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    SYSTEMS, METHODS AND APPARATUS FOR PROPULSION
    2.
    发明申请
    SYSTEMS, METHODS AND APPARATUS FOR PROPULSION 失效
    系统，方法和装置

    公开(公告)号：US20080134667A1

    公开(公告)日：2008-06-12

    申请号：US11782631

    申请日：2007-07-24

    Applicant: Thomas Clayton Pavia ,  James Robert Grote

    Inventor： Thomas Clayton Pavia ,  James Robert Grote

    IPC: F02K9/97

    CPC classification number: F02K9/64 ,  F02K9/972 ,  F02K9/974 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2300/121 ,  F05D2300/171 ,  F05D2300/1721 ,  F05D2300/1723

    Abstract: In some embodiments a propulsion system includes a thrust chamber having an inside wall, an expansion nozzle mounted to the thrust chamber and having an interior and having an exterior, a main propellant injector mounted to the thrust chamber to inject a fluid in the interior of the thrust chamber, the fluid comprising oxidizer, fuel and internal film coolant, the internal film coolant ranging from about 1% to about 5% of the fluid, limited coolant tubing circumscribing the exterior of the expansion nozzle to circulate an external coolant, and an injector mounted to the expansion nozzle to inject the external coolant in the interior of the expansion nozzle, the external convective coolant about 2.5% of the fluid. The system operates at lower temperatures while having conventional amounts of thrust, in which the thrust chamber can be made of thin walls of lower cost conventional metals with simple coolant tube construction.

    Abstract translation: 在一些实施例中，推进系统包括具有内壁的推力室，安装到推力室的膨胀喷嘴，并且具有内部并具有外部，主推进剂喷射器安装到推进室以将流体注入到内部 推进室，包括氧化剂，燃料和内部薄膜冷却剂的流体，内部薄膜冷却剂的范围为流体的约1％至约5％，限制膨胀喷嘴外部的限制冷却液管以使外部冷却剂循环，以及喷射器 安装到膨胀喷嘴以将外部冷却剂注入膨胀喷嘴的内部，外部对流冷却剂约为流体的2.5％。 该系统在较低温度下工作，同时具有常规的推力，其中推力室可由具有简单冷却剂管构造的较低成本常规金属的薄壁制成。

    Sealing arrangement
    3.
    发明申请
    Sealing arrangement 有权
    密封安排

    公开(公告)号：US20040150164A1

    公开(公告)日：2004-08-05

    申请号：US10693524

    申请日：2003-10-27

    Applicant: ROLLS ROYCE PLC

    Inventor： Jonathan J. Morgan

    IPC: F16J009/00

    CPC classification number: F01D11/001 ,  F01D11/02 ,  F04D29/023 ,  F04D29/083 ,  F05D2240/55 ,  F05D2300/1721 ,  F05D2300/1723 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2283 ,  F16J15/442 ,  F16J15/443

    Abstract: A sealing arrangement for sealing a leakage gap between relatively moveable parts in a flow path between a region of high-fluid pressure and a region of low fluid pressure comprises a sealing member having an upstream surface, a downstream surface, a radially outer surface and a radially inner surface, said sealing member being in communication with a housing via resilient means. The resilient means is fixedly joined to the upstream surface of the sealing member such that during operation both the radial force induced on the sealing member by fluid flowing axially into and circumferentially over the radially inner surface and the axial force induced on the sealing member because of a pressure difference across the sealing member is resisted by the resilient means.

    Abstract translation: 用于密封高流体压力区域和低流体压力区域之间的流动路径中相对移动部件之间的泄漏间隙的密封装置包括具有上游表面，下游表面，径向外表面和 径向内表面，所述密封构件通过弹性装置与壳体连通。 弹性装置固定地连接到密封构件的上游表面，使得在操作期间，通过流体轴向地流入径向内表面并周向地在径向内表面上引起的径向力和在密封构件上引起的轴向力，由于 通过弹性装置抵抗密封构件两端的压力差。

    COMPONENT, GAS TURBINE COMPONENT AND METHOD OF FORMING
    5.
    发明申请
    COMPONENT, GAS TURBINE COMPONENT AND METHOD OF FORMING 审中-公开
    组件，气体涡轮组件和形成方法

