利索-全球专利检索

  1. 登录
  2. 注册

搜索结果

19 条记录 (耗时 0.023 秒)

    Method of operating adaptive core engines
    1.
    发明授权
    Method of operating adaptive core engines 有权
    运行自适应核心引擎的方法

    公开(公告)号：US08622687B2

    公开(公告)日：2014-01-07

    申请号：US12871073

    申请日：2010-08-30

    申请人： Rollin George Giffin ,  Brandon Flowers Powell ,  Mark Harrington ,  James Edward Johnson

    发明人： Rollin George Giffin ,  Brandon Flowers Powell ,  Mark Harrington ,  James Edward Johnson

    IPC分类号： F02K3/00

    CPC分类号： F02K3/075 ,  F05D2220/323

    摘要： A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation. The operation may be transitioned from the high-power mode to a low-power mode by opening a rear block stator such that the rear block compressor receives at least a portion of the fluid flowing from the front block compressor and maintains an overall engine pressure ratio.

    摘要翻译： 公开了一种在自适应核心引擎中操作压缩机的方法。 该方法包括以下步骤：在高功率模式操作中操作前部块压缩机以将流体的压力增加到第一压力比; 操作联接到前部块压缩机的后部块式压缩机，使得前部块式压缩机和后部块式压缩机以相同的物理速度运行; 关闭从后块式压缩机轴向向前定位的后块定子叶片，使得流入后块式压缩机的流体基本上被切断; 并且保持阻挡门打开，使得在大功率模式操作期间，由前块式压缩机加压的基本上所有的流体都流经旁路通道。 操作可以通过打开后挡块定子从大功率模式转换到低功率模式，使得后块式压缩机接收从前块式压缩机流出的流体的至少一部分，并保持总体发动机压力比 。

    High pressure ratio aft fan
    2.
    发明授权
    High pressure ratio aft fan 有权
    高压比后排风机

    公开(公告)号：US07631484B2

    公开(公告)日：2009-12-15

    申请号：US11308219

    申请日：2006-03-13

    申请人： Rollin George Giffin ,  James Edward Johnson

    发明人： Rollin George Giffin ,  James Edward Johnson

    IPC分类号： F02K3/02

    CPC分类号： F02K3/062 ,  F02C3/073 ,  F02C7/042 ,  F05D2240/80 ,  Y02T50/672

    摘要： A fan assembly for a gas turbine engine includes a turbine rotor adapted to be disposed aft of a core of the gas turbine engine; a row of turbine blades carried by the rotor, each turbine blade extending from the rotor to a tip, the turbine blades adapted to extract energy from a stream of pressurized combustion gases generated by the core; and at least two rows of axially-spaced apart, radially-extending fan blades carried by the row of turbine blades for rotation therewith.

    摘要翻译： 一种用于燃气涡轮发动机的风扇组件，包括适于设置在燃气涡轮发动机的核心的后方的涡轮转子; 由转子承载的一排涡轮叶片，每个涡轮叶片从转子延伸到尖端，涡轮机叶片适于从由芯产生的加压燃烧气体流中提取能量; 以及至少两排轴向间隔开的径向延伸的风扇叶片，所述风扇叶片由所述一排涡轮机叶片承载以与其一起旋转。

    Positive displacement rotary components having main and gate rotors with axial flow inlets and outlets
    5.
    发明授权
    Positive displacement rotary components having main and gate rotors with axial flow inlets and outlets 有权
    具有具有轴向流入口和出口的主转子和闸转子的正位移旋转部件

    公开(公告)号：US08328542B2

    公开(公告)日：2012-12-11

    申请号：US12347617

    申请日：2008-12-31

    申请人： Kurt David Murrow ,  Rollin George Giffin

    发明人： Kurt David Murrow ,  Rollin George Giffin

    IPC分类号： F03C2/00 ,  F03C4/00 ,  F04C18/00 ,  F04C2/00

    CPC分类号： F01C1/165 ,  F01C1/20 ,  F01C11/002 ,  F01C11/006 ,  F04C29/12 ,  F04C2240/20 ,  F04C2250/101 ,  F04C2250/102

    摘要： An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.

    摘要翻译： 诸如压缩机或涡轮机或膨胀机的轴向流量正位移燃气涡轮发动机部件包括从完全轴向流入口延伸到下游轴向间隔开的轴向流出口的转子组件。 转子组件包括主转子和分别围绕主转子和转子的主轴和闸门轴线旋转的一个或多个转子。 主和门转子具有相互啮合的主螺旋叶片和门螺旋叶片，其从环形主浇道和浇口轮毂径向向外延伸，分别围绕并围绕主轴和闸轴缠绕。 在轴向流入口中相交的主和门环形开口径向地在围绕转子组件的壳体和主和浇口毂之间延伸。 主螺旋叶片在入口过渡部分中沿下游方向从0转变为完全径向高度。

    POSITIVE DISPLACEMENT ROTARY COMPONENTS HAVING MAIN AND GATE ROTORS WITH AXIAL FLOW INLETS AND OUTLETS
    6.
    发明申请
    POSITIVE DISPLACEMENT ROTARY COMPONENTS HAVING MAIN AND GATE ROTORS WITH AXIAL FLOW INLETS AND OUTLETS 有权
    具有轴向流入口和出口的主门和门旋转器的正位移旋转部件

