知搜-全球专利检索

  1. 登录
  2. 注册

搜索结果

28 条记录 (耗时 0.015 秒)

    Combustor flame stabilizing structure
    1.
    发明授权
    Combustor flame stabilizing structure 失效
    燃烧器火焰稳定结构

    公开(公告)号：US5857339A

    公开(公告)日：1999-01-12

    申请号：US447518

    申请日：1995-05-23

    申请人： William M. Roquemore ,  Dale T. Shouse ,  Kuang-Yu M. Hsu

    发明人： William M. Roquemore ,  Dale T. Shouse ,  Kuang-Yu M. Hsu

    IPC分类号： F23R3/20 ,  F23R3/24 ,  F02C1/00

    CPC分类号： F23R3/20 ,  F23R3/24

    摘要： A combustor structure is described which comprises a cavity defined in the combustor for trapping a vortex of fuel, air and hot combustion products to stabilize the flame, the cavity being formed in any suitable way such as being defined between two or more bluff bodies in tandem, or in a wall of the combustor, or in the combustor liner, and wherein fuel and air are injected directly into the fuel/air recirculation zone defined by the trapped vortex.

    摘要翻译： 描述了一种燃烧器结构，其包括限定在燃烧器中的空腔，用于捕获燃料涡流，空气和热燃烧产物以稳定火焰，空腔以任何合适的方式形成，例如串联在两个或多个非流线体之间 ，或在燃烧器的壁中，或在燃烧器衬套中，并且其中燃料和空气被直接注入由被捕获的涡流限定的燃料/空气再循环区域中。

    Combustion apparatus
    3.
    发明授权
    Combustion apparatus 失效
    燃烧装置

    公开(公告)号：US4048797A

    公开(公告)日：1977-09-20

    申请号：US638106

    申请日：1975-12-05

    申请人： John Philip Dabbs Hakluytt ,  John Ronald Tilston

    发明人： John Philip Dabbs Hakluytt ,  John Ronald Tilston

    IPC分类号： F23R3/24 ,  F02G1/00

    CPC分类号： F23R3/24

    摘要： The present invention provides gas turbine reheat combustion apparatus for aircraft propulsion. The apparatus includes means for producing a flame stabilization zone in a stream of combustion supporting gas flowing in a duct, said stabilization zone having a recirculatory flow region therein, an injector for introducing a fluid comprising an inert diluent such as, for example, nitrogen, into the recirculatory flow region, and means for supplying the fluid to the injector.

    摘要翻译： 本发明提供了用于飞行器推进的燃气轮机再热燃烧装置。 该装置包括用于在燃烧支持气流中产生火焰稳定区的装置，所述燃烧流在管道中流动，所述稳定区在其中具有再循环流动区域，用于引入包含惰性稀释剂例如氮气的流体的注射器， 进入再循环流动区域，以及用于将流体供应到喷射器的装置。

    Combustion chamber of a gas turbine with a ring-shaped head section
    8.
    发明授权
    Combustion chamber of a gas turbine with a ring-shaped head section 失效
    具有环形头部的燃气轮机的燃烧室

    公开(公告)号：US5934066A

    公开(公告)日：1999-08-10

    申请号：US948056

    申请日：1997-10-09

    申请人： Achim Schmid ,  Manfred Schwithal

    发明人： Achim Schmid ,  Manfred Schwithal

    IPC分类号： F23R3/00 ,  F23R3/10 ,  F23R3/24

    CPC分类号： F23R3/10 ,  F23R3/002

    摘要： A combustion chamber of a gas turbine with a ring-shaped head section, in which a front plate for receiving burners is provided, which are supplied with a primary airflow via annularly arranged air inlet openings in the head section, wherein the stagnation points being formed on the exterior of the head section (1) in respect to the inflow to the air inlet openings form a ring, within which the air inlet openings are located, and wherein furthermore the front plate has heat shields provided in the combustion chamber burner section and fixed in place by means of bolt connections. In addition, mounting openings for the bolt connections (11) are provided in the head section, wherein the backup points being formed on the exterior of the head section in respect to the inflow to the mounting openings form a ring, which is not located outside the ring formed by the backup points of the air inlet openings.

    摘要翻译： 一种具有环形头部的燃气轮机的燃烧室，其中设置有用于接收燃烧器的前板，其中，所述前板用于接收燃烧器，所述前板用于在所述头部部分中经由环形布置的空气入口开口提供主气流，其中形成所述停滞点 在头部部分（1）的相对于进入空气入口的流入的外部形成环，空气入口开口位于该环中，此外，前板具有设置在燃烧室燃烧器部分中的隔热罩， 通过螺栓连接固定到位。 此外，头部部分设置有用于螺栓连接部（11）的安装开口，其中相对于安装开口的流入而形成在头部部分的外部上的支撑点形成不位于外部的环 该环由进气孔的备份点形成。