Methods and apparatus for limiting fluid flow between adjacent rotor blades

摘要

A rotor assembly for a gas turbine engine includes a plurality of radially extending and circumferentially spaced rotor blades and a seal. Each of the blades includes a platform including a radially outer surface and a radially inner surface. The platform radially outer surface defines a surface for fluid flowing thereover. The seal includes at least one hollow member coupled to each rotor blade platform radially inner surface that is configured to reduce fluid flow through a gap defined between adjacent rotor blades.