    公开(公告)号：US20100166591A1

    公开(公告)日：2010-07-01

    申请号：US12347617

    申请日：2008-12-31

    申请人： Kurt David Murrow ,  Rollin George Giffin

    发明人： Kurt David Murrow ,  Rollin George Giffin

    IPC分类号： F04C18/16

    CPC分类号： F01C1/165 ,  F01C1/20 ,  F01C11/002 ,  F01C11/006 ,  F04C29/12 ,  F04C2240/20 ,  F04C2250/101 ,  F04C2250/102

    摘要： An axial flow positive displacement gas turbine engine component such as a compressor or a turbine or an expander includes a rotor assembly extending from a fully axial flow inlet to a downstream axially spaced apart axial flow outlet. The rotor assembly includes a main rotor and one or more gate rotors rotatable about parallel main and gate axes of the main and gate rotors respectively. The main and gate rotors having intermeshed main and gate helical blades extending radially outwardly from annular main and gate hubs, circumscribed about, and wound about the main and gate axes respectively. Intersecting main and gate annular openings in the axial flow inlet extend radially between a casing surrounding the rotor assembly and the main and gate hubs. The main helical blades transition from 0 to a full radial height in a downstream direction in an inlet transition section.

    摘要翻译： 诸如压缩机或涡轮机或膨胀机的轴向流量正位移燃气涡轮发动机部件包括从完全轴向流入口延伸到下游轴向间隔开的轴向流出口的转子组件。 转子组件包括主转子和分别围绕主转子和转子的主轴和闸门轴线旋转的一个或多个转子。 主和门转子具有相互啮合的主螺旋叶片和门螺旋叶片，其从环形主浇道和浇口轮毂径向向外延伸，分别围绕并围绕主轴和闸轴缠绕。 在轴向流入口中相交的主和门环形开口径向地在围绕转子组件的壳体和主和浇口毂之间延伸。 主螺旋叶片在入口过渡部分中沿下游方向从0转变为完全径向高度。

    HYBRID WORM GAS TURBINE ENGINE
    7.
    发明申请
    HYBRID WORM GAS TURBINE ENGINE 有权
    混合动力气体涡轮发动机

    公开(公告)号：US20080273969A1

    公开(公告)日：2008-11-06

    申请号：US11742789

    申请日：2007-05-01

    申请人： Kurt David Murrow ,  Rollin George Giffin ,  Oladapo Fakunle

    发明人： Kurt David Murrow ,  Rollin George Giffin ,  Oladapo Fakunle

    IPC分类号： F03B3/00

    CPC分类号： F01C1/107 ,  F01C11/008 ,  F02C3/055 ,  F02K3/06 ,  F05D2250/25

    摘要： A gas turbine engine has components including a compressor, a combustor, and a turbine. At least one component is radially bladed having at least one row of radially extending rotatable blades and at least another is a worm component having an inner body disposed within an outer body. The inner and outer bodies have offset inner and outer axes, intermeshed inner and outer helical blades wound about the inner and outer axes respectively, and at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes. An aircraft gas turbine engine has components in serial downstream flow relationship including a fan, a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, and a low pressure turbine. At least one of the components is radially bladed and at least one of the components is a worm component.

    摘要翻译： 燃气涡轮发动机具有包括压缩机，燃烧器和涡轮机的部件。 至少一个部件是径向叶片的，具有至少一排径向延伸的可旋转叶片，并且至少另一个部件是具有设置在外部主体内部的内部主体的蜗杆部件。 内部和外部主体具有偏移的内部和外部轴线，分别围绕内部轴线和外部轴线缠绕的相互啮合的内部和外部螺旋叶片，并且内部主体和外部主体中的至少一个可围绕内部轴线和外部轴线中的相应一个旋转。 飞机燃气涡轮发动机具有串联下游流量关系的部件，包括风扇，低压压缩机，高压压缩机，燃烧器，高压涡轮机和低压涡轮机。 至少一个部件是径向叶片的，并且组件中的至少一个是蜗杆部件。

    Axial flow positive displacement worm gas generator
    10.
    发明授权
    Axial flow positive displacement worm gas generator 有权
    轴流式正位移蜗轮气体发生器

    公开(公告)号：US07707815B2

    公开(公告)日：2010-05-04

    申请号：US11313146

    申请日：2005-12-19

    申请人： Kurt David Murrow ,  Rollin George Giffin ,  Oladapo Fakunle

    发明人： Kurt David Murrow ,  Rollin George Giffin ,  Oladapo Fakunle

    IPC分类号： F02C3/02

    CPC分类号： F01C1/107 ,  F01C1/084 ,  F01C11/008 ,  F02B53/00 ,  F02C5/06 ,  F02K5/00 ,  F03C2/08 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2250/25

    摘要： An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. The first twist slopes are less than the second twist slopes and the third twist slopes are less than the second twist slopes. A combustor section extends axially downstream through at least a portion of the second section.

    摘要翻译： 轴流容积式发动机具有在出口处轴向间隔开和上游的入口。 内部和外部主体具有偏移的内部和外部轴线从入口到出口通过串联下游流动关系的芯组件的第一，第二和第三部分延伸。 至少一个主体可围绕其轴线旋转。 内外体分别围绕内轴和外轴缠绕内螺旋叶片和外螺旋叶片。 内螺旋叶片和外螺旋叶片分别径向向外和向内延伸。 螺旋叶片分别在第一，第二和第三部分具有第一，第二和第三扭曲斜面。 第一扭转斜面小于第二扭转斜面，第三扭转斜面小于第二扭转斜面。 燃烧器部分沿着第二部分的至少一部分轴向向下延伸。