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公开(公告)号：US20130108466A1
公开(公告)日：2013-05-02
申请号：US13283710
申请日：2011-10-28
Applicant: Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
Inventor： Gabriel L. Suciu , Stephen P. Muron , Christopher M. Dye , Ioannis Alvanos , Brian D. Merry
CPC classification number: F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
Abstract: A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
Abstract translation: 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
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公开(公告)号：US20130108445A1
公开(公告)日：2013-05-02
申请号：US13283689
申请日：2011-10-28
Applicant: Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
Inventor： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
Abstract: A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
Abstract translation: 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，所述多个叶片中的每一个叶片在接合处从转子盘延伸，所述界面沿辐条限定。
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公开(公告)号：US20130000324A1
公开(公告)日：2013-01-03
申请号：US13172316
申请日：2011-06-29
Applicant: Ioannis Alvanos , Gabriel L. Suciu
Inventor： Ioannis Alvanos , Gabriel L. Suciu
IPC: F02C3/04
CPC classification number: F01D9/044 , F01D9/041 , F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/53 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.
Abstract translation: 燃气涡轮发动机包括压缩机，燃烧器部分和涡轮机。 涡轮机包括由陶瓷基体复合材料组成的集成壳体/定子段。
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公开(公告)号：US20120301306A1
公开(公告)日：2012-11-29
申请号：US13116199
申请日：2011-05-26
Applicant: Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
Inventor： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
IPC: F01D5/30
CPC classification number: F01D5/3046 , F01D5/225 , F01D5/282 , F01D5/284 , F05D2300/6033
Abstract: A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures.
Abstract translation: 用于燃气涡轮发动机的转子盘组件包括围绕旋转轴限定的转子毂，转子毂包括具有第一径向凸缘的叶片安装部分，第一径向凸缘具有多个第一孔，第二径向凸缘具有多个第二孔 。
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25.发明申请公开(公告)号：US20120297791A1
公开(公告)日：2012-11-29
申请号：US13116116
申请日：2011-05-26
Applicant: Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
CPC classification number: F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
Abstract translation: 用于燃气涡轮发动机的涡轮机排气箱包括在CMC核心机舱后部和CMC尾锥之间的多个CMC涡轮机排气外壳支柱。
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Patent Agency Ranking
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
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。
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公开(公告)号：US09938900B2
公开(公告)日：2018-04-10
申请号：US13116116
申请日：2011-05-26
Applicant: Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
Inventor： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
CPC classification number: F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
Abstract: A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
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公开(公告)号：US09347374B2
公开(公告)日：2016-05-24
申请号：US13405514
申请日：2012-02-27
Applicant: Gabriel L. Suciu , Ioannis Alvanos
Inventor： Gabriel L. Suciu , Ioannis Alvanos
CPC classification number: F02C6/08 , F01D5/081 , F01D9/065 , F02C7/18 , F02C7/185 , F05B2260/205 , Y02T50/676
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US09109458B2
公开(公告)日：2015-08-18
申请号：US13294787
申请日：2011-11-11
Applicant: Ioannis Alvanos , Gabriel L. Suciu
Inventor： Ioannis Alvanos , Gabriel L. Suciu
CPC classification number: F01D11/001 , F01D11/122 , F01D11/127 , F05D2230/64 , F05D2250/184 , F05D2260/38
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US09039364B2
公开(公告)日：2015-05-26
申请号：US13172316
申请日：2011-06-29
Applicant: Ioannis Alvanos , Gabriel L. Suciu
Inventor： Ioannis Alvanos , Gabriel L. Suciu
IPC: F04D29/44 , F04D29/54 , F03B1/00 , F03B11/02 , F03D5/00 , F01D1/02 , F03D1/04 , F03D3/04 , F03B3/16 , F01D9/04 , F01D25/24
CPC classification number: F01D9/044 , F01D9/041 , F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/53 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.
Abstract translation: 燃气涡轮发动机包括压缩机，燃烧器部分和涡轮机。 涡轮机包括由陶瓷基体复合材料组成的集成壳体/定子段。
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