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    • 16. 发明申请
    • Re-pressurisation device
    • 再加压装置
    • US20090133408A1
    • 2009-05-28
    • US12081655
    • 2008-04-18
    • Daniel Robertson
    • Daniel Robertson
    • F02C9/18
    • F04D25/04F02K3/068F04D19/022
    • A gas turbine engine re-pressurisation device (36) for cooled cooling fluid, the re-pressurisation device (36) comprising a compressor stage (42) and a turbine stage (46), characterised in that a common mounting means (58) is provided between the compressor stage (42) and the turbine stage (46) such that one of the compressor stage (42) and the turbine stage (46) is located radially inwardly of the other, the re-pressurisation device (36) further comprising fluid flow directing means (44) to direct a first portion of the fluid (40) through the compressor stage (42) and a second portion (54) through the turbine stage (46).
    • 一种用于冷却冷却流体的燃气涡轮发动机再加压装置(36),所述再加压装置(36)包括压缩机级(42)和涡轮级(46),其特征在于,共同的安装装置(58) 设置在压缩机级(42)和涡轮级(46)之间,使得压缩机级(42)和涡轮级(46)中的一个位于另一级的径向内侧,再加压装置(36)还包括 流体引导装置(44)以引导流体(40)的第一部分通过压缩机级(42)和通过涡轮级(46)的第二部分(54)。
    • 17. 发明申请
    • Proprotor blade with leading edge slot
    • Proprotor刀片带前缘槽
    • US20060239824A1
    • 2006-10-26
    • US10543222
    • 2003-01-23
    • Daniel RobertsonDudley SmithCharles HollimonJimmy NarramoreB. Mullins
    • Daniel RobertsonDudley SmithCharles HollimonJimmy NarramoreB. Mullins
    • A23L3/18
    • B64C11/16B64C27/467B64C29/0033
    • A proprotor blade (27a, 27b, 127a, 127b) having a fixed, spanwise, leading edge slot (215) located in at least the inboard portion of the proprotor is disclosed. The slot (215) is formed by a selectively shaped slat (217) disposed in a selectively shaped recessed area (219) located at the leading edge (202) of the main portion of the proprotor blade. The slot (215) is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat (217) and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft (11) and civilian-type tiltrotor aircraft (111) with only minor variations to accommodate the different shapes of the proprotor blades.
    • 公开了一种具有固定的,翼展方向的前缘槽(215)的推进器叶片(27a,27b,127a,127b),其位于至少在推进器的内侧部分中。 狭槽215由位于驱动器叶片的主要部分的前缘(202)上的选择性形状的凹入区域(219)中的选择性地成形的板条(217)形成。 狭槽215被选择成形,使得在推进器叶片的下翼面表面上的气流的一部分在推进器叶片的主要部分和板条(217)之间转向并在推进器的上部翼型表面处离开 刀。 本发明可以用于军用型倾转旋翼飞机(11)和民用型倾转旋翼飞机(111),只有微小的变化来适应不同形状的推进器叶片。
    • 19. 发明申请
    • INDUCTIVELY COUPLED POWER TRANSFER RECEIVER
    • 电感耦合功率传输接收机
    • US20140306545A1
    • 2014-10-16
    • US14129754
    • 2012-07-06
    • Daniel RobertsonKunal BhargavaAiguo Hu
    • Daniel RobertsonKunal BhargavaAiguo Hu
    • H02J5/00
    • H02J50/12H01F38/14H02J5/005
    • An inductively coupled power transfer receiver including a tunable circuit and a power supply circuit. The tunable circuit includes a power receiving coil in series with a first capacitance and a first variable impedance connected in parallel with the power receiving coil. The variable impedance includes at least one impedance element and one or more semiconductor devices for controlling the effective impedance of the first variable impedance. The first variable impedance may be a second capacitance in series with the first semiconductor device; an inductance in parallel with the first semiconductor device; a second capacitance in parallel with the first semiconductor device; or a capacitance and an inductor in parallel with the first semiconductor device. The power supply circuit includes a power control circuit which provides a control signal to the first variable impedance based on an output voltage produced by the power supply circuit.
    • 一种电感耦合功率传输接收器,包括可调谐电路和电源电路。 可调电路包括与第一电容串联的受电线圈和与电力接收线圈并联连接的第一可变阻抗。 可变阻抗包括用于控制第一可变阻抗的有效阻抗的至少一个阻抗元件和一个或多个半导体器件。 第一可变阻抗可以是与第一半导体器件串联的第二电容; 与第一半导体器件并联的电感; 与所述第一半导体器件并联的第二电容; 或与第一半导体器件并联的电容和电感器。 电源电路包括功率控制电路,其基于由电源电路产生的输出电压向第一可变阻抗提供控制信号。