    公开(公告)号：US20160341127A1

    公开(公告)日：2016-11-24

    申请号：US14717074

    申请日：2015-05-20

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Dechao LIN ,  Srikanth Chandrudu KOTTILINGAM ,  Xiaoxue DIAO ,  Nicholas THOMAS

    IPC: F02C7/22

    CPC classification number: F02C7/222 ,  F05D2230/50 ,  F05D2230/90 ,  F05D2260/95 ,  F05D2300/1723

    Abstract: Components are disclosed which include a first component section and a second component section joined to form a hollow structure defining a plenum having an interior surface, wherein the component sections each include mating ridges joined together along the length of the plenum, and a corrosion-resistant cladding layer including a corrosion-resistant material overlaying the interior surface of the plenum. In one embodiment, the component is a gas turbine combustor fuel manifold. A method of forming the components includes applying corrosion-resistant segments including a corrosion-resistant material to each of the surfaces of the component sections, and joining the component sections to form the component, wherein joining the component sections includes fusing the corrosion-resistant segments into the corrosion-resistant cladding layer, and joining the mating ridges of the component sections.

    Abstract translation: 公开了包括第一部件部分和第二部件部分的部件，所述第一部件部分和第二部件部分连接以形成限定具有内表面的集气室的中空结构，其中所述部件部分各自包括沿着所述集气室的长度连接在一起的配合脊，以及耐腐蚀 包覆层包括覆盖在增压室内表面的耐腐蚀材料。 在一个实施例中，部件是燃气轮机燃烧器燃料歧管。 形成部件的方法包括将包括耐腐蚀材料的耐腐蚀部分施加到部件部分的每个表面，以及将部件部分接合以形成部件，其中连接部件部分包括使耐腐蚀部分 进入耐腐蚀包覆层，并且连接各部件的配合脊。

    SYSTEMS, METHODS AND APPARATUS FOR PROPULSION
    7.
    发明申请
    SYSTEMS, METHODS AND APPARATUS FOR PROPULSION 审中-公开
    系统，方法和装置

    公开(公告)号：US20120060464A1

    公开(公告)日：2012-03-15

    申请号：US12472371

    申请日：2009-05-26

    Applicant: James Robert Grote ,  Thomas Clayton Pavia

    Inventor： James Robert Grote ,  Thomas Clayton Pavia

    IPC: F02K9/64

    CPC classification number: F02K9/64 ,  F02K9/972 ,  F02K9/974 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2300/121 ,  F05D2300/171 ,  F05D2300/1721 ,  F05D2300/1723

    Abstract: In some implementations a propulsion system includes a thrust chamber comprised of a combustion chamber and an expansion nozzle. The thrust chamber has an interior and exterior surfaces and a main propellant injector mounted to the thrust chamber to inject an oxidizer and a fuel into the interior of the thrust chamber. The total fluid flowing to the rocket engine is compromised of oxidizer, fuel, internal film coolant, and external convective coolant. The internal film coolant ranges from about 1% to about 10% of the total fluid. Reduced coolant tubing circumscribes the exterior of the thrust chamber to circulate an external convective coolant, and a nozzle film coolant manifold mounted to the expansion nozzle injects the external convective coolant onto the interior wall of the expansion nozzle, the external convective coolant being about 1% to about 10% of the total fluid flow to the thrust chamber.

    Abstract translation: 在一些实施方式中，推进系统包括由燃烧室和膨胀喷嘴构成的推力室。 推力室具有内部和外部表面以及安装在推力室上的主推进剂喷射器，以将氧化剂和燃料喷射到推力室的内部。 流入火箭发动机的总流体受到氧化剂，燃料，内膜冷却剂和外部对流冷却剂的影响。 内部膜冷却剂的范围为总流体的约1％至约10％。 减少的冷却剂管道围绕推力室的外部以循环外部对流冷却剂，并且安装到膨胀喷嘴的喷嘴膜冷却剂歧管将外部对流冷却剂喷射到膨胀喷嘴的内壁上，外部对流冷却剂为约1％ 到达推力室的总流体流量的约10％。

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