| 摘要 |
A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade 40, that includes an airfoil 42 a platform 44 a shank 46 and a dovetail 48, coupling the first rotor blade to a rotor shaft using the dovetail, and coupling a second rotor blade to the rotor shaft such that a shank cavity 98 is defined between the first and second blades. The method also comprises inserting a seal pin 58 into the horizontal platform seal pin slot such that a gap defined between the first and second rotor blade platforms are substantially sealed wherein the seal pin includes a first end 400, a second end 402 and a substantially cylindrical body 404 extending therebetween and sized to frictionally engage the slot, wherein at least one of the first and second ends has a cross-sectional area that is smaller than a cross-sectional area of the body. |
