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    Swirling midframe flow for gas turbine engine having advanced transitions
    2.
    发明授权
    Swirling midframe flow for gas turbine engine having advanced transitions 有权
    具有高级过渡的燃气涡轮发动机的旋转中架流

    公开(公告)号：US09528706B2

    公开(公告)日：2016-12-27

    申请号：US14105313

    申请日：2013-12-13

    Applicant: Matthew D. Montgomery ,  Richard C. Charron ,  Jose L. Rodriguez ,  Bernhard W. Küsters ,  Jay A. Morrison ,  Alexander R. Beeck

    Inventor： Matthew D. Montgomery ,  Richard C. Charron ,  Jose L. Rodriguez ,  Bernhard W. Küsters ,  Jay A. Morrison ,  Alexander R. Beeck

    IPC: F23R3/46 ,  F04D29/54 ,  F23R3/02 ,  F23R3/04 ,  F23R3/42

    CPC classification number: F23R3/46 ,  F04D29/542 ,  F04D29/545 ,  F04D29/547 ,  F23R3/02 ,  F23R3/04 ,  F23R3/425

    Abstract: A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.

    Abstract translation: 一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22） 多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移 方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。

    Mid-section of a can-annular gas turbine engine with a cooling system for the transition
    3.
    发明授权
    Mid-section of a can-annular gas turbine engine with a cooling system for the transition 有权
    具有用于过渡的冷却系统的罐环式燃气涡轮发动机的中段

    公开(公告)号：US09206699B2

    公开(公告)日：2015-12-08

    申请号：US13408061

    申请日：2012-02-29

    Applicant: David J. Wiebe ,  Jose L. Rodriguez

    Inventor： David J. Wiebe ,  Jose L. Rodriguez

    IPC: F01D9/02 ,  F01D25/12 ,  F02C3/14 ,  F23R3/52 ,  F23R3/58

    CPC classification number: F01D9/023 ,  F01D25/12 ,  F02C3/14 ,  F05D2250/314 ,  F23R3/52 ,  F23R3/58

    Abstract: A cooling system is provided for a transition (420) of a gas turbine engine (410). The cooling system includes a cowling (460) configured to receive an air flow (111) from an outlet of a compressor section of the gas turbine engine (410). The cowling (460) is positioned adjacent to a region of the transition (420) to cool the transition region upon circulation of the air flow within the cowling (460). The cooling system further includes a manifold (121) to directly couple the air flow (111) from the compressor section outlet to an inlet (462) of the cowling (460). The cowling (460) is configured to circulate the air flow (111) within an interior space (426) of the cowling (460) that extends radially outward from an inner diameter (423) of the cowling to an outer diameter (424) of the cowling at an outer surface.

    Abstract translation: 为燃气涡轮发动机（410）的过渡（420）提供冷却系统。 冷却系统包括构造成从燃气涡轮发动机（410）的压缩机部分的出口接收空气流（111）的整流罩（460）。 整流罩（460）定位成邻近过渡区域（420），以在气流（460）内的空气流循环时冷却过渡区域。 冷却系统还包括将空气流（111）从压缩机部分出口直接联接到整流罩（460）的入口（462）的歧管（121）。 整流罩（460）构造成使得空气流（111）在整流罩（460）的内部空间（426）内循环，该整流罩（460）从整流罩的内径（423）径向向外延伸到外壳 在外表面的整流罩。

    MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE TO INTRODUCE A RADIAL VELOCITY COMPONENT INTO AN AIR FLOW DISCHARGED FROM A COMPRESSOR OF THE MID-SECTION
    4.
    发明申请
    MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE TO INTRODUCE A RADIAL VELOCITY COMPONENT INTO AN AIR FLOW DISCHARGED FROM A COMPRESSOR OF THE MID-SECTION 有权
    CAN-ANNULAR气体涡轮发动机的中间部分将辐射速度分量引入从中段压缩机排出的空气流中

