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162 records (took 0.039 seconds)

    Spiral wound bound seal
    41.
    发明授权
    Spiral wound bound seal 有权
    螺旋缠绕封印

    公开(公告)号：US08690159B2

    公开(公告)日：2014-04-08

    申请号：US13381560

    申请日：2010-06-23

    Applicant: David J. Peer ,  Robert E. Kunselman

    Inventor： David J. Peer ,  Robert E. Kunselman

    IPC: F01D11/02

    CPC classification number: F16J15/3288 ,  F01D11/001 ,  F01D11/08 ,  F02C7/28 ,  F04D29/162 ,  F05D2240/56 ,  F05D2250/15 ,  F05D2250/25 ,  Y10T29/49826

    Abstract: A brush seal is disclosed that may include a spring-loaded seal arrangement configured to conform to a wide range of sealing diameters along the length of a rotor of a turbomachine. In particular, the brush seal may be manufactured with free ends configured to overlap and provide a finite amount of radially expandable/contractible play and yet maintain an effective seal. Consequently, the same brush seal design may be used in a range of locations along a rotor length without the need to specifically manufacture separate brush seals for each variance in dimension.

    Abstract translation: 公开了一种刷密封件，其可以包括弹簧加载的密封装置，其构造成沿着涡轮机的转子的长度符合宽范围的密封直径。 特别地，刷密封可以制造成具有被配置为重叠并且提供有限量的可径向扩张/收缩的游隙并且保持有效密封的自由端。 因此，可以沿着转子长度的一系列位置使用相同的电刷密封设计，而不需要为每个尺寸变化特别制造单独的电刷密封件。

    Jet Engine With Deflector
    42.
    发明申请
    Jet Engine With Deflector 有权

    公开(公告)号：US20130294894A1

    公开(公告)日：2013-11-07

    申请号：US13874731

    申请日：2013-05-01

    Applicant: Michael J. Kline

    Inventor： Michael J. Kline

    IPC: F01D17/10

    CPC classification number: F02C7/055 ,  F01D17/10 ,  F05D2250/15 ,  F05D2250/25 ,  Y02T50/672

    Abstract: A deflector for a jet engine. The deflector may prevent the jet engine from ingesting birds during a bird strike scenario. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

    TORSION SEAL
    44.
    发明申请
    TORSION SEAL 有权
    扭转密封

    公开(公告)号：US20120306167A1

    公开(公告)日：2012-12-06

    申请号：US13152585

    申请日：2011-06-03

    Applicant: Sheo Narain Giri

    Inventor： Sheo Narain Giri

    IPC: F01D11/00 ,  F16J15/02

    CPC classification number: F16J15/0887 ,  F01D11/003 ,  F05D2250/15 ,  F05D2260/38

    Abstract: A torsion seal is provided and includes a first section, a second section and a torsion section connected at opposite end portions thereof to the first and second sections and having a central portion extending between the opposite end portions to absorb differential thermal growth of vessels to which the first and second sections are coupled.

    Abstract translation: 提供扭转密封件，并且包括第一部分，第二部分和扭转部分，该部分在其相对端部处连接到第一和第二部分，并且具有在相对端部之间延伸的中心部分，以吸收容器的不同热生长， 第一和第二部分联接。

    Exhaust turbocharger
    47.
    发明授权
    Exhaust turbocharger 有权
    排气涡轮增压器

    公开(公告)号：US07343742B2

    公开(公告)日：2008-03-18

    申请号：US11209859

    申请日：2005-08-24

    Applicant: Rudolf Wimmer ,  Leopold Eistershofen

    Inventor： Rudolf Wimmer ,  Leopold Eistershofen

    IPC: F02B33/44 ,  F02M25/07 ,  F02M25/06 ,  F01D1/02 ,  F01D9/00

    CPC classification number: F02C3/34 ,  F01D9/026 ,  F02B29/0437 ,  F02M26/05 ,  F02M26/06 ,  F02M26/15 ,  F02M26/24 ,  F02M26/25 ,  F02M26/28 ,  F05D2220/40 ,  F05D2250/15 ,  F05D2250/25 ,  F05D2250/322 ,  Y02T10/146

    Abstract: An exhaust turbocharger with a housing, a compressor arranged in a compressor space and an exhaust turbine is arranged in a turbine space, whereby an exhaust line from the turbine outlet is connected to a low-pressure side of the compressor space via an exhaust recirculation line which extends through the housing and is designed largely in a spiral form in the housing. The recirculated exhaust gas flow arrangements improve the dynamics by providing higher turbocharger rotational speeds in the partial load range due to the production of a pre-twist by the exhaust recirculation stream.

