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33 条记录 (耗时 0.025 秒)

    Member having internal cooling passage
    3.
    发明授权
    Member having internal cooling passage 失效
    会员有内部冷却通道

    公开(公告)号：US5395212A

    公开(公告)日：1995-03-07

    申请号：US255882

    申请日：1994-06-07

    申请人： Shunichi Anzai ,  Kuzuhiko Kawaike ,  Isao Takehara ,  Tetsuo Sasada ,  Hajime Toriya

    发明人： Shunichi Anzai ,  Kuzuhiko Kawaike ,  Isao Takehara ,  Tetsuo Sasada ,  Hajime Toriya

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2260/2212

    摘要： The present invention effectively cools members with a small amount of cooling air. Turbulence promotor ribs are formed so that cooling fluid along a wall flows from a center of the wall to both end portions of the wall. A highly enhanced thermal conducting effect, namely high cooling heat transfer coefficient, can be obtained, and it is possible to cool members effectively with the small amount of cooling air.

    摘要翻译： 本发明有效地冷却了少量冷却空气的构件。 湍流促动肋形成为使得沿着壁的冷却流体从壁的中心流动到壁的两个端部。 可以获得高度增强的导热效果，即高冷却传热系数，并且可以用少量的冷却空气有效地冷却构件。

    Warming structure of gas turbine rotor
    5.
    发明授权
    Warming structure of gas turbine rotor 失效
    燃气轮机转子变暖结构

    公开(公告)号：US4880354A

    公开(公告)日：1989-11-14

    申请号：US272910

    申请日：1988-11-18

    申请人： Mitsuo Teranishi ,  Haruo Urushidani ,  Hajime Toriya ,  Shoji Ebine

    发明人： Mitsuo Teranishi ,  Haruo Urushidani ,  Hajime Toriya ,  Shoji Ebine

    IPC分类号： F01D5/08 ,  F01D25/10

    CPC分类号： F01D5/08 ,  F01D25/10

    摘要： A gas turbine rotor warming structure comprises a tubular member having an axially extending central through hole and a plurality of fine holes formed in a side wall thereof. The tubular member is inserted in central holes of rotor disks each having blades so as to form an annular gap between the inner surfaces of the central holes and the outer surface of the tubular member. The plurality of fine holes of the tubular member are formed so as to face the inner peripheral surface of the central holse of the rotor disks, so that gas extracted from a compressor is injected into the annular gap through the fine holes and impinges on the inner peripheral surfaces of the rotor disks, whereby inner peripheral portions of the rotor disks are warmed at the time of starting of the gas turbine. The extracted compressor gas which has warmed the inner peripheral portions of the rotor disks passes between the disks and cools the turbine blades.

    Blade profile for axial flow compressor
    7.
    发明授权
    Blade profile for axial flow compressor 失效
    轴流式压缩机叶片型材

    公开(公告)号：US5554000A

    公开(公告)日：1996-09-10

    申请号：US302261

    申请日：1994-09-08

    申请人： Yasuhiro Katoh ,  Yoshihiro Tsuda ,  Mitsuaki Yanagida ,  Hajime Toriya ,  Tetsuo Sasada

    发明人： Yasuhiro Katoh ,  Yoshihiro Tsuda ,  Mitsuaki Yanagida ,  Hajime Toriya ,  Tetsuo Sasada

    IPC分类号： F04D29/38 ,  F01D5/14 ,  F04D29/32 ,  F01D9/04

    CPC分类号： F04D29/324 ,  F01D5/141 ,  F04D21/00 ,  F05D2240/302 ,  Y10S416/02

    摘要： An axial flow compressor for use in a gas turbine or other industrial application having an improved efficiency is provided through modification of the blade shape and profile of the blades subject to a subsonic high velocity inlet flow so as to avoid shock losses in the blade rows, and improve the total efficiency. The curvature distribution on the suction surface of the stator blade rows or rotor blade rows of the axial flow compressor is adapted to have a local minimum in a region toward the leading edge of the blade, and then a local maximum. Thereby, an excessive increment in velocity on the suction surface from the leading edge to the position of the maximum velocity can be suppressed, and the occurrence of a shock wave can be avoided so as to minimize pressure loss in the blade rows, thus increasing the total efficiency of the axial compressor.