    公开(公告)号：US20130224007A1

    公开(公告)日：2013-08-29

    申请号：US13407987

    申请日：2012-02-29

    Applicant: Jose L. Rodriguez

    Inventor： Jose L. Rodriguez

    IPC: F01D1/04

    CPC classification number: F01D9/041 ,  F02C3/14 ,  F04D29/44 ,  F04D29/54

    Abstract: A midframe portion (113) of a gas turbine engine (110) is provided, including a compressor section (112) with a last stage blade (124). The compressor section (112) is configured to introduce a radial velocity component into an air flow (111) such that the air flow is discharged from the compressor section (112) at a mixed direction based on a combined longitudinal velocity component and radial velocity component. The midframe portion (113) further includes a manifold (121) to directly couple the air flow from an outlet of the compressor section (112) to an inlet of a respective combustor head (118) of the gas turbine engine (110).

    Abstract translation: 提供了一种燃气涡轮发动机（110）的中架部分（113），包括具有最后级叶片（124）的压缩机部分（112）。 压缩机部分（112）构造成将径向速度分量引入到空气流（111）中，使得空气流基于组合的纵向速度分量和径向速度分量在混合方向从压缩机部分（112）排出 。 中间部分（113）还包括将来自压缩机部分（112）的出口的空气流直接联接到燃气涡轮发动机（110）的相应燃烧器头部（118）的入口的歧管（121）。

    Air bag
    5.
    发明授权
    Air bag 失效
    气袋

    公开(公告)号：US5549326A

    公开(公告)日：1996-08-27

    申请号：US457857

    申请日：1995-06-01

    Applicant: Jose L. Rodriguez Ramos

    Inventor： Jose L. Rodriguez Ramos

    IPC: B60R21/16 ,  B60R21/217 ,  B60R21/231

    CPC classification number: B60R21/231 ,  B60R21/2171

    Abstract: An air bag (10) is made from a single panel (40) of fabric material which is folded and sewn to define an inflation fluid volume. The panel (40) has a generally rectangular configuration. Two retainer portions (44, 46) of the panel (40) project from opposite ends of a main body portion (42) of the panel. The panel (40) is folded along a fold line (140) so that the retainer portions (44, 46) overlie one another, as do end portions (70, 72) of the panel. The retainer portions (44, 46) and end portions (70, 72) of the panel (40) are sewn together, and a retainer (180) is then sewn into the joined retainer portions.

    Abstract translation: 安全气囊（10）由织物材料的单个面板（40）制成，其被折叠和缝合以限定充气流体体积。 面板（40）具有大致矩形的构造。 面板（40）的两个保持器部分（44,46）从面板的主体部分（42）的相对端突出。 面板（40）沿着折线（140）折叠，使得保持器部分（44,46）彼此重叠，如同面板的端部（70,72）一样。 面板（40）的保持器部分（44,46）和端部（70,72）被缝合在一起，然后将保持器（180）缝合到连接的保持器部分中。

    Gas turbine compressor inlet with reduced flow distortion
    6.
    发明授权
    Gas turbine compressor inlet with reduced flow distortion 有权
    燃气轮机压缩机入口具有减少的流量失真

    公开(公告)号：US08894361B2

    公开(公告)日：2014-11-25

    申请号：US13221109

    申请日：2011-08-30

    Applicant: Jose L. Rodriguez ,  Joseph L. Evins

    Inventor： Jose L. Rodriguez ,  Joseph L. Evins

    IPC: F01D1/02 ,  F02C7/06 ,  F04D29/54 ,  F02C7/04

    CPC classification number: F04D29/541 ,  F02C7/04 ,  F02C7/06

    Abstract: A gas turbine engine compressor has a compressor case comprising spaced apart inner and outer walls. An axial rotor is positioned within the outer wall. A bearing structure supports the axial rotor for rotation. A plurality of inlet guide vanes are coupled to the outer wall of the compressor case and radially extend inwardly, wherein each of at least a sub-set of said inlet guide vanes comprises a radial bore. Nested tie rods are received within a respective one of the inlet guide vane radial bores. Each tie rod comprises an outward end attached to the compressor case outer wall and an inward end attached to the compressor case inner wall.