    Abstract translation: 具有壳体的排气涡轮增压器，布置在压缩机空间中的压缩机和排气涡轮机布置在涡轮机空间中，由此来自涡轮机出口的排气管线经由排气再循环管线连接到压缩机空间的低压侧 其延伸穿过壳体并且主要以螺旋形式设计在壳体中。 由于由排气再循环流产生预扭转，通过在部分负载范围内提供更高的涡轮增压器转速来改善动力学。

    Composite integrally bladed rotor
    48.
    发明授权
    Composite integrally bladed rotor 有权
    复合一体叶片转子

    公开(公告)号：US07284957B2

    公开(公告)日：2007-10-23

    申请号：US11007503

    申请日：2004-12-08

    Applicant: David Charles Hornick ,  Frank J. Euvino, Jr. ,  James Tyler Roach

    Inventor： David Charles Hornick ,  Frank J. Euvino, Jr. ,  James Tyler Roach

    IPC: F04D5/24

    CPC classification number: F01D5/282 ,  F01D5/225 ,  F01D5/34 ,  F04D29/023 ,  F04D29/321 ,  F05D2250/15 ,  F05D2300/43 ,  F05D2300/603

    Abstract: The present invention relates to an integrally bladed rotor for use in a gas turbine engine. The integrally bladed rotor comprises a plurality of pairs of airfoil blades. Each pair of blades has a spar which extends from a first tip of a first one of the airfoil blades in the pair to a second tip of a second one of the airfoil blades in the pair. The rotor further comprises an outer shroud integrally joined to the first and second tips in each pair of airfoil blades and an inner diameter hub.

    Abstract translation: 本发明涉及一种用于燃气涡轮发动机的整体叶片转子。 整体叶片转子包括多对翼型叶片。 每对叶片具有翼形件，翼梁从一对翼型叶片的第一叶片的第一端部延伸到一对翼型叶片的第二叶片的第二端部。 转子还包括与每一对翼型叶片中的第一和第二尖端一体地连接的外护罩和内径毂。

    Propulsion system
    49.
    发明授权
    Propulsion system 失效
    推进系统

    公开(公告)号：US07229029B2

    公开(公告)日：2007-06-12

    申请号：US10677800

    申请日：2003-10-03

    Applicant: Oscar D. Windham

    Inventor： Oscar D. Windham

    IPC: B64D33/00 ,  B63H11/00 ,  F02K1/00

    CPC classification number: F02K1/00 ,  F05D2210/40 ,  F05D2250/15 ,  F05D2250/25

    Abstract: A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft. The propulsion system also contemplates a vehicle including the modified 3D spiral nozzle exhaust profile

    Abstract translation: 用于喷气式或火箭推进式车辆的推进系统，其中所得的喷射式排气喷嘴轮廓为3D螺旋。 推进系统可应用于任何喷气式或火箭推进式车辆，包括飞机和船只。 推进系统还考虑了包括改进的3D螺旋喷嘴排气轮廓的车辆

    Scroll casing for centrifugal blowers
    50.
    发明申请
    Scroll casing for centrifugal blowers 审中-公开
    滚筒式离心式鼓风机

    公开(公告)号：US20060165521A1

    公开(公告)日：2006-07-27

    申请号：US11170113

    申请日：2005-06-30

    Applicant: Jae-Won Kim

    Inventor： Jae-Won Kim

    IPC: F03B3/16

    CPC classification number: F04D29/422 ,  F01D9/026 ,  F05D2250/15

    Abstract: Disclosed herein is a scroll casing for centrifugal blowers provided outside of an impeller for forming a spiral air flow path, comprising: an outlet for discharging air; and a cut-off formed between the impeller and the outlet for serving as a boundary between an outlet air flow field and an internal air flow field wherein when a difference in pressure between an inlet and outlet of the centrifugal blower, indicated by a height of a water column, is designated by Δp (expressed in mm Aq), a water density is designated by ρ, a gravitational acceleration is designated by g, an outer diameter of the impeller is designated by D, and an angle of a circular arc defined from a position of the cut-off to a position where an expansion of the scroll casing ends is designated by θ (expressed in radians), an equation θ=(7π/4)−{(Δp)/(ρ g D)}×(π/180) is satisfied, thereby balancing the internal air flow and the outlet air flow even when a centrifugal blower is operated under high suction pressure condition, and thus, enhancing the performance of the centrifugal blower.

    Abstract translation: 本文公开了一种用于离心鼓风机的涡旋壳体，其设置在用于形成螺旋空气流路的叶轮的外侧，包括：用于排出空气的出口; 以及在叶轮和出口之间形成的用于在出口空气流场和内部空气流场之间的边界的切口，其中当离心式鼓风机的入口和出口之间的压力差由高度 水柱由Deltap（以mm Aq表示）表示，水密度由rho表示，重力加速度用g表示，叶轮的外径由D表示，圆弧的角度被定义 从截止位置到涡旋壳体的膨胀端部的位置由θ（以弧度表示）表示，方程θ=（7pi / 4） - {（Deltap）/（rho g D）} 即使在离心式鼓风机在高吸入压力条件下运转时，也能够平衡内部气流和出口空气流，从而提高离心式鼓风机的性能。

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