中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

72 records (took 0.012 seconds)

    Gas turbine engine with concave pocket with knife edge seal
    24.
    发明申请
    Gas turbine engine with concave pocket with knife edge seal 有权
    带凹口的燃气轮机，带刀口密封

    公开(公告)号：US20080124215A1

    公开(公告)日：2008-05-29

    申请号：US11605678

    申请日：2006-11-29

    Applicant: Roger E. Paolillo ,  Ioannis Alvanos ,  Cheng-Zhang Wang

    Inventor： Roger E. Paolillo ,  Ioannis Alvanos ,  Cheng-Zhang Wang

    IPC: F01D25/00

    CPC classification number: F01D11/001 ,  F01D11/02 ,  F05D2250/712

    Abstract: A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.

    Abstract translation: 燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。 每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。 凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。

    Fluid brush seal with segment seal land
    25.
    发明申请
    Fluid brush seal with segment seal land 审中-公开
    流体刷密封带段密封垫

    公开(公告)号：US20080095616A1

    公开(公告)日：2008-04-24

    申请号：US11584062

    申请日：2006-10-20

    Applicant: Ioannis Alvanos ,  John P. Virtue

    Inventor： Ioannis Alvanos ,  John P. Virtue

    IPC: F01D11/00

    CPC classification number: F01D11/001 ,  F01D5/3007 ,  F05D2240/56

    Abstract: A turbine rotor for a turbine engine includes multiple rotor disks having rotor blades mounted about the circumference of each of the rotor disks. A fluid seal extends about the circumference of each rotor disk in close proximity to a stationary component of the rotor to separate the space between the rotor blades and a stationary component into separate cavities. The fluid seal includes a seal land on the rotor disk and a brush seal extending from the stationary component. A plurality of disk land segments and a plurality of blade land segments form the seal land. The disk seal segments are located on the rotor disk between the rotor blades. The blade land segments are located on the rotor blades. After the rotor blades are assembled, the blade land segments and the disk land segments fit together to form a segmented ring-like seal land around the circumference of the rotor disk.

    Abstract translation: 用于涡轮发动机的涡轮转子包括具有安装在每个转子盘周围的转子叶片的多个转子盘。 流体密封件围绕每个转子盘的圆周延伸，靠近转子的固定部件，以将转子叶片和固定部件之间的空间分离成单独的空腔。 流体密封件包括转子盘上的密封区域和从静止部件延伸的刷子密封件。 多个盘片区段和多个刀片区域段形成密封区域。 圆盘密封段位于转子叶片之间的转子盘上。 刀片区段位于转子叶片上。 在组装转子叶片之后，刀片接合段和盘片区段装配在一起以在转子盘周围形成分段的环状密封环。

    Gas turbine engine cooling system
    26.
    发明授权
    Gas turbine engine cooling system 有权
    燃气轮机发动机冷却系统

    公开(公告)号：US09435259B2

    公开(公告)日：2016-09-06

    申请号：US13405527

    申请日：2012-02-27

    Applicant: Gabriel L. Suciu ,  Ioannis Alvanos

    Inventor： Gabriel L. Suciu ,  Ioannis Alvanos

    IPC: F02C6/08 ,  F01D5/08 ,  F02C7/08

    CPC classification number: F02C6/08 ,  F01D5/08 ,  F02C7/08

    Abstract: A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.

    Abstract translation: 燃气涡轮发动机包括热交换器，扩散器壳体，通道和喷嘴组件。 热交换器与放气气流交换热量以提供调节气流。 扩散器壳体包括容纳调节气流的增压室。 通道流体地连接在热交换器和扩散器壳体之间，并且经调节的气流通过通道连通并进入通风室。 喷嘴组件与扩散器壳体的气室流体连通以接收来自气室的经调节的气流。

    Gas turbine engine buffer cooling system
    28.
    发明授权
    Gas turbine engine buffer cooling system 有权
    燃气轮机发动机缓冲冷却系统

    公开(公告)号：US09038398B2

    公开(公告)日：2015-05-26

    申请号：US13405466

    申请日：2012-02-27

    Applicant: Gabriel L. Suciu ,  Ioannis Alvanos

    Inventor： Gabriel L. Suciu ,  Ioannis Alvanos

    IPC: F02C6/08 ,  F01D5/08 ,  F02C7/06 ,  F02C7/18

    CPC classification number: F02C7/185 ,  F01D5/081 ,  F01D25/125 ,  F02C6/08 ,  F02C7/06 ,  F05D2220/32 ,  F05D2260/232

    Abstract: A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.

    Abstract translation: 燃气涡轮发动机包括热交换器，轴承室和与轴承室流体连通的喷嘴组件。 热交换器与放气气流交换热量以提供调节气流。 轴承室与热交换器流体连通。 第一通道将经调节的气流从热交换器传递到轴承室。 第二通道将经调节的气流从轴承室传送到喷嘴组件。

Patent Agency Ranking