中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

72 records (took 0.023 seconds)

    TURBINE COOLANT SUPPLY SYSTEM
    34.
    发明申请
    TURBINE COOLANT SUPPLY SYSTEM 有权
    涡轮冷却液供应系统

    公开(公告)号：US20130323010A1

    公开(公告)日：2013-12-05

    申请号：US13485579

    申请日：2012-05-31

    Applicant: John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    Inventor： John H. Mosley ,  Ioannis Alvanos ,  Phililp S. Stripinis ,  Douglas Paul Freiberg ,  Hector M. Pinero ,  John J. O'Connor ,  Jon Pietrobon

    IPC: F01D5/18

    CPC classification number: F01D5/082 ,  F01D25/12

    Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.

    Abstract translation: 构造成围绕延伸穿过燃气涡轮发动机的中心的轴线在圆周方向上旋转的燃气涡轮发动机包括涡轮级。 涡轮级包括盘，多个叶片和小型盘。 盘包括具有槽的外径边缘，围绕轴线的内径孔，前表面和后表面。 多个叶片耦合到槽。 微型盘联接到转子的后表面以在其间限定冷却室，以便将冷却空气引导到狭槽。 在本发明的一个实施例中，冷却气室通过所有旋转部件连接到径向内部的压缩机排放空气入口，使得冷却空气抵靠内径孔。

    BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING
    35.
    发明申请
    BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING 有权
    缓冲器冷却系统提供气体涡轮发动机结构冷却

    公开(公告)号：US20130219918A1

    公开(公告)日：2013-08-29

    申请号：US13405502

    申请日：2012-02-27

    Applicant: Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    Inventor： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    IPC: F02C6/08 ,  F02C3/00

    CPC classification number: F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

    Abstract: A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.

    Abstract translation: 燃气涡轮发动机包括具有第一热交换器，第一通道，第二通道和第三通道的缓冲冷却系统。 第一热交换器与放气气流交换热量以提供调节气流。 第一通道将调节气流的第一部分与燃气涡轮发动机的高压压缩机连通，第二通道将调节气流的第二部分连通到燃气涡轮发动机的高压涡轮机，并且第三通道 调节气流的第三部分到燃气涡轮发动机的低压涡轮机。

    Turbine cooling air sealing
    36.
    发明授权
    Turbine cooling air sealing 有权
    涡轮冷却空气密封

    公开(公告)号：US08517666B2

    公开(公告)日：2013-08-27

    申请号：US11224613

    申请日：2005-09-12

    Applicant: Ioannis Alvanos ,  Rajendra K. Agrawal ,  Hector M. Pinero

    Inventor： Ioannis Alvanos ,  Rajendra K. Agrawal ,  Hector M. Pinero

    IPC: F01D5/08 ,  F01D5/18

    CPC classification number: F01D5/081 ,  F01D11/001 ,  F01D25/12 ,  F02C7/18 ,  F02C7/28

    Abstract: A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing system restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing system restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing system and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.

    Abstract translation: 涡轮发动机部分具有静止叶片台和旋转叶片台。 叶片台与叶片台间隔开以在它们之间形成环形室。 歧管将加压流体输送到腔室。 外径（OD）密封系统限制加压流体从腔室泄漏。 内径（ID）密封系统限制加压流体从腔室泄漏。 流动引导件在内径密封系统和歧管之间径向延伸。 流动导向装置将室平分成一个固定室部分和一个旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。

    Bearing mounting system in a low pressure turbine
    39.
    发明申请
    Bearing mounting system in a low pressure turbine 有权
    轴承安装系统在低压涡轮机

    公开(公告)号：US20090148271A1

    公开(公告)日：2009-06-11

    申请号：US12001130

    申请日：2007-12-10

    Applicant: Ioannis Alvanos ,  Gabriel L. Suciu

    Inventor： Ioannis Alvanos ,  Gabriel L. Suciu

    IPC: F02C7/06

    CPC classification number: F02C7/06 ,  F01D25/16 ,  F05D2220/321 ,  Y02T50/671

    Abstract: A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.

    Abstract translation: 用于具有通过支撑转子支撑在低压轴上的低压涡轮机的燃气涡轮发动机的轴承安装系统包括低压涡轮壳体，前轴承和后轴承以及前支撑结构和后支撑件 结构体。 低压涡轮机壳体围绕低压涡轮机。 前轴承和后轴承定位在低压轴上以跨越支撑转子。 前支撑结构和后支撑结构分别将前轴承和后轴承分别连接到低压涡轮箱。 低压轴在前轴承和后轴承之间轴向延伸。 在一个实施例中，涡轮机包括多个相邻的转子盘，并且支撑转子包括将转子盘中的一个与轴连接的圆锥形支撑件。

    Cavity on-board injection for leakage flows
    40.
    发明授权
    Cavity on-board injection for leakage flows 有权
    腔内注入用于泄漏流

    公开(公告)号：US07114339B2

    公开(公告)日：2006-10-03

    申请号：US10813520

    申请日：2004-03-30

    Applicant: Ioannis Alvanos ,  Rajendra Agrawal ,  Hector M. Pinero ,  Jin Hu

    Inventor： Ioannis Alvanos ,  Rajendra Agrawal ,  Hector M. Pinero ,  Jin Hu

    IPC: F02C7/12 ,  F01D11/00

    CPC classification number: F01D25/12 ,  F01D5/081 ,  F02C7/18 ,  F05D2240/81 ,  F05D2260/60 ,  F05D2260/6022 ,  Y02T50/676

    Abstract: A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.

    Abstract translation: 公开了一种具有涡轮部分冷却系统的燃气涡轮发动机，其能够将燃气涡轮发动机的涡轮部分冷却到最佳工作温度范围，同时基本上不降低发动机性能。 本公开提供了许多不同的结构，包括在二次空气流动空腔内提供转动箔，转动孔和转动槽，其将冷却和寄生的泄漏空气转向或引导到与涡轮部分基本对准的方向 通过涡轮机部分的气体流动路径。

Patent Agency Ranking