Patent ID: 7090466
Filing Date: 2006-08-15
Classification: F01D,F05D,Y10T

Abstract:
1. A method for assembling a rotor assembly for gas turbine engine, said method comprising: providing a first rotor blade that includes an airfoil, a platform, a shank that extends radially inward from the platform and includes a horizontal platform seal pin slot and a dovetail that extends radially inward from the shank; coupling the first rotor blade to a rotor shaft using the dovetail; coupling a second rotor blade to the rotor shaft such that a shank cavity is defined between the first and second blades; and inserting a seal pin 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, a second end and a substantially cylindrical body extending therebetween and sized to frictionally engage the slot, 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, wherein at least one of the first and second ends includes a radius portion that is tapered from an outer peripheral surface of the body and is configured to substantially engage a shank sidewall.