• 学术搜索
  • 科研智能体
    • Research Labs
    • AI 阅读
    • AI 文库
    • 深度研究
    • 学者亮点
  • 学术资源
    • AI2000
    • 期刊/会议
    • 学者库
    • 学术API
    • 溯源树
    • 数据集
  • 知识沉淀
    • 学术空间
订阅小程序
旧版功能
aminer vip
开通会员低至0.73元/天
一次搞定AI科研
立即登录
  • English
  • 联系方式
    专

    任意柱面共形超构表面共形天线及其设计方法

    KR20180198079A
    发明人
    刘凯越, 蔡通, 李腾耀, 郑娜娥, 王书, 李汀立
    受让人
    UNIV INFORMATION ENG
    申请人
    Bugeye Technologies Inc.
    申请号
    060096
    申请日
    1968-05-15
    公开(公告)号
    KR20180198079A
    公开(公告)日
    2003-08-25
    IPC分类号
    H01R004/18H01R004/70H01R043/048H01R004/62
    CPC分类号
    -
    优先权号
    147927
    优先权日
    1995-06-13
    摘要

    NOVELTY - A plate cutter (40) has an anvil roll (42) opposed to a male die roll (44) in a frame (46) and the die roll has cutter blades (48a) to sever the paper-less plates from a pasted metal strip with a plate configuration. A cartridge heater heats the die roll to a temperature of 180-210 degrees C to prevent the paste sticking to the metal mesh strip.

    USE - Paper elimination in production of battery plates.

    DETAILED DESCRIPTION - AN INDEPENDENT CLAIM is included for apparatus for continuously cutting pasted, expanded, punched or cast lead or lead alloy mesh strips into battery plates.

    DESCRIPTION OF DRAWING(S) - The drawing shows the cutter

    Anvil roll (42)

    Die roll (44)

    Blades (48a)

    Frame (46)

