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    GAS TURBINE ENGINE CASE
    51.
    发明申请
    GAS TURBINE ENGINE CASE 有权
    气体涡轮发动机箱

    公开(公告)号：US20090180864A1

    公开(公告)日：2009-07-16

    申请号：US12013617

    申请日：2008-01-14

    Applicant: Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry

    Inventor： Ioannis Alvanos ,  Gabriel L. Suciu ,  Brian D. Merry

    IPC: F01D25/24 ,  B23P15/04

    CPC classification number: F01D25/24 ,  F01D25/243 ,  F01D25/246 ,  F05D2230/60 ,  Y02T50/671 ,  Y10T29/49826

    Abstract: A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.

    Abstract translation: 燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。 在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。

    Fluid injection system
    52.
    发明授权
    Fluid injection system 有权
    流体注射系统

    公开(公告)号：US07534088B1

    公开(公告)日：2009-05-19

    申请号：US11455882

    申请日：2006-06-19

    Applicant: Ioannis Alvanos ,  Joel H. Wagner

    Inventor： Ioannis Alvanos ,  Joel H. Wagner

    IPC: F01D5/08

    CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D11/005 ,  F05D2240/12 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2240/81 ,  F05D2250/314 ,  Y02T50/673 ,  Y02T50/676

    Abstract: In accordance with the present invention, there is provided a system for injecting a secondary fluid stream into a primary fluid stream with improved aerodynamic efficiency. The secondary fluid stream is injected into the primary fluid stream at a tangential angle and radial location that reduces both mixing and endwall losses. A platform borders the primary fluid stream and contains a trailing edge surface. A rail extends radially from the platform and one or more conduits enter the rail in a substantially radial direction. The conduits extend through the radial length of the rail, continue into the platform, and terminate at the trailing edge surface. The secondary fluid stream is conveyed by the conduits through the rail and the platform, to the trailing edge surface, for injecting into the primary fluid stream at an optimal angle and radial location.

    Abstract translation: 根据本发明，提供了一种用于将次流体流注入具有改善的空气动力学效率的主流体流中的系统。 次级流体流以切向角度和径向位置注入主流体流中，从而减少混合和端壁损耗。 平台与主流体流相邻并且包含后缘表面。 轨道从平台径向延伸，并且一个或多个管道在基本径向方向上进入轨道。 导管延伸穿过导轨的径向长度，继续进入平台，并终止在后缘表面。 第二流体流被导管通过导轨和平台输送到后缘表面，用于以最佳角度和径向位置注入主流体流。

    Integrated bladed fluid seal
    54.
    发明授权
    Integrated bladed fluid seal 有权
    集成叶片流体密封

    公开(公告)号：US07334983B2

    公开(公告)日：2008-02-26

    申请号：US11260357

    申请日：2005-10-27

    Applicant: Ioannis Alvanos ,  Rajendra Agrawal ,  Gregory E. Reinhardt

    Inventor： Ioannis Alvanos ,  Rajendra Agrawal ,  Gregory E. Reinhardt

    IPC: F01D11/02

    CPC classification number: F01D11/02 ,  F01D5/081 ,  F01D11/001 ,  F02C7/28 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

    Abstract translation: 公开了用于限制冷却空气泄漏并改善冷却空气对密封件的分配的燃气轮机叶片与叶片接口密封件的各种实施例。 因此，涡轮转子包含径向延伸和周向分布的叶片的第一和第二阶段。 阶段通过位于叶片的径向内侧的环形联接器彼此轴向分开，在它们之间形成室。 在叶片级之间插入叶片级。 叶片台包含一个面向径向内侧的平台。 环从第一和第二叶片台阶中的每一个朝向叶片台轴向突出。 环也可以从联接器径向伸向叶片台。 环与陆部径向配合，并一起形成叶片与叶片接口密封。 联接器包括用于将冷却的流体径向引入到腔室中以用于冷却密封件的孔。

    Integrated bladed fluid seal
    56.
    发明申请
    Integrated bladed fluid seal 有权
    集成叶片流体密封

    公开(公告)号：US20070098545A1

    公开(公告)日：2007-05-03

    申请号：US11260357

    申请日：2005-10-27

    Applicant: Ioannis Alvanos ,  Rajendra Agrawal ,  Gregory Reinhardt

    Inventor： Ioannis Alvanos ,  Rajendra Agrawal ,  Gregory Reinhardt

    IPC: F04D29/08

    CPC classification number: F01D11/02 ,  F01D5/081 ,  F01D11/001 ,  F02C7/28 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

    Abstract: Disclosed are various embodiments of a gas turbine blade to vane interface seal for restricting leakage of cooling air and improving the apportioning of the cooling air to the seal. Accordingly, a turbine rotor contains a first and a second stage of radially extending and circumferentially distributed blades. The stages are separated axially from one another by an annular coupling located radially inboard of the blades, forming a chamber therebetween. Interposed between the blade stages is a vane stage. The vane stage contains a land, facing radially inwardly. A ring projects axially from each of the first and second blade stages towards the vane stage. A ring may also project radially from the coupling towards the vane stage. The rings radially cooperate with the land and together form the blade to vane interface seal. The coupling contains an aperture for radially introducing a cooled fluid to the chamber for use in cooling the seal.

    Abstract translation: 公开了用于限制冷却空气泄漏并改善冷却空气对密封件的分配的燃气轮机叶片与叶片接口密封件的各种实施例。 因此，涡轮转子包含径向延伸和周向分布的叶片的第一和第二阶段。 阶段通过位于叶片的径向内侧的环形联接器彼此轴向分开，在它们之间形成室。 在叶片级之间插入叶片级。 叶片台包含一个面向径向内侧的平台。 环从第一和第二叶片台阶中的每一个朝向叶片台轴向突出。 环也可以从联接器径向伸向叶片台。 环与陆部径向配合，并一起形成叶片与叶片接口密封。 联接器包括用于将冷却的流体径向引入到腔室中以用于冷却密封件的孔。

    Cavity on-board injection for leakage flows
    57.
    发明申请
    Cavity on-board injection for leakage flows 有权
    腔内注入用于泄漏流

    公开(公告)号：US20050217277A1

    公开(公告)日：2005-10-06

    申请号：US10813520

    申请日：2004-03-30

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

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

    IPC: F01D5/08 ,  F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F02C7/12

    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。

    Gas turbine engine cooling system
    58.
    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
    60.
    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。

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