Methods and apparatus for assembling gas turbine engine...

Details Methods and apparatus for assembling gas turbine engine... Methods and apparatus for assembling gas turbine engine...

2006-08-15

2006-08-15

Look, Edward K. (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Rotor having flow confining or deflecting web, shroud or...

Axially extending shroud ring or casing

C416S239000, C029S889210, C277S637000, C277S644000

Reexamination Certificate

active

07090466

ABSTRACT:
A method facilitates assembling a rotor assembly for gas turbine engine. The method comprises providing a first rotor blade that includes an airfoil, a platform, a shank and a dovetail, 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 is defined between the first and second blades. The method also comprises 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, 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.

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patent: 6776583 (2004-08-01), Wang et al.
patent: 6932575 (2005-08-01), Surace et al.

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