    权利要求
    1 . A gas turbine engine turbine blade comprising: a turbine blade body including an inner platform, an airfoil extending radially outwardly of the inner platform, the airfoil having a leading edge and a trailing edge, and a suction wall and a pressure wall; said turbine blade body having mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face; said turbine blade body being formed of one of a polymer matrix composite, metal matrix composite or ceramic matrix composite, and there being a protective coating on the radially outer faces of said at least one enlarged mount portions; there being uncoated portions radially inward and radially outward of the protective coating on the radially outer faces of said at least one mount portion; and wherein one of two axial ends of said at least one circumferentially extending mount portion also receives the protective coating.
    2 . The blade as set forth in claim 1 , wherein there are two radially spaced ones of said circumferentially extending mount portion of each of said suction wall side and said pressure wall side, and each of said circumferentially extending mount portions having the coating on said radially outer face.
    3 . (canceled)
    4 . The blade as set forth in claim 2 , wherein the protective coating is on said one axial end of both of said circumferentially extending mount portions.
    5 . The blade as set forth in claim 4 , wherein the coating is also on an opposed one of said axial ends of at least one of the circumferentially extending mount portions.
    6 . (canceled)
    7 . The blade as set forth in claim 1 , wherein the coating is also on an opposed one of said axial ends of at least one of the circumferentially extending mount portion.
    8 . The blade as set forth in claim 1 , wherein there are uncoated portions radially inward and radially outward of the protective coating on said at least one of the axial ends.
    9 . A gas turbine engine comprising: a compressor section, a combustor section and a turbine section; said turbine section including a shaft rotating with a turbine disk, said turbine disk having a plurality of slots and said turbine disk formed of a metal, turbine blades received within each of said slots; said turbine blades including an inner platform, an airfoil extending radially outwardly of the inner platform, the airfoil having a leading edge and a trailing edge, and a suction wall side and a pressure wall side, and mount structure including at least one circumferentially outwardly extending mount portions each having a radially outer face; said turbine blade being formed of one of a polymer matrix composite, metal matrix composite or ceramic matrix composite, and there being a protective coating on the radially outer faces of said at least one circumferentially outwardly extending mount portions; there being uncoated portions radially inward and radially outward of the protective coating on the radially outer faces of said at least one mount portion; and wherein one of two axial ends of at least one of said circumferentially extending mount portions also receives the protective coating, and a mount features secures the blades in the disk and contacts the circumferentially extending mount portion at a location on the axial end receiving the coating.
    10 . The gas turbine engine as set forth in claim 9 , wherein there are two radially spaced ones of said circumferentially extending mount portions on each of said suction wall side and said pressure wall side, and each of said circumferentially extending mount portions having the coating on said radially outer face.
