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    Integrated ceramic matrix composite disk for gas turbine engine
    1.
    发明专利
    Integrated ceramic matrix composite disk for gas turbine engine 有权
    用于气体涡轮发动机的集成陶瓷基复合材料盘

    公开(公告)号：JP2012246925A

    公开(公告)日：2012-12-13

    申请号：JP2012119126

    申请日：2012-05-25

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： ALVANOS IOANNIS ,  SUCIU GABRIEL L

    IPC: F01D5/28 ,  F01D5/02 ,  F01D5/12 ,  F01D5/20 ,  F01D9/02 ,  F01D9/04 ,  F01D11/02 ,  F01D11/08 ,  F01D25/00 ,  F02C7/00 ,  F02C7/28

    CPC classification number: F01D5/282 ,  F01D5/066 ,  F01D5/284 ,  F01D5/34 ,  F01D11/001 ,  F05D2300/6033

    Abstract: PROBLEM TO BE SOLVED: To provide an additional disk for a gas turbine engine.SOLUTION: CMC disks 64A, 64B and 64C for a gas turbine engine 20 include CMC hubs 68A, 68B and 68C defined about an axis, and a plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs. The CMC disks 64A, 64B and 64C for the gas turbine engine 20 include the plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs 68A, 68B and 68C, and rails 80A, 80C integrated with the respective CMC hubs on sides opposite to the plurality of airfoils. The rails define rail platforms adjacent to the plurality of airfoils and tapered to a rail inner bore.

    Abstract translation: 要解决的问题：提供用于燃气涡轮发动机的附加盘。 解决方案：用于燃气涡轮发动机20的CMC盘64A，64B和64C包括围绕轴限定的CMC轮毂68A，68B和68C以及与各个CMC轮毂一体化的多个CMC翼型66A，66B和66C。 用于燃气涡轮发动机20的CMC盘64A，64B和64C包括与相应的CMC集线器68A，68B和68C一体化的多个CMC翼型66A，66B和66C，以及与侧面上的相应CMC轮毂一体化的轨道80A，80C 与多个翼型件相对。 导轨限定与多个翼型件相邻的轨道平台并且逐渐变细到轨道内孔。 版权所有（C）2013，JPO＆INPIT

    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY AND BLADE FOR ROTOR ASSEMBLY
    3.
    发明专利
    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY AND BLADE FOR ROTOR ASSEMBLY 审中-公开

    公开(公告)号：JP2006342796A

    公开(公告)日：2006-12-21

    申请号：JP2006153022

    申请日：2006-06-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA

    IPC: F01D11/02 ,  F02C7/28 ,  F16J15/44

    Abstract: PROBLEM TO BE SOLVED: To provide a seal assembly for restricting leaking-out of cooling air in constant. SOLUTION: An inside cavity 50 is positioned between a vane support part 52 and a rotor assembly 54 on the inside in the radial direction of an annular duct 30. The cooling air 40 is introduced into the cavity 50 by a duct 70, and cools a blade 58 by flowing in a conduit 72. The cavity 50 is separated from the duct 30 by a seal 80 having land 84 and a segment-like ring 86, and air pressure is properly maintained over the whole engine conditions. The ring 86 extends by crossing the cavity 50 from a neck area 96. One complete segment-like ring 86 is formed by aligning a plurality of adjacent ring segments 186 in a state of inserting the blade 58 into a disc. Leaking-out restriction is improved by extending a runner 200 outside in the radial direction from the ring 86 by inclining to a shaft 11. COPYRIGHT: (C)2007,JPO&INPIT

    Vane structure and low-pressure turbine for gas turbine engine
    4.
    发明专利
    Vane structure and low-pressure turbine for gas turbine engine 有权
    瓦斯结构和低压涡轮发动机

    公开(公告)号：JP2012246915A

    公开(公告)日：2012-12-13

    申请号：JP2012099334

    申请日：2012-04-25

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： SUCIU GABRIEL L ,  ALVANOS IOANNIS ,  MERRY BRIAN D ,  DYE CHRISTOPHER M

    IPC: F01D9/04 ,  F01D25/24 ,  F02C7/00

    CPC classification number: F01D5/284 ,  F01D5/147 ,  F01D5/282 ,  F01D9/041 ,  F01D11/001 ,  F01D25/246 ,  F05D2240/12 ,  F05D2300/6033

    Abstract: PROBLEM TO BE SOLVED: To provide a full hoop ring structure that prevents leakage of fluid from between each segment of a vane structure.SOLUTION: A vane structure 64B includes: a ceramic matrix composite ring 66 on the outer peripheral side; a ceramic matrix composite ring 68 on the inner peripheral side; and a multiple of ceramic matrix composite airfoils 70 incorporated between the ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side. The ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side are basically wound around the multiple of incorporated airfoils 70 so as to form a full hoop. The design of the full hoop rings allows to maximize the utilization of the fiber strength of the ceramic matrix composite material in the full hoop configuration.

