably extends radially outwardly from a circumferential body part of the rotor disc by a distance which is greater than the radially inward penetration of a heat-affected zone arising from the laser deposition used to form the respective blade.

    摘要翻译： 提出了一种制造整体叶片式转子的方法，优选用于涡轮机的所谓的“叶片”，该方法包括以下步骤：提供一种转子盘，该转子盘具有围绕其周边整体形成的多个间隔开的径向突起; 并且通过激光沉积形成从每个突起径向大致向外延伸的相应的翼型叶片。 每个突起优选地从转子盘的周向主体部分径向向外延伸一定距离，该距离大于由用于形成相应刀片的激光沉积引起的受热影响区的径向向内穿透。

    Rotor With Blades Secured by Woven Fiber Attachment System
    126.
    发明申请
    Rotor With Blades Secured by Woven Fiber Attachment System 审中-公开
    带有叶片的转子由机织纤维附着系统固定

    公开(公告)号：US20160146023A1

    公开(公告)日：2016-05-26

    申请号：US14933129

    申请日：2015-11-05

    申请人： United Technologies Corporation

    发明人： Anthony R. Bifulco ,  Damon K. Brown ,  Nicholas Aiello

    IPC分类号： F01D5/30 ,  F01D5/14

    CPC分类号： B23P15/006 ,  F01D5/282 ,  F01D5/34 ,  F05D2300/6033

    摘要： A propulsive engine rotor configured for operation within a gas turbine includes a plurality of spaced airfoil blades circumferentially affixed to an outer hoop-style rim. At least two of the airfoil blades have an integral root configured to extend either through or at least radially inwardly from the rim. A woven fiber system provides that the blade roots are interdigitally wrapped by a plurality of woven fibers before impregnation and/or encapsulation of the fibers and wrapped roots within a ceramic or other composite matrix material to form a composite ring. The composite ring defines the interior body of the rotor, includes a bore through which passes the rotational axis of the rotor, and has a lower mass than the rotor rim. The woven fiber interface between the roots increases the tensile load capacity of the airfoil blades relative to the composite ring, and increases the self-sustaining radius of the rotor.

    摘要翻译： 构造成用于在燃气涡轮机内操作的推进式发动机转子包括多个间隔开的叶片叶片，周向地固定在外箍型轮缘上。 至少两个翼型叶片具有构造成从轮缘延伸穿过或至少径向向内延伸的整体根部。 编织纤维系统规定，在将纤维和包裹的根部浸入陶瓷或其它复合基质材料中以形成复合环之前，叶片根部被多个编织纤维叉指地包裹。 复合环限定转子的内部主体，包括通过转子的旋转轴线并且具有比转子轮辋更低的质量的孔。 根部之间的机织纤维界面增加了翼型相对于复合环的拉伸载荷能力，并提高了转子的自维持半径。

    TURBINE NOZZLE AND MANUFACTURING METHOD THEREOF
    128.
    发明申请
    TURBINE NOZZLE AND MANUFACTURING METHOD THEREOF 审中-公开
    涡轮喷嘴及其制造方法

    公开(公告)号：US20150354593A1

    公开(公告)日：2015-12-10

    申请号：US14760517

    申请日：2014-02-17

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Hiromichi HIRAKI ,  Yoshihiro KAWAMATA

    IPC分类号： F04D29/54 ,  B23K31/02 ,  B23P15/00 ,  B23K1/00

    CPC分类号： F04D29/54 ,  B23K1/0018 ,  B23K31/02 ,  B23P15/006 ,  B23P15/008 ,  F01D9/044 ,  F01D25/246 ,  F05D2230/237 ,  Y10T29/49325

    摘要： A manufacturing method of a turbine nozzle is provided. The method includes: (A) forming a first part which includes a blade and one of an inner ring portion and an outer ring portion integrated therein; (B) forming the other of the inner ring portion and the outer ring portion as a second part; (C) combining the first part and the second part such that an outer side surface of the inner ring portion and an inner side surface of the outer ring portion are arranged to oppose each other and that a gap is formed between the blade of the first part and the second part; and (D) flowing a brazing material in a molten state into the gap to braze the blade of the first part and the second part.

    摘要翻译： 提供一种涡轮喷嘴的制造方法。 该方法包括：（A）形成第一部分，该第一部分包括一个叶片和一体的内环部分和一个外环部分; （B）形成作为第二部分的内环部分和外环部分中的另一个; （C）组合第一部分和第二部分，使得内环部分的外侧表面和外环部分的内侧表面布置成彼此相对，并且在第一部分和第二部分的叶片之间形成间隙 部分和第二部分; 和（D）将熔融状态的钎焊材料流入所述间隙以钎焊所述第一部分和所述第二部分的所述刀片。