    11 . (canceled)
    12 . The gas turbine engine as set forth in claim 10 , wherein the protective coating is formed on said one axial end of both of two circumferentially extending mount portions, and the mount feature is a cover plate formed of a metal and secured to the disk.
    13 . The gas turbine engine as set forth in claim 12 , wherein the coating is also on an opposed one of said axial ends of at least one of the circumferentially extending mount portions, and there being a mini-disk fixed to said shaft, and in contact with the mount structure on the turbine blades, with said mini-disk formed of a metal and contacting the blade at a location on the opposed axial end, and the location receiving the coating.
    14 . The gas turbine engine as set forth in claim 10 , wherein the coating is also on an opposed one of said axial ends of at least one of the circumferentially extending mount portions, and there being a mini-disk fixed to said shaft, and in contact with the mount structure on the turbine blades, with said mini-disk formed of a metal and contacting the blade at a location on the opposed axial end, and the location receiving the coating.
    15 . (canceled)
    16 . The gas turbine engine as set forth in claim 9 , wherein the coating is also on an opposed one of said axial ends of at least one of the circumferentially extending mount portions, and there being a mini-disk fixed to said shaft, and in contact with the mount structure on the turbine blades, with said mini-disk formed of a metal and contacting the blade at a location on the opposed axial end, and the location receiving the coating.
    17 . A gas turbine engine turbine blade comprising: a turbine blade body including an inner platform, an airfoil extending radially outward of the inner platform, the airfoil having a leading edge and a trailing edge, and a suction wall and a pressure wall; said turbine blade body having mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side, and each having a radially outer face and a pair of opposed axial ends; and said turbine blade body being formed of one of a polymer matrix composite, metal matrix composite or ceramic matrix composite, and there being a protective coating on the at least one mount portion at at least one of the axial ends; and there being uncoated portions on said at least one circumferentially outwardly extending mount portion at the at least one axial end radially inward and radially outward of the protective coating.
    18 . The gas turbine engine blade as set forth in claim 17 , wherein the coating is also on an opposed one of said axial ends of at least one of said circumferentially extending mount portion.
    19 . The gas turbine engine blade as set forth in claim 18 , wherein there are uncoated portions radially inward and radially outward of the protective coating on each of said axial ends.
    20 . The gas turbine engine blade as set forth in claim 17 , wherein there are uncoated portions radially inward and radially outward of the protective coating on at least one of said axial ends.
    说明书
    [0001]技术领域
    [0002]本发明涉及一种具有高热电性能的CdS基热电材料及其制备方法,属于热电材料技术领域。
    [0003]背景技术
    [0004]热电材料是一种将热能和电能直接相互转换的一种材料。热电材料由于自身无污染,尺寸小,无噪音,可精确控制温度,且使用寿命长的特点,在温差发电领域和半导体制冷方面有着巨大的市场潜力与应用前景。热电材料的性能由无量纲优值zT=[S 2 σ/(κ e +κ L )]表征,提高电导率σ和塞贝克系数S,同时降低热导率κ(κ是载流子热导率κ e ,晶格热导率κ L 和双极效应κ B 之和)是材料优化的关键,但该三个物理量相互关联,难以单独调控,这是限制材料热电性能提升的主要原因。理想的热电材料应具备较高的塞贝克系数、高的电导率和低的晶格热导率,从而获得较大的zT值。
