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    • 1. 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。
    • 7. 发明授权
    • Dense media processing cyclone
    • 密集的媒体处理旋风
    • US5340481A
    • 1994-08-23
    • US22907
    • 1993-02-26
    • Norman B. Mullins
    • Norman B. Mullins
    • B01D21/26B04C5/081
    • B04C5/081B01D21/267B01D2221/04B04C2005/133
    • Raw coal, in slurry form, is fed to a dense media cyclone, entering tangentially into the cyclone. Three major forces act on the solid particles as they travel radially and helically inside the cyclone body, forcing the heavier particles toward the wall of the body and the lighter particles toward the center. As the lighter particles near the frustoconical portion of the cyclone body, their velocity vector changes horizontally, causing them to exit the cyclone through the adjustable vortex finder. The heavier particles exit the opposite end through the apex, of which the diameter may be changed by interchangeable apex inserts. Adjusting the vortex finder and diameter of the apex allows the selection of a desired cut size and gravity of the particles. The attributes of the cyclones allow for a separation of coal from ash and sulfur in the 28.times.325 mesh size fraction.
    • 以泥浆形式的原煤被送入密集的介质旋风分离器,切向进入旋风分离器。 三个主要的力量作用在固体颗粒上,因为它们在旋风体内部径向和螺旋状地运动,迫使较重的颗粒朝向身体的壁并且较轻的颗粒朝向中心。 作为旋风体的截头圆锥体附近的较轻的颗粒,它们的速度矢量水平变化,使得它们通过可调节的涡流发生器离开旋风分离器。 较重的颗粒通过顶点离开另一端,直径可以通过可互换的顶点插入物来改变。 调整涡旋取样器和顶点的直径允许选择所需的切割尺寸和颗粒的重力。 旋风分离器的属性允许从28x325目尺寸级分中的煤与灰分和硫分离。
    • 9. 发明授权
    • Proprotor blade with leading edge slot
    • Proprotor刀片带前缘槽
    • US07594625B2
    • 2009-09-29
    • US10543222
    • 2003-01-23
    • Daniel B. RobertsonDudley E. SmithCharles L. HollimonJimmy C. NarramoreRobert B. Mullins
    • Daniel B. RobertsonDudley E. SmithCharles L. HollimonJimmy C. NarramoreRobert B. Mullins
    • B64C39/00
    • 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。