A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation, said rotor blade assembly comprising: a shank portion formed from a ceramic matrix composite material; a platform portion formed from a substantially similar CMC material as that of said shank portion, said platform portion coupled to said shank portion, wherein said platform portion and said shank portion cooperate to at least partially define two opposing side portions of said rotor blade assembly, wherein said opposing side portions are angularly separated with respect to the axis of rotation; a damper; and a damper retention apparatus, wherein at least a portion of said damper retention apparatus is coupled to said shank portion, said damper retention apparatus comprises at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly, wherein said at least one angled bracket apparatus comprises a first portion and a second portion, said second portion coupled to said first portion, said first portion and said second portion define an angle therebetween, said first portion coupled to said shank portion, said second portion extends outwardly from said shank portion toward an adjacent shank portion of a circumferentially adjacent rotor blade assembly, wherein said damper retention apparatus comprises a CMC insert coupled to an interface defined by a side wall of said shank portion and an underside of said platform portion via a first interference fit and the CMC insert is coupled to the platform underside, the interface, and the second portion, wherein a pocket is formed within said CMC insert, said pocket is sized and orientated to receive at least a portion of said damper via a second interference fit, and wherein said damper is retained in said damper retention apparatus via the second interference fit. a shank portion formed from a ceramic matrix composite material; a platform portion formed from a substantially similar CMC material as that of said shank portion, said platform portion coupled to said shank portion, wherein said platform portion and said shank portion cooperate to at least partially define two opposing side portions of said rotor blade assembly, wherein said opposing side portions are angularly separated with respect to the axis of rotation; a damper; and a damper retention apparatus, wherein at least a portion of said damper retention apparatus is coupled to said shank portion, said damper retention apparatus comprises at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly, wherein said at least one angled bracket apparatus comprises a first portion and a second portion, said second portion coupled to said first portion, said first portion and said second portion define an angle therebetween, said first portion coupled to said shank portion, said second portion extends outwardly from said shank portion toward an adjacent shank portion of a circumferentially adjacent rotor blade assembly, wherein said damper retention apparatus comprises a CMC insert coupled to an interface defined by a side wall of said shank portion and an underside of said platform portion via a first interference fit and the CMC insert is coupled to the platform underside, the interface, and the second portion, wherein a pocket is formed within said CMC insert, said pocket is sized and orientated to receive at least a portion of said damper via a second interference fit, and wherein said damper is retained in said damper retention apparatus via the second interference fit.