    [0005]GeTe作为窄宽体导体,因为Ge不能完全参与反应进而产生Ge空位,产生了大量的空穴载流子,使之具有高热导率和低塞贝克系数,从而导致其热电性能不高,限制了GeTe的热电材料的规模应用。而采用不同的元素掺杂和烧结成型工艺会对GeTe的的组成、晶体及其热电性能产生了巨大影响。
    [0006]CN104681706B的专利申请公开了高优值的P型FeNbHfSb热电材料及其制备方法,该方法的具体步骤如下:原料组成为FeNb 1-x Hf x Sb,其中,x=0.06~0.2;该方法还公开了P型FeNbHfSb热电材料的制备方法,首先按组成为FeNb 1-x Hf x Sb的化学剂量比称取原料铁、铌、铪和锑,氩气保护下,经熔炼得到铸锭;将铸锭粉碎成颗粒,再经烧结得到所述的P型FeNbHfSb热电材料。该方法存在如下缺陷:采用该方法主要针对其zT峰值突破,通常具有较高热电性能的材料受成分影响较大,难以在工业上实现大规模生产。
    [0007]发明内容
    [0008]本发明所要解决的第一个技术问题是提供一种具有高热电性能的CdS基热电材料。
    [0009]本发明具有高热电性能的CdS基热电材料,其原料组成为:A x CdS,其中,A为Cu、Al、Ag、Zn、Ti或Bi,x=0.005-0.02。
    [0010]进一步的,本发明具有高热电性能的CdS基热电材料,其化学式A x CdS中的x值为可以为0.005,0.006,0.007,0.008,0.009,0.010,0.011,0.012,0.013,0.014,0.015,
    [0011]0.016,0.017,0.018,0.019或0.02等,其中x值优选为0.005,0.01或0.02。
    [0012]本发明还提供了上述具有高热电性能的CdS基热电材料的制备方法,其包括如下步骤:
    [0013]a、准备单质硫和单质镉的固体物块,球磨,破碎成粉末,按照Cd、S化学计量为1:1称量混合,将混合料预压成型;
    [0014]b、将a步骤所得到的混合料进行第一次高压成型;
    [0015]c、将b步骤第一次高压成型后的混合料冷却,球磨,按照化学计量比A x CdS,进行掺杂混合;其中,A为Cu、Al、Ag、Zn、Ti或Bi,x=0.005-0.02;x值优选为0.005,0.006,0.007,0.008,0.009,0.010,0.011,0.012,0.013,0.014,0.015,0.016,0.017,
    [0016]0.018,0.019或0.02等;x值更优选为0.005,0.01或0.02;
    [0017]d、将c步骤掺杂混合后所得产物进行第二次高压成型,冷却,球磨,等离子放电烧结,得到具有高热电性能的CdS基热电材料。
    [0018]其中,本发明具有高热电性能的CdS基热电材料的制备方法,步骤a中所述球磨破采用常规球磨设备即可,球磨破碎时间一般为10-40min即可;球磨破碎时间优选为30min。
    [0019]进一步的,为了提高高压成型效果,上述步骤b中所述第一次高压成型的工作压力优选为1.8-2.2Gpa,工作温度为优选为1133-1303K,工作时长优选为50-70min;更进一步的,第一次高压成型的工作压力更优选为2.0Gpa,工作温度更优选为1273K,工作时长更优选为60min。
    [0020]其中,为了提高所制备的具有高热电性能的CdS基热电材料的性能,上述步骤c中掺杂混合后所得混合料的粉粒颗粒直径优选为50μm-500μm。
    [0021]进一步的,为了提高高压成型效果,上述步骤d中所述第二次高压成型的工作压力优选为1.8-2.2Gpa,工作温度优选为1133-1303K,工作时长优选为25-35min。更进一步的,第二次高压成型的工作压力更优选为2Gpa,工作温度更优选为1173K,工作时长更优选为30min。
    [0022]其中,为了提高所制备的具有高热电性能的CdS基热电材料的性能,上述步骤d中所述等离子放电烧结中工作压力优选为55-65MPa,工作温度优选为1013-1033K,工作时长优选为8-12min。进一步的,作为更优选的技术方案,步骤d中所述等离子放电烧结中工作压力为60MPa,工作温度为1023K,工作时长为10min。
    [0023]其中,上述具有高热电性能的CdS基热电材料的制备方法,所述a、c、d步骤中球磨比优选为5:1。球磨时间优选为10-70min。
    [0024]本发明有益效果为:
    [0025]1、本发明利用Cu/Al/Ag/Zn/Ti/Bi掺杂金属元素对载流子浓度优化的协同作用,实现了CdS载流子浓度大范围调控,实现了较高的载流子迁移率,Cu/Al/Ag/Zn/Ti/Bi金属元素实现了引入大量点缺陷,声速下降,增强了声子散射和化学键软化,实现了CdS基体热电材料的性能突破,在CdS基体热电材料从80%到99.9%范围内均实现较高热电性能,工作温度内300-800K的平均zT>1.5,其中最大zT值达到1.75。宽成分区间能够提高工业生产的容错率,利于批量生产,为实现更高的转换效率奠定基础,本发明有良好的社会经济效益。
    [0026]2、本发明对产物进行高温反应前,进行了球磨处理,此步骤不但提高了反应物的细度,而且提高了其均匀度,提高了产物的均一性和最终的性能。
    [0027]具体实施方式
    [0028]下面结合实施例对本发明的具体实施方式做进一步的描述,并不因此将本发明限制在所述的实施例范围之中。
    [0029]实施例1
    [0030](1)准备以下材料:S(99.999%,颗粒),Cd(99.99999%,颗粒),Al(99.99999%,颗粒),Cu(99.999%,颗粒),Ag(99.999%,颗粒),Zn(99.999%,颗粒),Ti(99.999%,粉末),Bi(99.8%,块状)按照Cd、S化学计量为1:1称量混合,称取16.0g的单质硫和56.0g的单质镉。以锆球为研磨球,在研钵中进行常规研磨破碎,破碎时间为30min。球磨比为5:1,球磨转速为100rpm,球磨60min。再将混合物装在高压成型机中,控制其工作压力为2Gpa,工作温度为1273K,工作时长为60min。
    [0031](2)按照化学计量比A x CdS(A:Cu、Al、Ag、Zn、Ti、Bi,x=0.005,0.01,0.02)称量纯度大于99.99%的单质原料Cu、Al、Ag、Zn、Ti、Bi,再进行(1)同等条件下的球磨。
    [0032](3)待(1)中混合物冷却后再对其使用(1)同等条件下的球磨,并按照化学计量比A x CdS(A:Cu、Al、Ag、Zn、Ti或Bi,x=0.005,0.01,0.02)进行掺杂混合。所述混合料粉粒颗粒直径为50μm-500μm。
    [0033](4)将掺杂混合后的产物进行第二次高压成形。其第二次高压成形的工作压力条件为2Gpa,工作温度为1173K,工作时长30min。
    [0034](5)将(4)所得产物冷却后,再次以(1)同等条件下的球磨混合均匀,在60MPa,1023K条件下进行等离子放电烧结10分钟得到最终的块体样品。测定所得掺杂不同金属元素的样品zT值,结果如表1所示。
    [0035]表1
    [0036]实施例2
    [0037]本实施例与实施例1基本相同,不同之处在于,本实施例中,所述第二次高压成型的工作压力条件为先以5℃/min的升温速度先升至900℃,保温1h,然后再以3℃/min的升温速度升温至1000℃,保温40min,之后以5℃/min的降温速度降至室温。测定所得掺杂不同金属元素的样品zT值,结果如表2所示。
    [0038]表2
    [0039]实施例3
    [0040]本实施例与实施例1基本相同,不同之处在于,本实施例中,所述第二次高压成型的工作压力条件先以5℃/min的升温速度先升至900℃,保温1.5h,然后再以3℃/min的升温速度升温至1000℃,保温30min,之后以5℃/min的降温速度降至室温。测定所得掺杂不同金属元素的样品zT值,结果如表3所示。
    [0041]表3
    [0042]本具体实施例仅仅是对本发明的解释,并不是对本发明的限制,本领域技术人员在阅读完本发明说明书后,在本发明基础上做一些修改或改进,但是只要在本发明的权利要求范围内都受到专利法的保护。
    同族专利
    暂无同族专利