Rotor blade and fan

A rotor blade used for any one of a fan and a compressor of an aircraft engine, and using a composite material of fibers and a matrix resin as a constituent material, the rotor blade comprising:

• a rotor blade main body provided with a ventral surface and a dorsal surface;
• and
• a rotor blade root portion formed integrally on a base end side of the rotor blade main body;
• wherein the rotor blade main body is formed by stacking a plurality of composite sheets each made from the fibers and the matrix resin, and includes a plurality of first composite sheet groups and a plurality of second composite sheet groups which are provided in a blade thickness direction;
• wherein the plurality of first composite sheet groups and the plurality of second composite sheet groups are provided on mutually opposite sides with respect to a reference plane between two of the composite sheets stacked on one another;
• wherein each first composite sheet group includes a plurality of the composite sheets which are stacked one on another from the reference plane toward the dorsal surface, and which are different from one another in terms of an orientation angle of the fibers;
• wherein each second composite sheet group includes a plurality of the composite sheets which are stacked one on another from the reference plane toward the ventral surface, and which are different from one another in terms of the orientation angle of the fibers;
• wherein a stacking pattern of the plurality of composite sheets in the first composite sheet group from the reference plane toward the dorsal surface and a stacking pattern of the plurality of composite sheets in the second composite sheet group from the reference plane toward the ventral surface are the same;
• wherein a composite direction of orientation directions of the fibers in the plurality of composite sheets in each of the first composite sheet group and the second composite sheet group inclines to a trailing edge from a span direction;
• and
• wherein the composite direction in each of the first composite sheet group and the second composite sheet group inclines to the trailing edge by 20 degrees to 45 degrees from the span direction.