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    Swash plate type compressor
    41.
    发明授权
    Swash plate type compressor 失效
    斜盘式压缩机

    公开(公告)号：US4285640A

    公开(公告)日：1981-08-25

    申请号：US60462

    申请日：1979-07-25

    Applicant: Takamitu Mukai

    Inventor： Takamitu Mukai

    IPC: F04B27/08 ,  F04B27/10 ,  F04B1/18 ,  F16C17/06

    CPC classification number: F04B27/1054 ,  F04B27/0886 ,  F05C2201/025 ,  F05C2201/0475 ,  F05C2201/0493 ,  F05C2203/06 ,  F05C2253/12

    Abstract: A swash plate type compressor for compressing a refrigerant of an air conditioning system incorporating therein a rotating swash plate made of an aluminum alloy, one or more compressor pistons reciprocating in a cylinder block for effecting compression of the refrigerant, and an operative engagement means which is between the swash plate and the piston or pistons. The operative engagement means is made of a carbon steel material and a flattened face of the operative engagement means contacting the aluminum alloy swash plate consisting of a cementation treatment layer formed in the carbon steel material of the operative engagement means.

    Abstract translation: 一种斜盘式压缩机，用于压缩其中装有由铝合金制成的旋转斜盘的空调系统的制冷剂，一个或多个在气缸体中往复运动的压缩机活塞，用于压缩制冷剂;以及操作接合装置， 在斜盘和活塞或活塞之间。 操作接合装置由碳钢材料和与操作接合装置的碳钢材料中形成的胶结处理层组成的铝合金斜盘接触的操作接合装置的平坦表面制成。

    Composite aerofoil
    45.
    发明公开
    Composite aerofoil 有权
    Verbundschaufel

    公开(公告)号：EP1669547A2

    公开(公告)日：2006-06-14

    申请号：EP05256747.6

    申请日：2005-11-01

    Applicant: Rolls-Royce plc

    Inventor： McMillan, Alison Jane

    IPC: F01D5/28 ,  F01D5/14

    CPC classification number: B29C70/222 ,  B29C70/865 ,  B29D99/0028 ,  B29L2031/08 ,  D03D25/005 ,  F01D5/147 ,  F01D5/282 ,  F05C2201/025 ,  F05D2230/60 ,  F05D2240/301 ,  F05D2250/20 ,  F05D2250/293 ,  F05D2300/2261 ,  F05D2300/2283 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/612 ,  F05D2300/614 ,  Y02E10/721 ,  Y02T50/43 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T442/20 ,  Y10T442/2975 ,  Y10T442/3195

    Abstract: A composite blade (26) comprises a three-dimensional arrangement of reinforcing fibres (58) and a matrix material (60) infiltrated around the three-dimensional arrangement of woven reinforcing fibres (60). The three-dimensional arrangement of woven reinforcing fibres (58) defines a plurality of cavities (56) within the aerofoil (28). The composite blade (26) comprises an aerofoil portion (38) and a root portion (36). The aerofoil portion (38) comprises a leading edge (44), a trailing edge (46), a concave pressure surface wall (50), a convex suction surface wall (52) and a tip (48). The aerofoil portion (36) comprises a plurality of webs (54) extending between, and being secured to, the concave pressure surface wall (50) and the convex suction surface wall (52) to produce a Warren girder structure. The three-dimensional arrangement of woven reinforcing fibres (58) are arranged to produce the concave pressure surface wall (50), the convex suction surface wall (52) and the plurality of webs (54). The matrix material (60) is an organic resin and the reinforcing fibres (58) comprise carbon fibres.

    Abstract translation: 复合叶片（26）包括增强纤维（58）和渗透在编织增强纤维（60）的三维布置周围的基质材料（60）的三维排列。 编织增强纤维（58）的三维布置在机翼（28）内限定多个空腔（56）。 复合叶片（26）包括机翼部分（38）和根部（36）。 机翼部分（38）包括前缘（44），后缘（46），凹形压力表面壁（50），凸起的吸力表面壁（52）和尖端（48）。 机翼部分（36）包括在凹压表面壁（50）和凸形抽吸表面壁（52）之间延伸并固定到凸形抽吸表面壁（52）之间的多个腹板（54），以产生沃伦梁结构。 编织增强纤维（58）的三维布置被布置成产生凹压表面壁（50），凸形抽吸表面壁（52）和多个腹板（54）。 基质材料（60）是有机树脂，增强纤维（58）包含碳纤维。

    Nickel-based single-crystal alloy
    49.
    发明专利
    Nickel-based single-crystal alloy 有权
    镍基单晶合金

    公开(公告)号：JP2009114501A

    公开(公告)日：2009-05-28

    申请号：JP2007289127

    申请日：2007-11-07

    Applicant: Hitachi Ltd ,  株式会社日立製作所

    Inventor： YOSHINARI AKIRA ,  TAMAOKI HIDEKI

    IPC: C22C19/05 ,  B22D21/00 ,  B22D27/04 ,  C22F1/00 ,  C22F1/10 ,  F01D5/28 ,  F02C7/00

    CPC classification number: C22C19/057 ,  F01D5/28 ,  F05C2201/025 ,  F05C2201/0466 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/134 ,  F05D2300/607 ,  Y02T50/671

    Abstract: PROBLEM TO BE SOLVED: To provide a Ni-based single crystal alloy with which the solidifying crack at the time of casting a large wing does not occur, and the sufficient strength in the crystal grain boundary to secure the reliance during using is provided and to further higher temperature of combustion gas, while having the excellent high temperature strength as the same range as the conventional single crystal alloy, the further excellent oxidizing resistant characteristic is provided, too.
    SOLUTION: The Ni-based single crystal alloy has the composition composed by wt.% of 0.06-0.09% C, 0.016-0.035% B, 0.2-0.4% Hf, 0-0.02% Zr, 6.5-8.5% Cr, 0.4-1.0% Mo, 5.5-9.5% W, 1.2-3.1% Re, 8-10% Ta, 0.3-1.0% Nb, 0-0.4% Ti, 4.7-5.4% Al, 0.5-5.0% Co, 0.1-5% Fe and the balance substantially Ni.
    COPYRIGHT: (C)2009,JPO&INPIT

    Abstract translation: 要解决的问题：提供一种不会发生铸造大型机翼时的固化裂纹的Ni基单晶合金，并且在晶界的足够强度以确保使用时的依赖性是 提供并进一步提高燃烧气体的温度，同时具有与常规单晶合金相同范围的优异的高温强度，还提供了更好的耐氧化性能。 解决方案：Ni基单晶合金的组成为：重量％为0.06-0.09％C，0.016-0.035％B，0.2-0.4％Hf，0-0.02％Zr，6.5-8.5％Cr ，0.4-1.0％Mo，5.5-9.5％W，1.2-3.1％Re，8-10％Ta，0.3-1.0％Nb，0-0.4％Ti，4.7-5.4％Al，0.5-5.0％Co，0.1 -5％Fe，余量基本为Ni。 版权所有（C）2009，JPO＆INPIT

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