Invention Grant
US08727733B2 Gas turbine compressor last stage rotor blades with axial retention 有权
燃气轮机压缩机最后阶段转子叶片具有轴向保持力

Gas turbine compressor last stage rotor blades with axial retention
Abstract:
A rotor blade and blade retention key assembly includes: a radially outer airfoil, a shank and a radially inner attachment dovetail. The attachment dovetail has a radially innermost surface formed with a notch at one axial end thereof, and a retention key is received in the notch, and rotatable from a retracted position where a retention key portion is substantially flush with the radially innermost surface, to an extended position where the retention key portion projects inwardly from said radially innermost surface and into a recess or pocket formed in a rotor wheel slot to prevent axial movement of the blade within the slot.
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