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    Buffer cooling system providing gas turbine engine architecture cooling
    32.
    发明授权
    Buffer cooling system providing gas turbine engine architecture cooling 有权
    缓冲冷却系统提供燃气轮机发动机架构冷却

    公开(公告)号：US09157325B2

    公开(公告)日：2015-10-13

    申请号：US13405502

    申请日：2012-02-27

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

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

    CPC分类号： F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

    摘要： 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.

    摘要翻译： 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。

    Bearing mounting system in a low pressure turbine
    34.
    发明授权
    Bearing mounting system in a low pressure turbine 有权

    公开(公告)号：US08511986B2

    公开(公告)日：2013-08-20

    申请号：US12001130

    申请日：2007-12-10

    申请人： Ioannis Alvanos ,  Gabriel L. Suciu

    发明人： Ioannis Alvanos ,  Gabriel L. Suciu

    IPC分类号： F04D29/04

    CPC分类号： F02C7/06 ,  F01D25/16 ,  F05D2220/321 ,  Y02T50/671

    摘要： 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.

    Gas turbine engine buffer cooling system
    36.
    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：US09347374B2

    公开(公告)日：2016-05-24

    申请号：US13405514

    申请日：2012-02-27

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos

    IPC分类号： F02C6/08 ,  F01D5/08 ,  F01D9/06 ,  F02C7/18

    CPC分类号： F02C6/08 ,  F01D5/081 ,  F01D9/065 ,  F02C7/18 ,  F02C7/185 ,  F05B2260/205 ,  Y02T50/676

    摘要： A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.

    摘要翻译： 燃气涡轮发动机包括热交换器，中涡轮机架，延伸穿过中涡轮机框架的至少一部分的通道和第一喷嘴组件。 热交换器与放气气流交换热量以提供调节气流。 中涡轮机架与热交换器流体连通。 调节气流通过通道连通并被第一喷嘴组件接收以调节燃气涡轮发动机硬件。

    Turbomachinery seal
    37.
    发明授权
    Turbomachinery seal 有权
    涡轮机械密封

    公开(公告)号：US09109458B2

    公开(公告)日：2015-08-18

    申请号：US13294787

    申请日：2011-11-11

    申请人： Ioannis Alvanos ,  Gabriel L. Suciu

    发明人： Ioannis Alvanos ,  Gabriel L. Suciu

    IPC分类号： F01D11/00 ,  F01D11/12

    CPC分类号： F01D11/001 ,  F01D11/122 ,  F01D11/127 ,  F05D2230/64 ,  F05D2250/184 ,  F05D2260/38

    摘要： A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor.

    摘要翻译： 用于将旋转机械的转子密封到其定子上的用于将转子环绕并通过间隙分离的密封件包括：非旋转密封元件，其接收在定子的环形槽内并且可相对于其径向平移并延伸到间隙 用于密封转子承载的旋转密封元件。 容纳在非旋转密封元件和狭槽的底板之间的弹性偏置元件将非旋转密封元件径向向内朝向旋转密封元件偏压并且限制非旋转密封元件的径向向外移动。 从狭槽延伸到所述间隙中的引导件接合非旋转密封元件以防止其与机器转子的轴向不对准。

    BUFFER COOLING SYSTEM PROVIDING GAS TURBINE ENGINE ARCHITECTURE COOLING
    39.
    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

    申请人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Camelia Galos

    IPC分类号： F02C6/08 ,  F02C3/00

    CPC分类号： F01D5/081 ,  F02C6/08 ,  F02C7/06 ,  F02C7/185

    摘要： 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.

    摘要翻译： 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。

    Bearing mounting system in a low pressure turbine
    40.
    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

    申请人： Ioannis Alvanos ,  Gabriel L. Suciu

    发明人： Ioannis Alvanos ,  Gabriel L. Suciu

    IPC分类号： F02C7/06

    CPC分类号： F02C7/06 ,  F01D25/16 ,  F05D2220/321 ,  Y02T50/671

    摘要： 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.

    摘要翻译： 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。