    Abstract translation: 要解决的问题：提供一种防止来自叶片结构的每个部分之间的流体泄漏的完整环形环结构。 解决方案：叶片结构64B包括：外周侧的陶瓷基复合环66; 内周侧的陶瓷基复合环68; 以及并列在外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68之间的多个陶瓷基复合翼型件70。 外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68基本上缠绕在多个配置的翼型件70上，以形成完整的箍。 全环环的设计允许最大限度地利用全环形结构中的陶瓷基复合材料的纤维强度。 版权所有（C）2013，JPO＆INPIT

    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY, BLADE FOR ROTOR ASSEMBLY AND INTER-STAGE CAVITY SEAL
    5.
    发明专利
    SEAL ASSEMBLY OF GAS TURBINE ENGINE, ROTOR ASSEMBLY, BLADE FOR ROTOR ASSEMBLY AND INTER-STAGE CAVITY SEAL 审中-公开

    公开(公告)号：JP2006342797A

    公开(公告)日：2006-12-21

    申请号：JP2006154370

    申请日：2006-06-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALVANOS IOANNIS ,  AGRAWAL RAJENDRA ,  VIRTUE JOHN P JR ,  HILL JAMES D ,  PINERO HECTOR M ,  JOHNSON ERIKA

    IPC: F01D11/02 ,  F02C7/28

    Abstract: PROBLEM TO BE SOLVED: To provide a seal assembly for restricting leaking-out of cooling air in constant. SOLUTION: An inside cavity 50 is positioned between a vane support part 52 and a rotary assembly 54 on the inside in the radial direction of an annular duct 30. The cooling air 40 is introduced into the cavity 50 by a duct 70, and cools a blade 58 by flowing in a conduit 72. The cavity 50 is separated from the duct 30 by a seal 80, and air pressure is properly maintained over the whole engine conditions. A segment-like ring 86 extends by crossing the cavity 50 from a divided rim area 110, and a runner 170 is aligned with land 84. One complete segment-like ring 86 is formed by aligning a plurality of adjacent ring segments 164 and 166 in a state of inserting the blade 58 into a disc. Leaking-out restriction is improved by extending the runner 170 outside or inside in the radial direction from the ring 86 by inclining to a shaft 11. COPYRIGHT: (C)2007,JPO&INPIT

    Airfoil and vane, made of ceramic composite material, for gas turbine engine, and method for forming the airfoil made of ceramic composite material
    9.
    发明专利
    Airfoil and vane, made of ceramic composite material, for gas turbine engine, and method for forming the airfoil made of ceramic composite material 有权
    陶瓷复合材料制造用气体涡轮发动机的空气和风扇以及形成陶瓷复合材料的气体的方法

    公开(公告)号：JP2012246919A

    公开(公告)日：2012-12-13

    申请号：JP2012105607

    申请日：2012-05-07

    Applicant: United Technologies Corp ,  ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation

    Inventor： SUCIU GABRIEL L ,  ALVANOS IOANNIS

    IPC: F01D5/28 ,  F01D5/14 ,  F01D9/02 ,  F01D25/00 ,  F02C7/00

    CPC classification number: F01D25/246 ,  F01D5/282 ,  F01D5/284 ,  F01D9/041 ,  F01D11/008 ,  F05D2240/12 ,  F05D2300/6033 ,  Y10T29/49323 ,  Y10T29/49337

    Abstract: PROBLEM TO BE SOLVED: To provide an airfoil, made of a ceramic composite material, for a gas turbine engine.SOLUTION: Each CMC airfoil 66 made of a ceramic composite material has an airfoil portion 68 defined between a leading edge 70 and a trailing edge 72, and fillets 74, 76 forming a transition to inner and outer platform segments 78, 80 on each side of the airfoil portion 68. A CMC ply 88 used for manufacturing the CMC airfoil 66 forms an I-shaped fiber structure. The pressure side 82, the suction side 84, and the platform segments 78, 80 are continuously and integrally formed. A first portion of the CMC ply 88 defines the airfoil portion 68, the pressure side 82, and the suction side 84. Transverse portions of the CMC ply 88 defines the platform segments 78, 80. The platform section 78, 80 are chevron-shaped to provide a complementary geometry with respect to each adjacent platform section.

    Abstract translation: 要解决的问题：提供一种用于燃气涡轮发动机的由陶瓷复合材料制成的翼型件。 解决方案：由陶瓷复合材料制成的每个CMC翼型件66具有限定在前缘70和后缘72之间的翼型部分68，以及形成向内平台段78和外平台段80的过渡的圆角74和76， 翼型部分68的每一侧。用于制造CMC翼型66的CMC层88形成I形纤维结构。 压力侧82，吸力侧84和平台段78,80连续地和一体地形成。 CMC层88的第一部分限定翼型部分68，压力侧82和吸力侧84. CMC层88的横向部分限定平台段78,80。平台段78,80是人字形 以相对于每个相邻的平台部分提供互补的几何形状。 版权所有（C）2013，JPO＆INPIT

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