Rotor blade assembly

A method comprising the steps of:

• extending a composite blade portion a length from a root to a tip, wherein a leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root;
• fixing a base portion to the composite blade portion proximate to the root;
• extending a sheath around the composite blade portion and positioned along the length adjacent to the base portion and between the root and the end point of the leading edge, wherein said sheath is spaced apart from said composite blade portion by a gap therebetween that extends along the length;
• and
• releasably connecting the sheath to at least one of the base portion and the composite blade portion.

An aircraft propulsion device comprising:

• a compressor section;
• a combustor section operable to receive compressed fluid from said compressor section;
• a turbine section operable to receive combustion gases from said combustor section;
• an exhaust section operable to receive combustion gases from said turbine section;
• a rotor assembly positioned downstream of said exhaust section and including:
• a composite blade portion extending a length from a root to a tip, wherein a leading edge of said composite blade portion extends from said tip to an end point along said length between said tip and said root;
• a base portion fixed to said composite blade portion proximate to said root and formed from a different material than said composite blade portion;
• and
• a sheath extending around said composite blade portion and positioned along said length between said root and said end point of said leading edge, said sheath positioned such that combustion gases exiting said exhaust section directly impinge on said sheath,
• wherein said sheath is mounted on said base portion and/or wherein said sheath is mounted on said composite blade portion.