会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 6. 发明授权
    • Method and system of pulsed or unsteady ejector
    • 脉冲或不稳定喷射器的方法和系统
    • US06308740B1
    • 2001-10-30
    • US09639187
    • 2000-08-15
    • Brian R. SmithDaniel N. MillerPatrick J. YagleErich E. BenderKerry B. Ginn
    • Brian R. SmithDaniel N. MillerPatrick J. YagleErich E. BenderKerry B. Ginn
    • E03B500
    • F02C9/50F02C7/04F04B45/04F04F5/16F04F5/54Y10T137/87619Y10T137/87652
    • The present invention reveals a method and apparatus for more efficiently injecting a primary fluid flow in a fluid ejector used to pump lower velocity fluid from a secondary source. In one embodiment, the primary fluid flow is a pulsed or unsteady fluid flow contained within an inner nozzle situated within a secondary flow field. This secondary fluid flow is bounded within the walls of an ejector or shroud. The secondary and primary fluid flows meet within the ejector shroud section wherein the secondary fluid flow is entrained by the primary fluid flow. The geometry of the ejector shroud section where the primary and secondary fluids mix is such as to allow the beginning of primary injector pulse to be synchronized with an acoustic wave moving upstream through the ejector initiated by the exiting of the previous pulse from the ejector shroud. The ejector's geometric properties are determined by the acoustic properties, frequency, duty cycle, and amplitude, of the pulsed primary fluid flow. Furthermore, the frequency, duty cycle and amplitude of the primary fluid flow may be varied in order to vary the efficiency of the injector.
    • 本发明揭示了一种用于在用于从次级源泵送较低速度流体的流体喷射器中更有效地喷射主流体流的方法和装置。 在一个实施例中,主流体流是包含在位于二次流场内的内部喷嘴内的脉冲或不稳定流体流。 该次级流体流动在喷射器或护罩的壁内。 次级和初级流体流动在喷射器护罩部分内相交,其中次流体流被主流体流动夹带。 初级和次级流体混合的喷射器护罩部分的几何形状允许初级喷射器脉冲的开始与通过喷射器的上游移动的声波同步,该喷射器由从喷射器护罩的先前脉冲的离开开始。 喷射器的几何特性由脉冲初级流体流的声学特性,频率,占空比和幅度决定。 此外,可以改变初级流体流的频率,占空比和幅度,以改变喷射器的效率。
    • 9. 发明授权
    • Vortex generation device
    • 涡流生成装置
    • US09079658B2
    • 2015-07-14
    • US12869884
    • 2010-08-27
    • Brian R. SmithPatrick J. Yagle
    • Brian R. SmithPatrick J. Yagle
    • B64C1/38B64C23/06
    • B64C23/06Y02T50/162
    • A vortex generation device for reducing drag on an upswept aircraft fuselage afterbody and including a vortex generator vane that extends longitudinally from along an outer mold line of the fuselage of an aircraft adjacent an upswept afterbody of the fuselage and that is configured and positioned to reduce drag on an upswept aircraft fuselage afterbody by developing vortices that counteract vortices generated along such an upswept fuselage afterbody. The vane is disposed aft of a side paratrooper jump door of the aircraft fuselage and has a spine and leading end that are faired smoothly into the mold line of the fuselage.
    • 一种涡流发生装置,用于减少上行的飞行器机身后部的阻力,并包括涡流发生器叶片,该涡流发生器叶片沿着机身机身的外部模具线在机身的上升后身体之间纵向延伸,并且被配置和定位成减小阻力 通过开发涡流来抵抗沿着这种上升的机身后身产生的涡流,在一个上升的机身后身上。 叶片位于飞机机身的侧伞式跳伞的后方,并具有顺利进入机身模具线的脊柱和前端。