    Abstract translation: 燃气涡轮发动机压缩机具有包括间隔开的内壁和外壁的压缩机壳体。 轴向转子位于外壁内。 轴承结构支撑轴向转子旋转。 多个入口导向叶片联接到压缩机壳体的外壁并且向内径向延伸，其中所述入口导向叶片的至少一个子组中的每一个包括径向孔。 嵌套的拉杆容纳在相应的一个入口引导叶片径向孔内。 每个拉杆包括附接到压缩机壳体外壁的外端和附接到压缩机壳体内壁的内端。

    TURBINE CYLINDER CAVITY HEATED RECIRCULATION SYSTEM
    7.
    发明申请
    TURBINE CYLINDER CAVITY HEATED RECIRCULATION SYSTEM 审中-公开
    涡轮缸加热再循环系统

    公开(公告)号：US20140301834A1

    公开(公告)日：2014-10-09

    申请号：US13855886

    申请日：2013-04-03

    Applicant: Barton M. Pepperman ,  Yan Yin ,  Jose L. Rodriguez ,  Evan C. Landrum ,  Jiping Zhang

    Inventor： Barton M. Pepperman ,  Yan Yin ,  Jose L. Rodriguez ,  Evan C. Landrum ,  Jiping Zhang

    IPC: F01D25/10

    CPC classification number: F01D25/10 ,  F01D11/24 ,  F02C7/26 ,  F05D2260/20

    Abstract: A turbine engine heating system configured to heat compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine heating system may include a heating air extraction system configured to withdraw air from the turbine engine and to pass that air thru a heating element configured to increase a temperature of the air supplied by the heating air extraction system. The air may then be passed to a heating air supply system via an air movement device. The heating air supply system may be in communication with a turbine cylinder cavity of the turbine engine positioned radially outward from at least one turbine assembly. The heated air may be passed into the turbine cylinder cavity to reduce the cooling rate of the turbine vane carriers after shutdown and before a warm restart to limit tip rubbing.

    Abstract translation: 公开了一种涡轮发动机加热系统，其构造成加热压缩机和涡轮叶片组件以消除燃气涡轮发动机的热重启期间的涡轮机和压缩机叶片尖端摩擦。 涡轮发动机加热系统可以包括加热空气抽取系统，该系统构造成从涡轮发动机抽出空气，并使该空气通过构造成增加由加热空气抽取系统供应的空气的温度的加热元件。 然后可以经由空气移动装置将空气传送到加热空气供应系统。 加热空气供应系统可以与从至少一个涡轮机组件径向向外定位的涡轮发动机的涡轮机气缸腔连通。 加热的空气可以进入涡轮机气缸腔，以降低关闭后和热再启动之前的涡轮叶片载体的冷却速率，以限制末端摩擦。

    TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE
    8.
    发明申请
    TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE 有权
    在涡轮发动机的空气中的温度控制

    公开(公告)号：US20140119880A1

    公开(公告)日：2014-05-01

    申请号：US13663737

    申请日：2012-10-30

    Applicant: Jose L. Rodriguez ,  David A. Little ,  Jiping Zhang ,  Abdullatif M. Chehab

    Inventor： Jose L. Rodriguez ,  David A. Little ,  Jiping Zhang ,  Abdullatif M. Chehab

    IPC: F01D17/00 ,  F01D25/00

    CPC classification number: F01D9/065 ,  F01D25/162 ,  F02C7/18 ,  F05D2260/601

    Abstract: A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space.

    Abstract translation: 一种涡轮发动机，包括在涡轮发动机的外部和内部之间限定的中间空间。 提供了一种流动增压器，其包括位于中间空间内的流动体，并且包括入口端口，出口端口和在入口和出口之间的流体内延伸的流动通道。 入口端口接收位于中间空间内的第一介质流，并且流体将第二介质的通电流注入流体内的第一介质的一部分，以从出口产生混合介质的通电流 混合介质的通电流在中间空间内产生与流体相邻的第一介质的流动。

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