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    • 6. 发明授权
    • Light emitting device
    • 发光装置
    • US08772761B2
    • 2014-07-08
    • US13203072
    • 2010-02-22
    • Kazuyuki YamaeKenichiro Tanaka
    • Kazuyuki YamaeKenichiro Tanaka
    • H01L35/24
    • H01L51/5036H01L51/5268
    • The light emitting device includes an organic electroluminescent element (20) and a diffractive optical element (30). The organic electroluminescent element (20) includes an anode layer (21), a cathode layer (22), and plural light emitting layers (231 and 232) interposed between the anode layer (21) and the cathode layer (22) and configured to emit light rays with different wavelengths. The diffractive optical element (30) is positioned in paths of light rays emitted from the organic electroluminescent element (20). The diffractive optical element (30) is designed to have different grating patterns (311 and 312) diffracting the light rays respectively emitted from the light emitting layers (231 and 232) for reducing chromatic aberration.
    • 发光器件包括有机电致发光元件(20)和衍射光学元件(30)。 有机电致发光元件(20)包括阳极层(21),阴极层(22)和介于阳极层(21)和阴极层(22)之间的多个发光层(231和232) 发出不同波长的光线。 衍射光学元件(30)位于从有机电致发光元件(20)发射的光线的路径中。 衍射光学元件(30)被设计成具有衍射从发光层(231和232)发射的光的衍射的不同的光栅图案(311和312),以减少色差。
    • 8. 发明申请
    • AIRCRAFT ENGINE
    • 飞机发动机
    • US20140026589A1
    • 2014-01-30
    • US14110016
    • 2012-04-04
    • Tatsuhiko GoiKenichiro TanakaKoji WatanabeIsao Fujii
    • Tatsuhiko GoiKenichiro TanakaKoji WatanabeIsao Fujii
    • F02C7/32
    • F16H15/00F02C7/275F02C7/32F02C7/36F05D2260/4031F05D2260/532F05D2270/024F05D2270/304Y02T50/671
    • To provide an aircraft engine in which an accessory can be directly supported with no accessory gearbox intervening to thereby suppress an increase in size thereof, the aircraft engine (E) includes a take-out shaft (11) having a first end portion, connected with an engine rotary shaft (9) and extending in a radially outward direction, and also having a second end portion connected with an accessory (1), and a mounting pad (12) provided in an engine main body (EB) and to which the accessory (1) is fitted. The mounting pad (12) forms an outer perimeter of an opening (48) through which the take-out shaft (11) extends. The opening (48) is sealed by a covering (47), through which the take-out shaft (1) extends, and a sealing member (49) to seal between the covering (47) and the take-out shaft (11).
    • 为了提供一种飞机发动机,其中附件可以直接支撑,而没有中间的附件齿轮箱,从而抑制其尺寸的增加,飞行器发动机(E)包括具有第一端部的取出轴(11) 发动机旋转轴(9)并且沿径向向外的方向延伸,并且还具有与附件(1)连接的第二端部,以及设置在发动机主体(EB)中的安装垫, 配件(1)。 安装垫(12)形成开口(48)的外周边,取出轴(11)通过该外周延伸。 开口(48)由取出轴(1)延伸穿过的覆盖物(47)和用于密封覆盖物(47)和取出轴(11)之间的密封构件(49)密封, 。