知搜-全球专利检索

  1. Login
  2. Sign Up

Search Results

135 records (took 0.019 seconds)

    PROPULSION SYSTEM AND METHODS OF USE THEREOF
    41.
    发明申请
    PROPULSION SYSTEM AND METHODS OF USE THEREOF 审中-公开

    公开(公告)号：US20170129617A1

    公开(公告)日：2017-05-11

    申请号：US14935814

    申请日：2015-11-09

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Manoj Ramprasad Shah ,  Narendra Digamber Joshi

    IPC: B64D27/24 ,  B64C11/00

    Abstract: Embodiments of a propulsion system are provided herein. In some embodiments, a propulsion system for an aircraft may include an electrical power supply; a motor coupled to the electrical power supply, wherein the electrical power supply provides power to the motor; and a fan disposed proximate a rear portion of an aircraft and rotatably coupled to the motor, wherein the fan is driven by the motor.

    ULTRA COMPACT COMBUSTOR
    43.
    发明申请
    ULTRA COMPACT COMBUSTOR 审中-公开
    超紧凑型COMBUSTOR

    公开(公告)号：US20150323184A1

    公开(公告)日：2015-11-12

    申请号：US14706679

    申请日：2015-05-07

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Venkat Eswarlu Tangirala ,  Narendra Digamber Joshi

    IPC: F23R3/00 ,  F04D29/54 ,  F23R3/44 ,  F23R3/12 ,  F23R3/34

    CPC classification number: F02C3/14 ,  F01D9/023 ,  F04D27/0246 ,  F04D29/542 ,  F04D29/544 ,  F04D29/563 ,  F05D2240/35 ,  F23R3/002 ,  F23R3/04 ,  F23R3/12 ,  F23R3/26 ,  F23R3/28 ,  F23R3/34 ,  F23R3/44 ,  F23R3/50

    Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.

    Abstract translation: 本文提供了一种用于燃气涡轮发动机的燃烧器的实施例。 在一些实施例中，用于燃气涡轮发动机的燃烧室可以包括具有至少部分地由前壁限定的内部容积的燃烧器，其中所述壁包括多个小面，每个小面具有流体连接到内部体积的通孔， 并且其中所述多个小面被定向成使得所述多个小面中的每一个的轴线偏离所述燃烧器的中心轴线一个角度。

    TUNED CAVITY ROTATING DETONATION COMBUSTION SYSTEM
    44.
    发明申请
    TUNED CAVITY ROTATING DETONATION COMBUSTION SYSTEM 有权
    调谐孔旋转爆轰燃烧系统

    公开(公告)号：US20150167544A1

    公开(公告)日：2015-06-18

    申请号：US14103928

    申请日：2013-12-12

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Narendra Digamber Joshi ,  Michael Solomon Idelchik

    IPC: F02B53/04

    CPC classification number: F02B53/04 ,  F23R7/00

    Abstract: A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.

    Abstract translation: 调谐腔旋转爆震燃烧系统包括具有入口和出口的环形室; 在所述环形室的入口处的阀板，并且包括围绕所述入口周向间隔开的多个开口; 多个管，其各自具有与所述阀板的对应开口连通的开口端，以及形成调谐空腔的封闭端，以及用于喷射空气的所述开口端和所述封闭端之间的第一开口; 以及对应于所述多个管的多个燃料喷射器，每个燃料喷射器构造成在所述第一开口和所述开放端之间将燃料喷射到所述管中。 调谐空腔中的每一个具有尺寸设定成与环形室中至少一个爆震波的连续爆震频率相同的频率的长度。 替代地或另外地，对应于多个管的多个阻火器被配置为阻止在引爆室中产生的至少一个爆震波行进到管中。

    GAS TURBINE ENGINE SYSTEM AND AN ASSOCIATED METHOD THEREOF
    45.
    发明申请
    GAS TURBINE ENGINE SYSTEM AND AN ASSOCIATED METHOD THEREOF 有权
    气体涡轮发动机系统及其相关方法

    公开(公告)号：US20140352321A1

    公开(公告)日：2014-12-04

    申请号：US13691017

    申请日：2012-11-30

    Applicant: General Electric Company

    Inventor： Joel Meier Haynes ,  Narendra Digamber Joshi ,  Huijuan Chen

    IPC: F23R3/34 ,  F02K3/00

    CPC classification number: F23R3/346 ,  F01D9/023 ,  F02K3/00 ,  F23R3/286 ,  F23R3/34 ,  F23R3/46

    Abstract: A gas turbine engine system includes a compressor, a combustor, and a turbine. The combustor is coupled to the compressor and disposed downstream of the compressor. The combustor includes a secondary combustor section coupled to a primary combustor section and disposed downstream of the primary combustor section. The combustor also includes a transition nozzle coupled to the secondary combustor section and disposed downstream of the secondary combustor section. The combustor further includes an injector coupled to the secondary combustor section, for injecting an air-fuel mixture to the secondary combustor section. The turbine is coupled to the combustor and disposed downstream of the transition nozzle; wherein the transition nozzle is oriented substantially tangential to the turbine.

    Abstract translation: 燃气涡轮发动机系统包括压缩机，燃烧器和涡轮机。 燃烧器联接到压缩机并设置在压缩机的下游。 燃烧器包括联接到主燃烧器部分并且设置在主燃烧器部分的下游的次级燃烧器部分。 燃烧器还包括连接到次级燃烧器部分并设置在次级燃烧器部分的下游的过渡喷嘴。 燃烧器还包括联接到次级燃烧器部分的喷射器，用于将空气 - 燃料混合物喷射到次级燃烧器部分。 涡轮联接到燃烧器并设置在过渡喷嘴的下游; 其中所述过渡喷嘴基本上与所述涡轮相切。

Patent Agency Ranking