A gas turbine engine, comprising: a fan section, comprising: a plurality of fan blade assemblies each being removably attached to a rotor of the fan section, wherein each fan blade comprises: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil, wherein the metal root is removably secured to a complimentary slot located in a surface of the rotor wherein the non-linear composite airfoil has a first root portion and the metal root has a slot for slidably receiving the first root portion therein; a first locking mechanism and a second locking mechanism for removably securing the first root portion to the slot and the metal root to the rotor, wherein the first locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the first end of the rotor and the second locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the second end of the rotor, and wherein the locking ring of the first locking mechanism has an enlarged portion configured to cover end portions of both the first root portion and the metal root; a compressor section; a combustor section; and a turbine section. a fan section, comprising: a plurality of fan blade assemblies each being removably attached to a rotor of the fan section, wherein each fan blade comprises: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil, wherein the metal root is removably secured to a complimentary slot located in a surface of the rotor wherein the non-linear composite airfoil has a first root portion and the metal root has a slot for slidably receiving the first root portion therein; a first locking mechanism and a second locking mechanism for removably securing the first root portion to the slot and the metal root to the rotor, wherein the first locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the first end of the rotor and the second locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the second end of the rotor, and wherein the locking ring of the first locking mechanism has an enlarged portion configured to cover end portions of both the first root portion and the metal root; a plurality of fan blade assemblies each being removably attached to a rotor of the fan section, wherein each fan blade comprises: a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil, a non-linear composite airfoil; and a metal root removably attached to the non-linear composite airfoil, wherein the metal root is removably secured to a complimentary slot located in a surface of the rotor wherein the non-linear composite airfoil has a first root portion and the metal root has a slot for slidably receiving the first root portion therein; a first locking mechanism and a second locking mechanism for removably securing the first root portion to the slot and the metal root to the rotor, wherein the first locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the first end of the rotor and the second locking mechanism is a locking ring configured to engage a plurality of locking hooks located at the second end of the rotor, and wherein the locking ring of the first locking mechanism has an enlarged portion configured to cover end portions of both the first root portion and the metal root; a compressor section; a combustor section; and a turbine section.