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    • 56. 发明授权
    • Method for cylindrical grinding turbine engine rotor assemblies
    • 圆柱磨削涡轮发动机转子组件的方法
    • US4512115A
    • 1985-04-23
    • US501983
    • 1983-06-07
    • Robert J. Miller
    • Robert J. Miller
    • B24B19/14B24B49/04F01D5/20B24B1/00
    • B24B49/04B24B19/14F01D5/20F05D2250/231Y02T50/673Y10T29/4932Y10T29/49758
    • Blade tips of a turbine rotor assembly are ground to precision dimensions of .+-.0.025 mm (.+-.0.001 inch) when the assembly is rotated at high speed during grinding. The speed should be sufficient to produce on the blades a radial acceleration of at least 700 times the force of gravity (6,900 m/s.sup.2). For compressor rotors the direction of rotation should be such that the blades move toward their concave side, and the speed should be sufficient to produce an axial flow. High resultant tip velocities are compensated for when dry grinding titanium alloys by moving the grinding media in the same direction as the tangential velocity at the point of contact. Burrs are eliminated by feeding at a very slow rate, of the order of 0.0004 mm/s when the final dimension is approached.
    • 当组件在研磨过程中高速旋转时,将涡轮转子组件的叶片尖端磨削成+/- 0.025 mm(+/- 0.001英寸)的精密尺寸。 速度应足以在叶片上产生至少700倍重力(6.900 m / s2)的径向加速度。 对于压缩机转子,旋转方向应该使得叶片朝向其凹侧移动,并且速度应足以产生轴向流动。 通过在与接触点的切向速度相同的方向上移动研磨介质来干磨钛合金时,可以补偿高得到的尖端速度。 当接近最终尺寸时,通过以非常慢的速度进给,大小为0.0004mm / s,消除毛刺。