Patent ID: 7976281

Claim:
A method of assembling a gas turbine engine rotor blade assembly, said method comprising: casting a rotor blade that includes a shank portion, an airfoil that is formed integrally with the shank portion, a first sidewall, a second sidewall joined to the first sidewall at a leading edge and at an axially-spaced trailing edge, and a platform portion that extends from the leading edge at least partially towards the trailing edge; casting a removable platform that includes: a shank portion formed unitarily with the removable platform, the shank portion configured to be positioned at least partially within a slot formed in a rotor assembly; and a cast-in plenum defined within the removable platform and the shank portion, the cast-in plenum having an exit positioned in flow communication with the platform portion and an entrance positioned in flow communication with a shank portion lower surface; and coupling the removable platform to the rotor blade using a friction fit.