    摘要翻译： 通过修改叶片形状和受到亚音速高速入口流动的叶片轮廓来提供用于具有改进效率的燃气轮机或其他工业应用中的轴流式压缩机，以避免叶片排中的冲击损失， 并提高总体效率。 轴流式压缩机的定子叶片排或转子叶片排的吸力表面上的曲率分布适于在朝向叶片的前缘的区域中具有局部最小值，然后是局部最大值。 因此，可以抑制从前缘到最大速度位置的吸入面上的速度的过度增加，并且可以避免冲击波的发生，以使叶片排中的压力损失最小化，从而增加 轴流式压缩机的总效率。

    Thermal stress relaxation type ceramic coated heat-resistant element
    8.
    发明授权
    Thermal stress relaxation type ceramic coated heat-resistant element 失效
    热应力松弛型陶瓷涂层耐热元件

    公开(公告)号：US5630314A

    公开(公告)日：1997-05-20

    申请号：US320780

    申请日：1994-10-11

    申请人： Yoshitaka Kojima ,  Hideyuki Arikawa ,  Mitsuo Haginoya ,  Akira Mebata ,  Tetsuo Sasada ,  Hajime Toriya

    发明人： Yoshitaka Kojima ,  Hideyuki Arikawa ,  Mitsuo Haginoya ,  Akira Mebata ,  Tetsuo Sasada ,  Hajime Toriya

    IPC分类号： C23C4/02 ,  C23C14/02 ,  C23C14/08 ,  C23C14/22 ,  C23C28/00 ,  F01D5/28 ,  F02C6/18

    CPC分类号： C23C28/321 ,  C23C14/022 ,  C23C14/083 ,  C23C14/22 ,  C23C28/00 ,  C23C28/345 ,  C23C28/3455 ,  C23C4/02 ,  F01D5/28 ,  F01D5/288 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/671 ,  Y10T428/12549 ,  Y10T428/131 ,  Y10T428/1317 ,  Y10T428/25 ,  Y10T428/2949 ,  Y10T428/2991 ,  Y10T428/30

    摘要： The present invention provides ceramic coated heat-resistant elements which suffer no damages even under high heat load conditions and can afford a thermal barrier effect stably for a long period of time and can be used, for example, as buckets and stationary blades of turbines. A method for making the elements is also provided. The ceramic coated heat-resistant element comprises a heat resisting alloy base mainly composed of Ni and/or Co and a heat-resistant coating layer provided on the surface of the base and is characterized in that said heat-resistant coating layer comprises a metal layer of an alloy superior to the base in high-temperature corrosion and oxidation resistance and provided on the base, an Al.sub.2 O.sub.3 ceramic thin film layer provided on the metal layer, a ZrO.sub.2 ceramic coating layer having dense texture provided on the Al.sub.2 O.sub.3 ceramic thin film layer and a ZrO.sub.2 ceramic coating layer having columnar texture provided on the ZrO.sub.2 ceramic coating layer having dense texture and cracks are present only in said ZrO.sub.2 ceramic coating layer having columnar texture in the direction of thickness along the boundary of the columns. A mixed layer composed of a metal superior to the base in high-temperature corrosion and oxidation resistance and a ZrO.sub.2 ceramic may be provided between the base and the metal layer.

    摘要翻译： 本发明提供陶瓷涂层耐热元件，即使在高热负荷条件下也不会遭受损坏，并且能够长时间稳定地提供热障效果，并且可以用作例如水轮机和涡轮机的固定叶片。 还提供了制造元件的方法。 陶瓷涂层耐热元件包括主要由Ni和/或Co组成的耐热合金基体和设置在基体表面上的耐热涂层，其特征在于所述耐热涂层包括金属层 在高温腐蚀和抗氧化性优于基体的合金中，在基体上设置设置在金属层上的Al 2 O 3陶瓷薄膜层，在Al 2 O 3陶瓷薄膜层上提供具有致密纹理的ZrO 2陶瓷涂层，以及 具有密集纹理和裂纹的ZrO 2陶瓷涂层上具有柱状结构的ZrO 2陶瓷涂层仅存在于沿着柱边界的厚度方向上具有柱状结构的所述ZrO 2陶瓷涂层中。 在基材和金属层之间可以设置由高温耐腐蚀和抗氧化性优于基材的金属和ZrO 2陶瓷组成的混合层。

    Alloy-coated gas turbine blade and manufacturing method thereof
    9.
    发明授权
    Alloy-coated gas turbine blade and manufacturing method thereof 失效
    合金涂层燃气轮机叶片及其制造方法

    公开(公告)号：US5507623A

    公开(公告)日：1996-04-16

    申请号：US286787

    申请日：1994-04-04

    申请人： Yoshitaka Kojima ,  Kiyoshi Otake ,  Akira Mebata ,  Hideyuki Arikawa ,  Tetsuo Sasada ,  Hajime Toriya

    发明人： Yoshitaka Kojima ,  Kiyoshi Otake ,  Akira Mebata ,  Hideyuki Arikawa ,  Tetsuo Sasada ,  Hajime Toriya

    IPC分类号： C22C19/05 ,  C22C19/07 ,  C23C4/02 ,  C23C4/18 ,  C23C10/02 ,  C23C10/48 ,  C23C28/02 ,  F01D5/28 ,  F01D9/02

    CPC分类号： C23C4/02 ,  C23C10/02 ,  C23C10/48 ,  C23C4/18 ,  F01D5/286 ,  F01D5/288 ,  Y10T428/12458 ,  Y10T428/1275 ,  Y10T428/12944

    摘要： A coated layer of this invention is composed of a lower alloy-coated layer 2 formed of an MCrAlY alloy whose principal element is Co or Co and Ni, an upper alloy-coated layer 1 formed of an MCrAlY alloy whose principal element is Ni and a portion 4 in which an Al content of the surface portion of the upper coated layer 1 is largest and is reduced gradually towards a more internal part. Manufacturing thereof involves the steps of forming the lower and upper coated layers and effecting an Al diffusion treatment into the upper coated layer. The upper coated layer having the portion which exhibits the large Al content contributes to a high-temperature anticorrosive property. A gas turbine blade is provided with the alloy-coated layer, wherein the lower coated layer incorporates a composite function to prevent a high-temperature corrosion of a base material when cracks are caused in the upper coated layer due to thermal stress. The gas turbine blade exhibits effects of improving the reliability and increasing a life-time.

    摘要翻译： 本发明的涂层由主要元素为Co或Co和Ni的MCrAlY合金形成的下合金涂层2，由主要元素为Ni的MCrAlY合金形成的上合金涂层1和 部分4，其中上涂层1的表面部分的Al含量最大并且朝向更内部的部分逐渐减小。 其制造包括形成下涂层和上涂层并对Al涂层进行Al扩散处理的步骤。 具有大Al含量的部分的上涂层有助于高温防腐蚀性能。 燃气轮机叶片具有合金涂层，其中下涂层具有复合功能，以防止由于热应力在上涂层中引起裂纹时基体材料的高温腐蚀。 燃气轮机叶片具有提高可靠性和延长使用寿命的效果。

    Seals in steam turbine
    10.
    发明授权
    Seals in steam turbine 有权
    汽轮机密封

    公开(公告)号：US08500397B2

    公开(公告)日：2013-08-06

    申请号：US13396033

    申请日：2012-02-14

    申请人： Kenjiro Narita ,  Haruyuki Yamazaki ,  Hiroyuki Doi ,  Kei Kobayashi ,  Hajime Toriya

    发明人： Kenjiro Narita ,  Haruyuki Yamazaki ,  Hiroyuki Doi ,  Kei Kobayashi ,  Hajime Toriya

    IPC分类号： F01D5/20 ,  F01D11/08 ,  F04D29/08 ,  F04D29/18

    CPC分类号： F01D11/02 ,  F01D11/001 ,  F01D11/08 ,  F05D2220/31 ,  F05D2250/182 ,  F05D2300/5024 ,  F16J15/162 ,  F16J15/445 ,  F16J15/4472

    摘要： A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device.

    摘要翻译： 提供了一种用于蒸汽涡轮机的密封结构，其能够抑制由旋转部分和固定部分之间的摩擦产生的热量转移到旋转部分并抑制旋转部分的温度升高。 迷宫式密封装置用于抑制从蒸汽涡轮机的每个定子叶片（固定部分）和转子（旋转部分）之间存在的间隙泄漏的蒸汽量。 形成蒸汽轮机的密封结构，以确保在转子和密封件固定体上设置由可渗透金属构成的可渗透间隔件，并面对设置在迷宫式密封装置中的相应密封翅片。